World of Ham Radio 1997/WOHR97_AmSoft_(1997-02-01).iso/sat/sat_03/amsoft.iii

Text File | 1997-02-01 | 404KB | 9,051 lines

        WHATS-UP.DOC Release 1.40 Page 1



                            WHATS-UP (c) Joe Kasser, G3ZCZ, 1991-1996
                                           _______
             Joe Kasser G3ZCZ/W3      ____|__     |                  (tm)
                  POB 3419              --|       |    |-------------------
          Silver Spring, Md. 20918        |   ____|__  |  Association of
            Voice [phone]          |  |       |_|  Shareware
         Data BBS [phone]          |__|   o   |    Professionals
        Internet [e-mail]  -----|   |   |---------------------
                                             |___|___|    MEMBER

         The program is distributed as a Shareware product. You may freely
        copy and share the product for non commercial use, with your
        friends, classmates, associates and radio hams. If you decide to use
        the product, you are asked to become a registered user by completing
        the registration form and sending it, and $35.00 (drawn on a US Bank
        please) or equivalent in foreign currency to the author. Mastercard
        and Visa are accepted if more convenient.

         Upon receipt of your registration, you will receive one free update
        disk, telephone and mail (electronic and regular) support. Please do
        not use packet radio mail for commercial messages, or even those
        that may be construed as such by individual SYSOPS through whose
        BBSs the messages may pass.

         This product may not be sold or distributed with another product
        without the express written permission of Joe Kasser, G3ZCZ. Joe
        Kasser, G3ZCZ will only support unmodified copies of this software.
        Your comments and suggestions for changes are however welcome. If
        you are the first to suggest a change that is implemented, you will
        be sent a complimentary copy of the disk with the change
        incorporated.

         European Radio Amateur users may register (24.00 Pounds Sterling,
        VAT) and obtain support from Terry Dansey at ReadyCrest Ltd., PO Box
        75, Chatham, Kent, ME5 9DL, England. ReadyCrest Ltd., accepts credit
        cards (Access, Visa, MasterCard and Eurocard). Telephones: Voice 44
        (0)634-687168, FAX [phone], Data (BBS) 44 (0)634-200931.

         Potential Commercial and Educational Institution Users please
        contact Joe Kasser directly for modifications and/or details of Site
        licensing.




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                                      Table of Contents

        1.0 Introduction .......................................1
         1.1 Capabilities of WHATS-UP ..........................3
         1.2 Program Requirements ..............................4
         1.3 Packet Link Quality Measurements ..................5
         1.4 Copying Non-packet Telemetry ......................5
         1.5 Obtaining Updates .................................5
         1.6 Limit Checking ....................................6
         1.7 Radio Control .....................................6
         1.8 Using Different Terminal Units and TNCs ...........6
              1.8.1 PK-232 .....................................6
              1.8.2 KAM ........................................6
              1.8.3 MFJ-1278 ...................................7
              1.8.4 TNC1, TNC2 and PK-88 .......................7
              1.8.5 PK-900 .....................................7
              1.8.6 DSP-232 ....................................7
         1.9 Upgraders Note Incompatibility ....................7
         1.10 Logging Notes ....................................7
         1.11 SAREX/MIR automatic connect/digipeat mode ........8
         1.12 Self contained CW terminal .......................8
         1.13 Parallel port Interface ..........................8
         1.14 Equipping yourself for OSCAR ....................10

        2.0 Customization .....................................12
         2.1 Bringing WHATS-UP up for the First Time ..........12
         2.2 Editing the Configuration File ...................12
         2.3 Starting the program .............................13
              2.3.1 Default ...................................13
              2.3.2 User Chosen spacecraft ....................13
              2.3.3 Custom Mode ...............................14
         2.4 Screen Areas .....................................14
         2.5 Setting Up Customized Display Pages ..............15
              2.5.1 Customizing Analog Telemetry Channel
                                                 Displays .....15
              2.5.2 Customizing Status Telemetry Channel
                                                 Displays .....16
              2.5.3 Customizing Packet Header Displays ........16

        3.0 Modes .............................................17
         3.1 Standby Mode .....................................17
         3.2 Interactive Mode .................................17
         3.3 Real Time Mode ...................................17
         3.4 Orbital Dynamics Mode ............................17


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         3.5 Playback Mode ....................................19
         3.6 (Data) Extraction Mode ...........................19
         3.7 Mutual Visibility Mode ...........................19
         3.8 Audio Warnings and Orbit Data Displays ...........20
         3.9 Autotrack ........................................20

        4.0 Menus .............................................22
         4.1 Function Keys ....................................22
              4.1.1 FK 1 Capture to disk Toggle ...............22
              4.1.2 FK 2 Type of display
                           Engineering Units/Raw Byte Toggle ..22
              4.1.3 FK 3 Select display page ..................22
              4.1.4 FK 4 Change Doppler frequency display .....23
              4.1.5 FK 5 Display MH list ......................23
              4.1.6 Alt-B send a 'Break' to the TNC ...........23
              4.1.7 Alt-C connect to another packet station ...23
              4.1.8 Alt-D disconnect from another
                                       packet station .........23
              4.1.9 Alt-F flush receiver buffer ...............23
              4.1.10 Alt-I autotrack toggle ...................23
              4.1.11 Alt-J jump to DOS (shell) ................23
              4.1.12 Alt-P Printer on/off toggle ..............24
              4.1.13 Alt-S Sound on/off toggle ................24
              4.1.14 Alt-X Quit ...............................24
              4.1.15 Alt += debug toggle ......................24
              4.1.16 left arrow decreases playback speed ......24
              4.1.17 right arrow increases playback speed .....24
              4.1.18 Up arrow steps parallel port
                                       radio memory up ........24
              4.1.19 Down arrow steps parallel port
                                       radio memory down ......24
         4.2 Selections Menu ..................................24
              4.2.1 Change Display Page .......................25
              4.2.2 Edit Menu .................................25
              4.2.3 Files Menu ................................25
              4.2.4 Help Menu .................................25
              4.2.5 Jump to DOS ...............................25
              4.2.6 Modes Menu ................................25
              4.2.7 Log Menu ..................................26
              4.2.8 Orbits Menu ...............................26
              4.2.9 Radio Menu ................................26
              4.2.10 Spacecraft Menu ..........................26
              4.2.11 TNC or PK232 Menu ........................26
              4.2.12 Utilities Menu ...........................26


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              4.2.12 CW Menu ..................................26
              4.2.14 Exit to DOS ..............................26
              4.2.15 SAREX Menu ...............................26
         4.3 Modes Menu .......................................26
              4.3.1 Extract From Playback File ................27
              4.3.2 Interactive Mode ..........................27
              4.3.3 Orbital Parameters ........................27
              4.3.4 Mutual Visibility .........................27
              4.3.5 Playback Mode .............................27
              4.3.6 Real Time Mode ............................27
         4.4 Edit Menu ........................................27
              4.4.1 Edit Doppler File .........................30
              4.4.2 Any File ..................................30
              4.4.3 Edit Keplerian Element File ...............30
              4.4.4 Edit Spacecraft Configuration File ........30
              4.4.5 Pick Capture-to-disk File .................30
              4.4.6 Edit Capture-to-disk File .................30
              4.4.7 Edit WHATS-UP.SYS .........................30
              4.4.8 Two Files .................................30
              4.4.9 Edit Doppler Channel File .................31
              4.4.10 Edit Doppler Data File ...................31
              4.4.11 Pick Spacecraft Configuration File .......31
              4.4.12 Edit Today's Data ........................31
         4.5 Files Menu .......................................31
              4.5.1 Change Directory Path .....................31
              4.5.2 Change Playback File ......................31
              4.5.3 View Playback File ........................32
              4.5.4 Show Spacecraft Capture-to-disk Files .....32
              4.5.5 Show Data Files ...........................32
              4.5.6 Show Files for 1 Spacecraft ...............32
         4.6 Orbits Menu ......................................32
              4.6.1 Pick AMSAT Format Element Set .............32
              4.6.2 Edit Default Keplerian Element File .......33
              4.6.3 Load Element File .........................33
              4.6.4 Set Ref S/C (Mutual Visibility) ...........33
              4.6.5 Pick NASA 2 Line Element Set ..............33
              4.6.6 Show next pass ............................33
              4.6.7 Set Ref = Sun (Mutual Visibility) .........34
              4.6.8 View Spacecraft Orbit Elements ............34
              4.6.9 Show/hide Sun Data ........................34
         4.7 Radio Menu .......................................35
              4.7.1 Turn Doppler Tracking ON/OFF ..............35
              4.7.2 Set New Frequency .........................35
              4.7.3 Change Doppler Interval ...................35


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              4.7.4 Set Radio Modulation ......................36
              4.7.5 Read VFO A Frequency ......................36
              4.7.6 Set Default Frequency .....................36
              4.7.7 Select VFO A/B ............................36

              4.7.10 Set Current Radio Memory .................36
              4.7.11 Step Radio Memory Down ...................36
              4.7.12 Set Radio Memory Scan Delay ..............36
              4.7.13 Set Scan Radio Memory ON/OFF .............37
              4.7.14 Select Radio Memory ......................37
              4.7.15 Step Radio Memory Up .....................37
         4.8 Spacecraft Menu ..................................37
              4.8.1 Show Spacecraft Configuration File ........37
              4.8.2 Default Spacecraft ........................37
              4.8.3 picK Spacecraft ...........................37
              4.8.4 Change Spacecraft .........................38
              4.8.5 Pick Ops. Schedule ........................38
              4.8.6 Show Ops. Schedule ........................38
         4.9 TNC Menu .........................................38
              4.9.1 UoSAT ASCII Beacon ........................39
              4.9.2 Phase 3 RTTY Beacon .......................39
              4.9.3 Set Morse Code (CW) .......................39
              4.9.4 Fuji/MicroSat ASCII Packet ................39
              4.9.4 Configure TNC .............................39
              4.9.5 FM Packet .................................39
              4.9.6 SARA ASCII Beacon .........................40
              4.9.6 Select MFJ-1278 Radio Port
                        (if TNC is an MFJ 1278) ...............40
              4.9.7 Select AO-13 PSK (if TNC is a DSP-2232) ...40
              4.9.8 Select 9600 Baud Packet
                        (if TNC is a DSP-2232 or PK-900) ......40
         4.10 Utilities Menu ..................................40
              4.10.1 Change Directory Path ....................40
              4.10.2 Enable/Disable RS-232 Port ...............40
              4.10.3 Enable/Disable TNC Port
              4.10.4 Turn MET Window ON/OFF ...................41
         4.10.5 Show Space on Disk ............................41
              4.10.6 Reset Header Counters ....................41
              4.10.7 Show Defaults ............................41
              4.10.8 Show Files ...............................41
              4.10.9 Show Color Chart .........................42
              4.10.10 Reconfigure WHATS-UP ....................42
         4.11 Debug Menu ......................................42
              4.11.1 CW Tone Test .............................42


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              4.11.2 Turn Debug OFF ...........................42
              4.11.3 Set Frequency ............................42
              4.11.4 Interrogate Radio ........................43
              4.11.5 Show Defaults ............................43
              4.11.6 Command Radio ............................43
              4.11.7 Speak Frequency ..........................43
              4.11.8 Identify Radio ...........................43
         4.12 Log Menu ........................................43
              4.12.1 Alt-A Append Entry .......................44
              4.12.2 Alt-E Edit Log Entry .....................45
              4.12.3 Alt-H Scan Log by Call ...................45
              4.12.4 Pack Logbook .............................45
              4.12.5 Alt-S Scan Log by Call ...................45
              4.12.6 Alt-U Toggle Delete Mark .................45
              4.12.7 Alt-X eXit Log ...........................46
              4.12.8 Ins Toggle Insert Mode ...................46
              4.12.9 End Show Last Page .......................46
              4.12.10 Home Show First Page ....................46
              4.12.11 PgUp Move Up One Page ...................46
              4.12.12 PgDn Move Down One Page .................46
              4.12.13 Up Arrow Move Up One Entry ..............46
              4.12.14 Down Arrow Move Down One Entry ..........46
         4.13 SAREX Menu ......................................46
              4.13.1 Set Attack Mode ON/OFF ...................47
              4.13.2 Change SAREX Call ........................47
              4.13.3 Set Attack Mode Attack Mode [QCB] ........47
              4.13.4 Reset SAREX Flags ........................48
              4.13.5 Turn Zap R0MIR-1 ON/OFF ..................48
              4.13.6 Single/Multiple User Connects ............48
         4.14 CW Menu .........................................48
              4.14.1 Sound Text ...............................49
              4.14.2 Set CW Speed .............................49
              4.14.3 Turn CW keyboard ON/OFF ..................49
              4.14.4 Set CW Note ..............................50
              4.14.5 Show CW Memories .........................50
              4.14.6 Transmit Text ............................50
              4.14.7 Slow CW Down .............................50
              4.14.8 Speed CW Up ..............................50
              4.14.9 Change CW Memory 1..10 ...................50

        5.0 Orbital Elements ..................................51
         5.1 Basics ...........................................51
         5.2 Orbital Trajectories .............................51
         5.3 Types of orbits ..................................52


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              5.3.1 Kepler's Laws .............................53
          5.4 Orbital Elements ................................53
              5.4.1 Angle of Inclination ......................54
         5.4.2 Right Ascension of Ascending Node (RAAN) .......54
              5.4.3 Eccentricity and Semimajor Axis ...........55
              5.4.4 Decay Rate ................................56
              5.4.5 Argument of Perigee .......................56
              5.4.6 Epoch Time (of Ascending Node)
                        and Revolution Number .................56
              5.4.7 The Mean Motion ...........................57
              5.4.8 The Catalog Number ........................57
              5.4.9 Mean Anomaly ..............................57
         5.5 Anticipated Spacecraft Lifetimes .................57
              5.5.1 Orbital Decay .............................57
              5.5.2 Battery lifetime ..........................58
              5.5.3 Radiation Damage ..........................58

        6.0 The Spacecraft ....................................60
         6.1 Receiving system components ......................61
              6.1.1 Antennas ..................................61
              6.1.2 Receivers .................................62
              6.1.3 Terminal Units and Modems .................63
         6.2 Receiving Signals from DOVE ......................64
         6.3 Receiving Signals from UO-2 ......................65
         6.4 Receiving Signals from AO-13 .....................65
         6.5 Receiving PSK Modulated Signals in the 70cm Band .66

        7.0 Decoding Spacecraft Telemetry .....................68
         7.1 DOVE (DO-17) .....................................69
         7.2 UoSAT-2 ..........................................72
         7.3 AO-13 ............................................75
         7.4 AO-16, WO-18 and LO-19 ...........................83
         7.5 Fuji-OSCAR 20 ....................................91

        8.0 Spacecraft No Longer Active ......................101
         8.1 Fuji-OSCAR 12 ...................................101
         8.2 SARA-OSCAR 23 ...................................104
              8.2.1 The Primary Mission ......................105
              8.2.2 The Secondary Mission ....................106
              8.2.3 The Downlink .............................107
              8.2.4 The Onboard Electronics ..................107
              8.2.5 The Power System .........................108
              8.2.6 Mechanical integration ...................108
              8.2.7 Thermal Control ..........................109


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              8.2.8 Educational Opportunities ................109
         8.3 ARSENE ..........................................110
              8.3.1 Arsene Telemetry Equations ...............110
              8.3.2 ARSENE Digital status telemetry ..........114
         8.4 AO-21 (RM-1) ....................................115

        9.0 File formats .....................................124
         9.1 Configuration File (WHATS-UP.SYS) ...............124
              9.1.1 Your callsign ............................125
              9.1.2 Default spacecraft Name ..................125
              9.1.3 Station Latitude .........................125
              9.1.4 Station longitude ........................126
              9.1.5 Station Altitude .........................126
              9.1.6 Station minimum antenna elevation
                             for acquisition .................126
              9.1.7 Default Kepler file ......................126
         9.1.8 UTC offset ....................................126
              9.1.9 Default directory path ...................126
              9.1.10 Default extracted data file .............126
              9.1.11 Default file name
                        with list of telemetry parameters
                        to extract file ......................126
              9.1.12 TNC Type ................................127
              9.1.13 Serial port to TNC ......................127
              9.1.14 PC TNC Serial baud rate .................127
              9.1.15 PC TNC port data bits ...................127
              9.1.16 PC TNC port Stop bits ...................127
              9.1.17 PC TNC Port parity bits .................127
              9.1.18 Status (top) window color ...............127
              9.1.19 Incoming window color ...................127
              9.1.20 Outgoing window color ...................128
              9.1.21 Prompt window color .....................128
              9.1.22 Alarm window color ......................128
              9.1.23 Bottom window color .....................128
              9.1.24 Emphasis color ..........................128
              9.1.25 Option color ............................128
              9.1.26 Parameter changed color .................128
              9.1.27 Parameter limit exceeded color ..........128
              9.1.28 Orbit element window color ..............128
              9.1.29 Orbit element window In range color .....128
              9.1.30 Orbit element window early warning
                                         color ...............128
              9.1.31 Orbit element window next one up
                                         color ...............128


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              9.1.32 Logbook window color ....................128
              9.1.33 SAREX call display color in
                                 Status window ...............128
              9.1.34 Active color ............................128
              9.1.35 Orbit element post pass color ...........128
              9.1.36 Orbit alert dit time ....................128
              9.1.37 Orbit alert note ........................128
              9.1.38 Flag Sound ..............................128
              9.1.39 Doppler display Flag ....................129
              9.1.40 TNC Command to select modem for CW ......129
              9.1.41 TNC Command to select modem for
                                  UoSAT ASCII 1200 baud ......129
              9.1.42 TNC Command to select modem for
                                  1200 baud PSK ..............129
              9.1.43 TNC Command to select modem for
                                  400 baud AO-13 PSK .........129
              9.1.44 TNC Command to select modem for
                                  9600 baud packet ...........129
              9.1.45 TNC Command to select modem for
                                  1200 baud FM AFSK ..........129
              9.1.46 Logbook file ............................129
              9.1.47 QSO Logging flag ........................129
              9.1.48 Minimum angle of the sun for darkness
                                       at your QTH ...........129
              9.1.49 TNC stream switch character .............130
              9.1.50 Spacecraft Configuration File Linkages ..130
              9.1.51 Marker and Comment line .................130
              9.1.52 CW Memory contents ......................131
              9.1.53 The marker line .........................131
              9.1.54 TNC configuration commands ..............131
         9.2 Spacecraft Parameter Files ......................131
              9.2.1 Spacecraft ID ............................132
              9.2.2 Spacecraft Suffix ........................132
              9.2.3 Beacon Frequency .........................133
              9.2.4 Doppler Measurement File .................133
              9.2.5 Spacecraft Identification in
                                  Keplerian Element File .....133
              9.2.6 Doppler Measurement Sample Interval ......133
              9.2.7 Initial Frequency Offset .................133
              9.2.8 Autotrack flag ...........................133
              9.2.9 Modulation ...............................134
              9.2.10 Data Type ...............................134
              9.2.11 Receiver Type ...........................134
              9.2.12 Receiver Address ........................134


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              9.2.13 PC Serial port to Radio .................135
              9.2.14 PC Radio port Serial baud rate ..........135
              9.2.15 PC Radio port data bits .................135
              9.2.16 PC TNC port Stop bits ...................135
              9.2.17 PC Radio Port parity bits ...............135
              9.2.18 Post pass delay .........................136
              9.2.19 Station minimum usable pass time ........136
              9.2.20 Early warning time (EWT) ................136
              9.2.21 SAREX/Mir Callsign ......................136
              9.2.22 SAREX/Mir Header Delay ..................136
              9.2.23 SAREX/Mir Attack Mode ...................136
              9.2.24 SAREX/Mir Beacon Text ...................137
              9.2.25 LPT parallel port
                        radio memory parameters ..............137
              9.2.26 Selected or default display page number .137
              9.2.27 Page Definitions ........................137
              9.2.28 Telemetry Parameter Configuration .......137
              9.2.29 Digital Telemetry Status Channels .......144
              9.2.30 Packet/Link Parameters ..................146
         9.3 Telemetry Channel Extraction File ...............148
         9.4 Extracted Telemetry Data File ...................149
         9.5 Doppler File ....................................149
              9.5.1 The Time .................................149
              9.5.2 The Doppler Mark .........................150
              9.5.3 The Frequency ............................150
              9.5.4 The Doppler Shift ........................150
              9.5.5 The Measured Shift .......................150
              9.6 Kepler Element Files (*.TLE) ...............151
         9.7 AMSAT Format Element File (*.AMS) ...............152
              9.8 Spacecraft Operations File .................153

        10.0 Glossary ........................................155

        11.0 References and Further Reading ..................156

        12.0 Change History ..................................157

        13.0 Obtaining Further Information ...................158

        14.0 Other Products by Joe Kasser, W3/G3ZCZ ..........159
        14.1 PC-HAM 3.52 .....................................159
              14.1.1 LOGBOOK..................................159
              14.1.2 CONTEST .................................159
              14.1.3 CQSS ....................................159


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              14.1.4 WHATSON .................................159
        14.2 STARTREK The Computer Program ...................159
        14.3.LAN-LINK 2.34 ...................................160
        14.4 ELMER 1.00 ......................................161
        14.5 BASIC PACKET RADIO ..............................162

        15.0 How Shareware Works .............................164

        Appendix 1 WHATS-UP 1.40 REGISTRATION FORM ...........166
        Index ................................................167




































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        1.0 Introduction

         WHATS-UP is a ground station tool for communicating through and
        monitoring the state of satellites.

         WHATS-UP is a tool which provides you the Radio Amateur, or the
        Educator, with the capability to perform experiments in spacecraft
        orbital dynamics as well as monitoring the environment onboard
        several of the Orbiting Satellites Carrying Amateur Radio (OSCAR)
        during individual passes or over long periods of time.

        WHATS-UP is a table driven program which uses configuration files to
        allow maximum flexibility. If you have a Kenwood Radio, WHATS-UP
        will monitor a default frequency, the when a spacecraft comes up
        over the horizon, WHATS-UP will tune the Radio's VFO A to the
        spacecraft beacon frequency (plus a presettable offset) and set the
        receive mode for the satellite of interest. If the Radio responds
        correctly, WHATS-UP will allow you to read back the VFO A frequency
        during the pass and capture the data to a Doppler measurement file
        for later import to a spreadsheet. At the end of the pass, WHATS-UP
        will return the radio to the default frequency and communications
        mode.

        This version of the program is configured for a TNC-1, TNC-2, PK-88,
        PK-900, DSP 2232, KAM and PK-232. Note, it will not allow you to
        copy non packet telemetry if you don't have a multi-mode terminal
        unit. It will intercept the Microsat Binary telemetry from AMSAT-
        OSCAR 16 (PACSAT or AO-16), WEBER-OSCAR 18 (WEBERSAT or WO-18) and
        LUSAT-OSCAR 19 (LUSAT or LO-19)) and display and process them as if
        they were DOVE-OSCAR 17 (DO-17) ASCII telemetry. NOTE: AMSAT have
        STILL NOT FINALIZED or PUBLISHED the Binary Telemetry Format for the
        Microsats.

         Spacecraft in the OSCAR series send back volumes of Telemetry daily
        and apart from the odd Command station, few if any Radio Amateurs or
        Educators seem to be doing anything with it. Radio Amateurs tend to
        concentrate on the communications capabilities of the spacecraft and
        ignore their telemetry completely. If they do listen to a beacon,
        it's usually just to check that the transponder is on, heaven forbid
        - to actually copy any data.

         The telemetry can tell us a story. It can tell us what is happening
        to both the spacecraft and its environment. As such it has a
        tremendous educational potential which has remained just that - a


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        potential for at least the last eight years.

         Before every satellite launch the equations and format for the
        spacecraft telemetry are published by the builders. The telemetry
        tells us about the health and welfare of the spacecraft itself, and
        something about the payload. Spacecraft health and welfare
        information tells us about the battery, solar cells and on board
        computer status. Payload information can range from information
        about transponder loading/utilization to data from instruments that
        measure the environment of the space in and around the satellite.
        Battery Telemetry is used by the command stations to determine when
        the spacecraft can be used, and when the transponders should be shut
        down. The number of individuals not associated with command stations
        who have decoded spacecraft telemetry and published their findings
        can be counted using the fingers of one hand.

         Capturing, decoding and displaying telemetry from orbiting
        spacecraft in real time, in the classroom, is an excellent way of
        introducing space science to students. Signals from these spacecraft
        are downlinked on frequencies that can be received on regular
        vhf/uhf scanner radio receivers. WHATS-UP provides an introduction
        as to how this can be done using readily available low cost
        equipment. General topics discussed cover telemetry, the spacecraft
        themselves. Groundstation hardware topics include receiving
        antennas, radio receivers and modems. Software topics discussed
        include the software used to track the spacecraft and the software
        used to both decode and display the data in real time as well as
        that for post pass analysis. Excluding the Personal Computer, a
        simple telemetry capturing groundstation can be set up for less than
        $500.00 in equipment costs.

         There is no substitute for the excitement of hands-on experience in
        awakening an interest in space. While OSCARs in the main, transmit
        down to the ground (downlink) telemetry in morse code, several of
        them also utilize standard computer literate digital data schemes
        such as BAUDOT or ASCII codes. The thrill of receiving a signal from
        space soon fades however if the data cannot be understood. Even
        after the data has been decoded, watching the temperatures on-board
        a spacecraft as it passes overhead is also of little interest, but,
        what can be made interesting is receiving and capturing the data
        over many days or even months and looking for trends and
        relationships.

         You can capture telemetry just by listening to a spacecraft and


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        copying morse code by ear writing it down with a pencil on a piece
        of paper. All you need to do is listen on the correct frequency at
        the right time and you will hear some signals. Write down what you
        hear. Apart from the thrill of copying a signal from a satellite,
        there's not much else to do with the data. While you can look up the
        conversion equations and get a snapshot of what is happening, it
        soon becomes tedious and only dedicated souls do it regularly.

         When AMSAT were building the Phase 3A spacecraft, personal
        computing was in its infancy. That was before the Apple 2 or the
        TRS-80; that was the day of the home built S-100 machine, and the
        AMSAT-GOLEM-80 Project. At that time, Karl Meinzer, DJ4ZC, had
        written a native German high level computer language called IPS.
        This language was very similar to Forth, but contained a multi-
         tasking kernel. This language was programmed into the spacecraft
        flight computer and also used in the ground command stations. Using
        a computer on the spacecraft allowed AMSAT to provide telemetry that
        could be captured by computer on the ground. While Phase 3A never
        made it into orbit (the launch vehicle malfunctioned), subsequent
        spacecraft continued to provide the same facility. Today UoSAT-2
        (UO-2), AMSAT-OSCAR 13 (AO-13), UoSAT-OSCAR 14 (UO-14), AMSAT-OSCAR
        16 (AO-16), DOVE-OSCAR 17 (DO-17), WEBER-OSCAR 19 (WO-18), LUSAT-
        OSCAR 19 (LO-19), Fuji-OSCAR 20 (FO-20) and AMSAT-OSCAR 21 (AO-21)
        are all sending back telemetry that you can capture with your PC and
        amateur radio equipment. As most non radio amateurs do not
        understand morse code, WHATS-UP concentrates on those spacecraft
        which downlink computer compatible telemetry and can be received
        with relatively simple equipment.

        1.1 Capabilities of WHATS-UP

        WHATS-UP contains the following features:

        *    Self contained CW (keyboard only - you copy audio by ear)
             satellite ground terminal with parallel port interface to Radio
             up/down frequency control.
        *    Automatic connect attempt and beaconing via MIR, SAREX or any
             other satellite with appropriate TNC.
        *    Automatic logging of Acquisition of Signal (AOS) in LAN-LINK
             compatible logbook.
        *    Display of spacecraft orbital elements and tracking data.
        *    Will automatically set your Kenwood receiver to spacecraft
             beacon frequency when the spacecraft comes above your horizon
             and return it to the default frequency when the pass is over.


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        *    Audio warning of AOS and loss of signal (LOS).
        *    Real-time, Interactive and Playback modes.
        *    Automatic Capture-to-disk of raw telemetry.
        *    Extracts telemetry channel data to a database or spreadsheet
             readable file for further analysis.
        *    Link quality measurement.
        *    Capability to display and print the raw telemetry as it is
             received.
        *    Up to 16 user configurable display pages (screens). You set the
             position on the page (width of engineering unit field, and
             number of decimal places) that a parameter is displayed at.
        *    Wild card page (parameter shows up on all pages).
        *    Selectable display of Engineering units or Hex byte for each
             display page.
        *    Display of raw packets (i.e. STATUS)
        *    Color changes if a parameter value changed between successive
             frames.
        *    Audio and visual alarms if a telemetry value exceeds, falls
             below or falls outside a preset limit value(s).
        *    Dumb split screen terminal mode with user selectable number of
             window rows.
        *    Customizable colors, PC to TNC baud rate, data parity and stop
             bits.
        *    Default spacecraft configuration files.
        *    UTC Time of day clock display (in HH:MM:SS format)

        1.2 Program Requirements

         IBM PC or clone with at least 256k memory.

         A Radio receiver and a TNC with an RS-232 interface is only
        required for real time data capture.

         The program DOES require that the packetized telemetry be received,
        and captured-to-disk with the packet header on a different line to
        the contents of the packet (HEADERLINE ON). I also suggest that you
        turn the date/time stamp on so that you will be able to playback
        your data and extract selected values and their corresponding time
        codes into a file that can be read into your spreadsheet program for
        further trend analysis.

         This version (the default) is set up to display all packets as wild
        cards (i.e. will show up on all pages), and then display several
        temperatures and solar cell array currents.


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         By putting the correct parameters in the SPACECRAFT.CNF file, you
        can set up any of the pages to display any of the telemetry channel
        data in any row and column in that page.

        1.3 Packet Link Quality Measurements

         The packet link quality part allows the following to be done. You
        can define which of the packets you want to display/count (If you
        just want to count them and not display them, set the page value to
        99). You can then view an incrementing count counter each time a
        selected packet is received. For example, using DO-17, you can also
        display the contents of the STATUS, WASH or BCRXMT packets in any
        display page. This feature allows you to get an idea of how good
        your receiving system is.

        1.4 Copying Non-packet Telemetry

         Packet telemetry, by definition is error free. The RTTY blocks from
        AO-13 on the other hand may be received with errors. These errors
        may take the form of garbled or missing characters. If your link is
        bad, and such hits do occur, you should edit the capture-to-disk
        file before you playback the telemetry and decode/display the data.

         If you get bad data in real time, look at the raw data. You will be
        able to see the quality of the link.

        1.5 Obtaining Updates

         It is anticipated that WHATS-UP is going to grow and incorporate
        features for decoding and displaying data from other spacecraft.
        Better Microsat binary telemetry decode and display capability will
        be added when AMSAT announce that the format has stabilized, and
        sufficient registered users express interest in having it. To stay
        on the mailing list and receive an update as it is released,
        register your copy, then send in a disk containing at least 1
        Megabytes (zipped) of captured data from the spacecraft of your
        choice. If you would like to exchange data with other educational
        institutions or users so as to be able to analyze more data than you
        can get on a single pass, indicate that fact and we will try and put
        you in direct touch with others who are similarly inclined.





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        1.6 Limit Checking

         Limits are only checked for parameters being displayed (in
        Engineering units). With this approach, you can set up different
        pages for different on-board subsystems, you can also set up
        different display pages of the same parameters for daylight,
        darkness and terminator crossing passes, with different limit values
        to draw your attention to changes.

        1.7 Radio Control

         Assuming you use a radio, when you first bring up WHATS-UP, it sets
        the radio VFO A to the beacon frequency of the default spacecraft
        configuration file (*.CNF). When a selected spacecraft is scheduled
        to come above your horizon WHATS-UP will tune the radio to the
        spacecraft's beacon frequency. When the pass is over, WHATS-UP will
        return the radio to the default frequency. You can thus set up a
        "dummy" configuration file for your local Packetcluster or voice
        repeater and monitor that channel as long as the selected spacecraft
        are below your horizon.

         If a pass is taking place, and a second selected spacecraft comes
        over your horizon, WHATS-UP will tune to its frequency UNLESS the
        autotrack is disabled. See Section 3.9 for a description of the
        autotrack feature.

        1.8 Using Different Terminal Units and TNCs

         This section briefly covers some of the differences between the
        various TNCs on the market. To copy PSK signals from Fuji-OSCAR 20
        and the microsats, you will need a PSK modem adapter for your TNC.
        WHATS-UP has no way of checking that it is present.

        1.8.1 PK-232

         The PK-232 does not have a software selectable TNC radio port. You
        have to use the switch on the panel. The PK-232 will receive signals
        from UO-11 properly, only if the hardware modification described in
        Section 7.2 of this document is performed.

        1.8.2 KAM

         The KAM cannot demodulate SARA's 300 baud ASCII or 1200 baud ASCII,
        so signals from SARA and UO-11 cannot be copied. The KAM 2.85


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        firmware used to develop WHATS-UP assumes vhf packet on the vhf
        port, and the non packet modes on the hf port. WHATS-UP 1.20 does
        not let you switch ports on the KAM.

        1.8.3 MFJ-1278

         The MFJ-1278 cannot copy SARA's 300 baud ASCII or UO-11's 1200 baud
        ASCII. WHATS-UP does not change the radio port. You set the radio
        command in the WHATS-UP.SYS file. If you wish to change the radio
        port, an option is provided in the Configure TNC Menu.

        1.8.4 TNC1, TNC2 and PK-88

         These TNCs only copy packet. The other modes will not work.

        1.8.5 PK-900

         This TNC is treated like a PK-232. If you have the optional 9600
        baud modem you can try for the 9600 baud microsats.

        1.8.6 DSP-232

         This TNCs will give you all known modes. The current firmware does
        not give you step track from the TNC to the Radio for PSK.

        1.9 Upgraders Note Incompatibility

         If you are upgrading from 1.30 or an earlier version the WHATS-
        UP.SYS and SPACECRAFT.CNF files in 1.40 are not compatible.

        1.10 Logging Notes

         When WHATS-UP logs an acquisition, it places some temporal
        information in the comments column. This information is, either:

        *    A check mark, if AOS is as scheduled.
        *    The number of minutes into the pass if AOS is late.
        *    A '>' and the estimated time to AOS is acquisition occurred
             when WHATS-UP computed the spacecraft as being below the
             horizon.

         This information is designed to help you update any estimates for
        AOS in the event your element set is out of date.



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        1.11 SAREX/MIR automatic connect/digipeat mode

         This feature should be used with caution as it has the potential to
        cause QRM to other stations on channel. As a safeguard, WHATS-UP
        will turn its attack mode off if it someone connects and sends a
        ':QRT:' instruction.

        1.12 Self contained CW terminal

         WHATS-UP contains a CW terminal, controlling the radio keyer and
        parallel port interface. You can connect the parallel port to the
        radio up/down buttons via the simple circuit described in Section
        1.13. With a display of the Orbit parameters, you can:

             Transmit CW by typing the characters at the keyboard.
             Copy CW by ear.
             Control the VFO to compensate for Doppler shift using the
             up/down arrows.
             Log the contacts into the logbook.

        And you don't need a TNC to do it. If you go on a cw satellite DX-
        pedition, and are taking along a laptop or notebook computer, try
        this feature. If you are staying home, try it in the shack.

        1.13 Parallel port Interface

         WHATS-UP contains a driver to interface the PC's parallel port to a
        radio. It maybe used as described in Section 1.12, or as described
        in this section.

         The interface circuit is shown in Figure 1.13. It consists of a TTL
        latching register type 75LS175 and optical isolators on the output
        side. You also need a 5 volt supply for the 74LS175 which may be
        obtained from any suitable source. Each optical isolator circuit is
        identical, so only one is shown below. A serial LED with each
        optical isolator provides visual indication that something is
        happening. You must use a strobed interface to ensure reliable
        control of each bit.

         The parts may be obtained from Radio Shack or any similar source
        and are not critical. Almost any optical isolator will do provided
        it can handle the open key voltage from the radio. If you are using
        a solid state radio which runs of a 12 Volt supply, then don't worry
        about the interface.


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        The port bit assignments are as follows:

        Bit            Assignment
         1             Key
         2             Radio up
         3             Radio down
         4..8          Unassigned/unused

         You can set the printer port assignment in the receiver address
        line of the SPACECRAFT.CNF file (Section 9.2.12).

              Figure 1.13 Simple parallel interface circuit.


                       +---------------+-----------------------< +5 volts
        PC Printer     |               |
        Port           |5V          RESISTOR (330 ohms)
           ST       -----              |      -------
        1 >--------|CK   |             |-|<|--|     |---------< key
           DB0     |     |   keyboard    LED  |     |---------< Common
        2 >--------|A  Qa|--------------------|_____|optical isolator
           DB1     |     |   radio up                      4N33 etc.
        3 >--------|B  Qb|---------------    similar isolation  -< Up
           DB2     |     |   radio down         circuits
        4 >--------|C  Qc|---------------                       -< Down
                   |     |
                   |     |Ground
                   |-----|-+
                74LS175    |
        25>----------------+--signal ground (also on 18..24).

        Notes
        1    Do not connect PC signal ground connect to radio common side.
             If you do, there is not much point in using isolation circuits.
        2    Decouple 5 Volt supply to PC Signal ground.
        3    Ground all unused inputs of the 74LS175 to avoid spurious
             effects due to transients.
        4    Use similar optical isolator connections for the up and down
             connections to the radio.
        5    Optional, but useful. Wire a 470 ohm resistor in series with a
             green LED across the 5Volts and ground.
        6    Use red LEDs in series with the optical isolators.
        7    Add pull-up resistors on PC interface lines and 74LS175 clear


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             and reset lines.


        1.14 Equipping yourself for OSCAR

        The OSCAR satellites use frequencies in the VHF and UHF bands not
        normally covered by the usual short wave or HF transceivers. Also
        since the spacecraft transponders receive on one band and transmit
        on a second, you will need to talk at them on one band and listen to
        them on a second band. That means, not only do they operate split
        frequency, but they operate split frequency on different bands.

        In order to work people via the OSCAR spacecraft, you will need
        transmitting equipment for your uplink and receiving equipment for
        the downlink. If you are already a serious VHF/UHF operator you will
        have SSB/CW equipment for the VHF/UHF bands used by the spacecraft.
        On the other hand if you are new to the satellite bands, you will
        have to purchase or otherwise obtain the necessary equipment.

        There are two types of OSCAR satellites in orbit at this time. The
        Phase 2 spacecraft are in low orbits, and carry a Mode A transponder
        with an uplink on the 2 Meter band, and a downlink on the 10 Meter
        band as well as a transceiver for a different Mode. The Phase 3
        spacecraft are in high orbits and carry a Mode B transponder with an
        uplink on the 70 Cm band and a downlink on the 2 Meter band. If you
        thus equip yourself for operation on the 2 Meter band, assuming that
        you have HF capability, you will be able to monitor signals from
        both types of satellites and may even be able to work Mode A.

        Take a look at the advertisements for 2 Meter SSB/CW transceivers in
        the magazines. They look nice, have useful specifications but the
        price! Do you really want to spend that money on a band you are not
        sure that you will be active on?. The VHF/UHF bands aren't like the
        HF ones. The majority of your contacts will be ground wave line-of-
        sight. That means that your maximum range under normal conditions
        will be between 100 and 200 miles.

        If you live in an area of high VHF/UHF activity you may find it
        worth while, because you will always have someone to talk to and
        when conditions are right, you will be able to work DX.

        Another factor to consider is the distance between the operating
        position and the antennas. Co-axial cable has significant losses at
        VHF/UHF frequencies. Satellite links are usually marginal, that


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        means that you cannot afford any reduction in your uplink power or
        in the strength of the downlink.

        Consider an alternative. In the days before commercial multi mode
        VHF/UHF equipment became available, many people got on the air using
        transverters. A transverter is a piece of equipment that contains a
        transmitting and a receiving converter. Equipment such as the old
        "Europa B" and the Microwave Modules series which are still
        available were used to good effect. The Microwave Modules and units
        made by other manufacturers are still available as you can see by
        looking at the advertisements in your favorite amateur radio
        magazine.

        The transverter must be driven by a transceiver. The output from the
        transceiver down converter is fed to the regular station receiver.
        The input to the transceiver up converter comes from a low power
        point in the transceiver. The well known FT-101 series of HF
        transceivers as well as a number of others were designed with
        transverters in mind. They are readily available on the used
        equipment market at reasonable prices. Look at those advertisements
        again, compare the cost of a used FT-101 (or similar rig) and a
        transverter with the cost of that multi mode VHF/UHF rig. Getting on
        two meters SSB this way has a number of advantages as follows.

        The FT-101 can be used as a back up HF rig in the event of a failure
        in the prime station transceiver. The FT-101 can also be modified to
        work the new WARC bands. It can thus be used in a stand alone manner
        from all bands 160 through 10 Meters.

        The transverter could even be mounted on the mast at the antenna,
        thus potentially providing a significant reduction in line losses
        bare).














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        2.0 Customization

        2.1 Bringing WHATS-UP up for the First Time

         WHATS-UP comes configured to use Com1 in the PC as the serial port
        between the PC and the PK-232, and with the serial port between the
        PC and the Kenwood Radio DISABLED (Set to 0). WHATS-UP is also
        configured to assume DOVE as the default spacecraft.

         If you type 'WHATS-UP' followed by the 'Enter' key, the program
        will load and start to do things. If the default serial ports are
        correct for your system, you need do nothing further, other than
        change the colors of the windows to your preference.

        2.2 Editing the Configuration File

         The configuration file is called WHATS-UP.SYS. You must edit it
        using option 'S' in the Edit Menu or with an ASCII word processor
        (in the non document mode) to set up the correct parameters on the
        RS-232 link between your TNC and your PC. See Section 10 for details
        of what parameter is on which line of the WHATS-UP.SYS file. If you
        wish to activate the Radio features, you must select a Radio Port.

         Before you make any changes, make sure that you do not try and edit
        your original, always work from a copy.

         These are the minimum set up items to change in the WHATS-UP.SYS
        file. Refer to Section 9 for fuller details of what items are on
        which lines. Bring up the Selections menu, the access the Edit Menu.
        choose the option for editing the WHATS-UP.SYS file. As you enter
        items on the lines listed below, delete the entries currently in
        place.

         Line 1: Enter your callsign instead of the default one. Use Capital
                 letters (Upper case). If you do not have a callsign, pick a
                 mnemonic that represents your school or organization. You
                 may use up to 10 characters. The callsign entered here,
                 will be shown at the top of the status window, next time
                 you load WHATS-UP, and will also (more important) be
                 appended to your capture-to-disk files to identify the
                 ground station which received the data.
         Line 3: Enter the latitude of your location. In the southern
                 hemisphere, use a negative number.
         Line 4: Enter the longitude of your station in degrees West of


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                 Greenwich in the range 0 to 359.9.
         Line 5: Enter the station altitude above sea level in meters. If
                 you don't know, don't change anything.
         Line 10: Enter the difference between local time in your PC and
                 UTC. For example, eastern standard time is 5.
         Line 12: Enter the name of the TNC (PK-232, PK-900, DSP-2232, TNC2,
                 KAM, MFJ1278, or PK-88).
         Line 15: If you are not using Com1 as the serial port between the
                 PC and the TNC, enter the port number on this line.
         Line 16: If you are not using 1200 baud between the PC and the TNC
                 enter the actual value on this line.
         Line 20: If you have a compatible radio with RS-232 control
                 capability, enter the port number on this line (usually
                 Port 2).

         Read Section 9.1 to see what else to change to make the PC
        communicate with the TNC and the radio.

         Save the file at this time. WHATS-UP will now work for you in its
        minimal mode. Read the manual to learn about its capabilities and
        use section 9 when you customize it to suit yourself.

        2.3 Starting the program

         You may start the program in three ways as follows.

        2.3.1 Default

         Type 'whats-up' and return (without the ' characters). This brings
        the program up in the default mode. It will read the whats-up.sys
        file to determine the spacecraft being monitored, and then prompt
        you for the mode.

        2.3.2 User Chosen spacecraft

         Type 'whats-up spacecraft' and return (without the ' characters).
        The program reads the spacecraft.sys file to load the parameters for
        the Microsat of choice, and then prompts you for the mode. Examples
        of the command are :

         'WHATS-UP DOVE' or 'WHATS-UP Fuji20'





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        2.3.3 Custom Mode

         Type 'whats-up spacecraft mode' and return (without the '
        characters). This brings the program up in the custom mode. It will
        read the whats-up.sys file to determine the spacecraft being
        monitored, and then start up in the mode you set. Valid modes are
        'p', 'i', 'o' and 'r'. Examples of the command are:

         'WHATS-UP DOVE R' or 'WHATS-UP Fuji20 R'

         If you place a command line like this in your autoexec.bat file,
        should you be copying telemetry in an unattended manner and a power
        failure take place, the system will boot up into the correct WHATS-
        UP mode when power is restored.

         When the program loads, the first thing it does is load the
        Keplerian data from the default data file and compute the current
        position of all the spacecraft. The following typical messages will
        be send during this activity.

         MIR Loaded
         RS-10/11 Loaded
         AO-13 Loaded
         UO-14 Loaded
         DO-17 Loaded
         Computing Next Pass for AO-10
         Computing Next Pass for UO-11
         Computing Next Pass for MIR
         Computing Next Pass for RS-10/11
         Computing Next Pass for AO-13
         Computing Next Pass for UO-14
         Computing Next Pass for DO-17

         If the default Keplerian data file is not present on the disk, the
        orbital mode will be disabled. If the default Keplerian data file is
        empty, WHATS-UP will abort with a Run-Time Error.

        2.4 Screen Areas

         The screen is divided into four window areas. The Status window
        occupies the top line. The prompt window occupies the bottom line.
        Raw data are always shown in the lower data area. This window also
        shows any outgoing text that you may type at the keyboard or any
        commands WHATS-UP sends to the TNC. The data area in the top half of


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        the screen contains the processed data (real time and playback), the
        raw data (interactive) and the orbital data display.

        2.5 Setting Up Customized Display Pages

         The ability to customize a display page is a unique tool provided
        by WHATS-UP. This tool allows you to group telemetry information so
        you can see how the monitor points you are interested in behave, and
        visually see the changes. You can locate information in any position
        on the screen and in any color you wish. You can also perform limit
        checking on the data, and have the "out-of-limit" show up in
        different colors and generate audible alarms.

         Setting up display pages is an orderly procedure using the
        information contained in Section 9. When you want to customize the
        displays, make a copy of the supplied spacecraft configuration file
        and work with it. Look at the format of the file, read Section 9.2
        to sure that you understand what is in the file. Use the editor to
        adjust the items in the spacecraft configuration file. After editing
        the file, reload the file to enter the changed parameters into
        WHATS-UP to see the effects of your changes. Repeat this procedure
        until you are satisfied.

         First, from the utilities menu, view the colors and decide on the
        color scheme for the window and data.

         Lay out the display page on graph paper for a screen window of 13
        rows by 78 columns.

         Decide on the name of the page. If it is a new page enter the name
        on a new line after the existing pages before the line that ends in
        an '*' character. Do not delete the '* character. After you have
        entered the page name, insert a comma character ',' and a number for
        the default page color. An example from the DOVE.CNF file for such
        an entry is shown below.

         PAYLOAD TRANSMITTER/RECEIVERS, 30

        2.5.1 Customizing Analog Telemetry Channel Displays

         The next few lines contain the analog telemetry decoding display
        information. Review Section 9.2 to see what has to be inserted in
        each of the elements. The analog telemetry lines are terminated with
        the following line, which must be present even if no data lines are


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        present.

         '* end of telemetry'

        2.5.2 Customizing Status Telemetry Channel Displays

         Section 9.2.14 describes the meaning of each item. The status
        telemetry lines are terminated with the following line, which must
        be present even if no data lines are present.

         '* end of status bytes'

        2.5.3 Customizing Packet Header Displays

         The packet header configuration lines contain the analog telemetry
        decoding display information. Details of the meaning of each item
        are given in section 9.2.15. The packet header lines are terminated
        with the following line, which must be present even if no data lines
        are present.

         '* end of packet types'

         If you want to change the colors that channels out of limit, or
        channels in which the data changed between telemetry frames are
        displayed in, you must change the entries in the WHATS-UP.SYS file.
        207 is a respectable value for the color to display data for which
        the limit has been exceeded (flashing white on red background).



















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        3.0 Modes

         WHATS-UP is designed to operate in a number of modes as listed
        below. Each mode has its own type of window display. To change
        things or select features, touch the 'Esc' key to bring up the top
        level menu. Menus in WHATS-UP are organized as a hierarchy, each
        option will take you as deep as necessary to make your selection.

        3.1 Standby Mode

         The standby Mode presents you with the Modes Menu as described in
        Section 4. This mode is activated if you bring up WHATS-UP without
        specifying a mode in the command line.

        3.2 Interactive Mode

         The Interactive mode is a dumb terminal. You can use it to give
        commands to the TNC. You should also use it to set the 'HEADERLINE
        ON'. In this mode, you will see the raw packets on the channel. You
        can also use this mode as a regular TNC program (If you do, you
        ought to get your head examined, because LAN-LINK will do the job
        much better). The capture-to-disk will turn on when the first packet
        is copied, and will turn off two minutes after the last.

        3.3 Real Time Mode

         The Real-time mode converts and displays engineering data. You can
        display up to 16 (configured by you) pages of information.
        Information that changes between successive frames, is shown in a
        different color. Information that has exceeded a preset (by you)
        limit is shown in an alarm color (default: blinking red). The
        capture-to-disk will turn on when the first packet is copied, and
        will turn off two minutes after the last.

        3.4 Orbital Dynamics Mode

         The orbital dynamics mode gives you a display of the positions of
        the spacecraft with respect to your location. If the spacecraft are
        out of range, then you see time related information. If the
        spacecraft are in range then you also see position related
        information. The time that the spacecraft comes above your horizon
        is when you acquire signals. This time is known as Acquisition of
        Signals (AOS) time. You lose signals when the spacecraft drops below
        your horizon. This time is known as Loss of Signals (LOS). WHATS-UP


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        allows you to define an early warning time (EWT) (in minutes) before
        AOS. The period of time between AOS and LOS is known as the pass.

         Orbit positional information is only as accurate as your PC clock
        and the reference Keplerian data supplied by AMSAT and other
        sources. You can expect an accuracy of within a minute or two if
        your PC clock is correct. WHATS-UP only provides time displays
        accurate to within a minute or two. Its not worth going for greater
        accuracy in most cases.

         The following information is only displayed for spacecraft in
        range.

         AZ Azimuth    - Pointing angle to spacecraft along horizon (0 =
                       North, 90 = East).
         EL Elevation  - Pointing angle to spacecraft from horizon to
                       zenith.
         RANGE         Distance between your station and the spacecraft. An
                       Up arrow next to it indicates that the altitude is
                       increasing, a down arrow, that it is decreasing.
         DPLR          Doppler shift on spacecraft's beacon signal.

         A typical example of part of the display is shown below.

        ══S/C═════WNDOW══AOS═══LOS══PASS════MA═════ALT════AZ══════EL═══RANGE
          UO-11    02:05 00:08 00:19 00:11  143     681
          AO-13    04:51       02:54 08:01  122   37723  47.92  24.91
         =DO-17    03:32 01:35 01:45 00:10  206*    792

         The first column provides information about the automatic
        sequencer.

         A check mark indicates that the spacecraft is the selected one for
             data to be captured.
         An equals sign indicates that WHATS-UP is configured to configure
             itself to tune to its beacon signal and capture data at AOS for
             that spacecraft.
         A "less than equals" sign indicates that WHATS-UP is configured to
             configure itself to tune to its beacon signal and capture data
             at EWT for that spacecraft.

         The display is color coded as follows.

        Spacecraft out of range  displayed in the default window color.


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        Spacecraft in range are displayed in the 'in range' color.
        Spacecraft within EWT are is displayed up in the EXT color. The
        spacecraft designator for the next spacecraft to come in range is
        displayed in the 'next one up' color. These colors may be configured
        to your preference in the WHATS-UP.SYS file.

        3.5 Playback Mode

         The Playback mode allows you to play back captured telemetry with 4
        speeds (speedy, slow, slower and snail's pace).

        3.6 (Data) Extraction Mode

         In this mode, data is extracted from a playback file into a file
        that can be read into a spreadsheet. If you answer the prompt for
        the default file with a non-existent filename, WHATS-UP will prompt
        you for individual channel numbers. To terminate the sequence and
        begin the extract mode, touch the 'Enter' key without entering a
        channel number. Note: Start and stop times are text string matches.

        3.7 Mutual Visibility Mode

         This mode provides a display of the mutual visibility between a
        spacecraft and all the others displayed in the window. A typical
        section of a display is shown below.

        ===S/C=WNDOW==AOS===LOS==PASS===MA====ALT=LAT====LONG==FTPRNT=D-SSP
        √MIR   00:48 22:46 22:54 00:08  66√   395 -46.25 287.01  4378 11259
         AO-10 02:42 00:39 07:09 06:29 217√ 19206 -13.89 343.58 16834 15543
         AO-13             22:02 08:28 189√ 30799 -39.77  68.49 17841  7504
        =AO-21 04:29 02:26 02:31 00:04 158√  1003  -5.67 155.89  6729  2139
         RS-12 00:14 22:11 22:23 00:11 245√   963 -24.46 111.93  6608  3646

         The information displayed in the mutual visibility mode window are
        as listed below.

         WNDOW    Time till AOS (if out of range, or time till LOS if in
                  range.
         AOS      Time of AOS. This item is not displayed if the spacecraft
                  is in range.
         LOS      Time of LOS.
         PASS     The amount of time that the pass will last. If the
                  spacecraft is in range, then this item displays the
                  minutes remaining till LOS.


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         MA       Mean Anomaly, or position of the spacecraft in its orbit
                  (see Section 5).
                  If the spacecraft have mutual visibility, a check mark '√'
                  character will be displayed following the MA value.
         ALT      The altitude of the spacecraft above sea level. An Up
                  arrow next to it indicates that the altitude is
                  increasing, a down arrow, that it is decreasing.
         LAT      The latitude of the point on the surface directly below
                  the spacecraft (sub-satellite point).
         LONG     The longitude of the point on the surface directly below
                  the spacecraft (sub-satellite point).
         FTPRINT  The diameter of the footprint of the satellite on the
                  surface of the earth.
         D-SSP    The distance between the sub-satellite point of the
                  satellite and the one for which mutual visibility has been
                  calculated.
         This mode is useful if you want to determine the possibility of a
        double hop communications link through two spacecraft, or want to
        see when Mir can work the Space Shuttle.

        3.8 Audio Warnings and Orbit Data Displays

         WHATS-UP provides audible warnings in morse code of AOS, LOS and
        EWT. Each warning consists of a letter followed by the spacecraft
        designator. An 'A' prefixes AOS, an 'L' prefixes LOS and a 'Q'
        prefixes EWT.

         WHATS-UP also shows orbit data associated with the selected
        spacecraft in the bottom window. This data which duplicates the line
        shown in the orbital mode, is there to be used in the real-time and
        interactive modes.

        3.9 Autotrack

         An autotrack flag is present in each spacecraft configuration file.
        The autotrack flag allows you to customize the way WHATS-UP switches
        radio frequencies and TNC modes. If the autotrack is disabled,
        WHATS-UP will not switch until after LOS of the satellite currently
        tracking. If the autotrack flag is enabled, WHATS-UP will switch
        radio frequency and TNC mode when a new spacecraft is present even
        if it is currently tracking one. You use the autotrack flag to stop
        WHATS-UP from switching away from a satellite in the middle of a
        pass if a new one comes up over the horizon.



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         If the autotrack flag a disabled, a flashing indicator will be seen
        next to the spacecraft name in the status window.

                                           WARNING

        If you disable the autotrack flag in the default configuration file,
        or manually load a spacecraft configuration file with the autotrack
        disabled, WHATS-UP will not change radio frequencies or TNC modes
        until the next LOS.





































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        4.0 Menus

         WHATS-UP provides various features organized in a hierarchy of
        menus. To bring up the top menu, touch the 'Esc' key.

        4.1 Function Keys

         The following function keys are active in the operational modes
        described in Section 3:

         FK 1          Capture to disk Toggle
         FK 2          Type of display Engineering Units/Raw Byte Toggle
         FK 3          Select display page
         FK 4          Change doppler frequency display
         FK 5          Display packet Monitor Heard (MH) list
         Alt-B         Send a 'Break' to the TNC Alt-C Connect to another
                       packet station
         Alt-D         Disconnect from another packet station
         Alt-F         Flush receiver buffer
         Alt-I         Autotrack toggle
         Alt-J         Jump to DOS (shell)
         Alt-P         Printer on/off toggle
         Alt-S         Sound on/off toggle
         Alt-X         Quit Mode
         Alt +=        Debug toggle
         left arrow    Decreases playback speed
         right arrow   Increases playback speed.

        4.1.1 FK 1 Capture to disk Toggle

         This function key turns the capture-to-disk ON if it is off, and
        turns it OFF if it is on.

        4.1.2 FK 2 Type of display Engineering Units/Raw Byte Toggle

         This function key changes the real-time, playback telemetry display
        between raw data and decoded engineering units.

        4.1.3 FK 3 Select display page

         This function key allows you to select a different customized data
        display page.




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        4.1.4 FK 4 Change Doppler frequency display

         This function key allows you to change the Doppler frequency
        display between the computed receive frequency and the difference
        between the satellite beacon frequency and the computed receive
        frequency.

        4.1.5 FK 5 Display MH list

         This function key configures WHATS-UP into the Interactive mode and
        sends a "MH" command to the TNC.

        4.1.6 Alt-B send a 'Break' to the TNC

         This function key allows you to send a "break" character to the
        TNC. You use it if you accidentally put the TNC in the transparent
        mode.

        4.1.7 Alt-C connect to another packet station

         This function key prompts you to enter a callsign, then, if you are
        in the packet communications mode, attempts to connect you to that
        station.

        4.1.8 Alt-D disconnect from another packet station

         This function key allows you to disconnect a packet mode
        connection.

        4.1.9 Alt-F flush receiver buffer

         This function key allows you to flush the receive buffer.

        4.1.10 Alt-I autotrack toggle

         This function key allows you to enable or disable the autotrack
        feature. You use this key to override the default value in the
        spacecraft configuration file.

        4.1.11 Alt-J jump to DOS (shell)

         This function key lets you jump into DOS for a while without
        exiting from WHATS-UP.



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        4.1.12 Alt-P Printer on/off toggle

         This function key lets you turn the printer on and off. If the
        printer is turned on, any incoming raw data will be echoed to the
        printer as well as to the screen.

        4.1.13 Alt-S Sound on/off toggle

         This function key lets you turn the sound on and off.

        4.1.14 Alt-X Quit

         This function key quits the mode and allows you to terminate WHATS-
        UP and return to DOS.

        4.1.15 Alt += debug toggle

         This function key lets you enable and disable the Debug Menu. If
        the debug menu is enabled, an '*' will be displayed on the left hand
        side of the status window.

        4.1.16 left arrow decreases playback speed

         This function key decreases playback speed in the Playback mode.

        4.1.17 right arrow increases playback speed.

         This function key increases playback speed in the Playback mode.

        4.1.18 Up arrow steps parallel port radio memory up

         This function key steps the parallel port radio memory up on
        channel.

        4.1.19 Down arrow steps parallel port radio memory up

         This function key steps the parallel port radio memory up on
        channel.

        4.2 Selections Menu

         This menu presents you with the following typical options.




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          C Change Display Page
          E Edit Menu
          F Files Menu
          H Help Menu
          J Jump to DOS
          L Log Menu
          M Modes Menu
          O Orbits Menu
          R Radio Menu
          S Spacecraft Menu
          T PK232 Menu
          U Utilities Menu
          W CW Menu
          X Exit to DOS
          Z SAREX Menu

        4.2.1 Change Display Page

         This option allows you to change the display page for the Real-
        time, Playback and Extraction Modes. It performs the same operation
        as Function key 3 (F3) when those modes are active.

        4.2.2 Edit Menu

         This option brings up the Edit Menu.

        4.2.3 Files Menu

         This option brings up the Files Menu.

        4.2.4 Help Menu

         This option displays help information for the function keys.

        4.2.5 Jump to DOS

         This option allows you to jump into a DOS Shell. You return to
        WHATS-UP by typing the DOS command 'EXIT'.

        4.2.6 Modes Menu

         This option brings up the Modes Menu.




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        4.2.7 Log Menu

         This option brings up the Log Menu.

        4.2.8 Orbits Menu

         This option brings up the Orbits Menu. This option is only
        available if an orbit element file (*.AMS or *.TLE) is present.

        4.2.9 Radio Menu

         This option brings up the Radio Menu if a Kenwood Radio is present
        and the interface is operational.

        4.2.10 Spacecraft Menu

         This option brings up the Spacecraft Menu.

        4.2.11 TNC or PK232 Menu

         This option brings up the TNC Menu.

        4.2.12 Utilities Menu

         This option brings up the Utilities Menu.

        4.2.13 CW Menu

         This option brings up the CW Menu.

        4.2.14 Exit to DOS

         This option allows you to terminate WHATS-UP and return to DOS.

        4.2.15 SAREX Menu

         This option brings up the SAREX Menu.

        4.3 Modes Menu

         When you bring up the Modes menu you will be prompted with the
        following options.




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         E Extract From Playback File
         I Interactive Mode
         O Orbital Parameters
         M Mutual Visibility
         P Playback Mode
         R Real Time Mode

         Type the letter associated with the option to perform it.

         Each of the options are described below.

        4.3.1 Extract From Playback File

         This option activates the Extraction mode.

        4.3.2 Interactive Mode

         This option activates the Interactive mode.

        4.3.3 Orbital Parameters

         This option activates the Orbital mode. This option is only active
        if Keplerian data files are in the defined directory path.

        4.3.4 Mutual Visibility

         This option activates the Mutual Visibility mode.

        4.3.5 Playback Mode

         This option activates the Playback mode.

        4.3.6 Real Time Mode

         This option activates the Real-time mode.

        4.4 Edit Menu

         WHATS-UP contains an ASCII text editor suitable for files less than
        64k in size. It is built based on Borland's Turbo Pascal Editor
        Toolbox and the commands are compatible with Sidekick and Wordstar.
        A summary of the editor commands is shown below.

         F10           Switch Windows (if more than one window open)


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         Backspace     Delete left char
         Del           Delete Char
         Enter         New line
         Ins           Toggle insert mode
         PgUp          Move cursor up one page
         PgDn          Move cursor down one page

         ^A            Move cursor left one word
         ^C            Move cursor down one page
         ^D            Move cursor right one character
         ^E            Move cursor up one line
         ^F            Move cursor right one word
         ^G            Delete one character
         ^H            Delete left one character
         ^I            Tab
         ^L            Find/replace next occurrence
         ^P            Insert a control character into the text
         ^M            New line
         ^N            Insert line
         ^R            Move cursor up one page
         ^S            Move cursor left one character
         ^T            Delete one word after cursor ^V Toggle insert mode
         ^W            Scroll up
         ^X            Move cursor down one line
         ^Y            Delete line at cursor
         ^Z            Scroll down
         ^K^B          Mark beginning of block
         ^K^C          Copy block to position of cursor
         ^K^D          Save file and exit edit ^K^H Hide block marker
         ^K^K          Mark end of block
         ^K^Q          Abandon file and exit edit
         ^K^R          Read file into screen
         ^K^T          Mark single word as block
         ^K^V          Move block to position of cursor
         ^K^W          Write block to disk file
         ^K^Y          Delete block
         ^K 1..9       Set marker 1 .. 9
         ^Q^A          Find text and replace
         ^Q^B          Move to beginning of block
         ^Q^C          Move to end of file
         ^Q^D          Move to right of line
         ^Q^E          Move to top of window
         ^Q^F          Find text


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         ^Q^I          Toggle autoindent mode
         ^Q^K          Move to end of block
         ^Q^R          Move to top of file
         ^Q^S          Move to left of line
         ^Q^X          Move to bottom of window
         ^Q^Y          Delete to end of line
         ^Q 1..9       Jump to marker 1..9

         The following options can be set in the Find/Find and Replace (^Qf
        and ^Qa) operations.

         #          locates #th occurrence
         G          global replace
         N          replace without Y/N question
         U          ignore upper case/lower case
         W          match whole words only

         Notes
         1 The ^ key in front of a character identifies the character as a
           'control' character. To activate it, hold down the Control key
           AND the character key.
         2 Some of the commands require two keystrokes.
         3 Use ^P to embed a control character in the text. For example, if
           you are creating a file containing commands to be sent to the
           TNC, to enter a control-C character into the file, use the ^P^C
           sequence of keystrokes.

         WHILE USING THE EDITOR, WHATS-UP can't receive and process
        characters from the TNC. All other features ARE INHIBITED OR LOCKED
        OUT.

         The Edit menu allows you to call up the various files for editing
        as shown by this typical display.

          D DOVE.DOP
          F Any File
          K WHATS-UP.TLE
          M c:dove.CNF
          P Pick ***.D17 File
          R c:910313.D17
          S WHATS-UP.SYS
          T Two Files
          W Arrays
          X whats-up.txt


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          Y Pick ***.CNF File
          Z Today's Data

         Type the letter corresponding to your choice.

        4.4.1 Edit Doppler File

         This option lets you edit the file containing Doppler measurements.

        4.4.2 Any File

         This option lets you edit any file.

        4.4.3 Edit Keplerian Element File

         This option lets you edit the default file containing Keplerian
        data.

        4.4.4 Edit Spacecraft Configuration File

         This option lets you edit the file containing the spacecraft
        configuration data, such as display pages, and automatic radio
        tuning options.

        4.4.5 Pick Capture-to-disk File

         This option lets you pick a capture-to-disk file to be edited. When
        you implement this option you will be presented with a list of
        available files. Move the cursor down to the desired file and push
        the 'Enter' key.

        4.4.6 Edit Capture-to-disk File

         This option lets you edit the file containing data captured during
        the last pass.

        4.4.7 Edit WHATS-UP.SYS

         This option lets you edit the WHATS-UP.SYS file.

        4.4.8 Two Files

         This option lets you edit any two files.



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        4.4.9 Edit Doppler Channel File

         This option lets you edit the file containing the channel numbers
        of the data to be extracted from the raw telemetry, processed and
        written to disk.

        4.4.10 Edit Doppler Data File

         This option lets you edit the file containing extracted  data.

        4.4.11 Pick Spacecraft Configuration File

         This option lets you pick a spacecraft configuration file to be
        edited. When you implement this option you will be presented with a
        list of available files. Move the cursor down to the desired file
        and push the 'Enter' key.

        4.4.12 Edit Today's Data

         This option lets you edit a file containing data captured today.
        You will be prompted for the particular spacecraft.

        4.5 Files Menu

         This menu presents you with the following typical options.

          A Change Directory Path
          F Change Playback File
          S Show Data Files
          V View Playback File
          Z Show *.D17 Files
          1 Show Files for 1 Spacecraft

        4.5.1 Change Directory Path

         This option allows you to temporarily change the directory path to
        the capture-to-disk files.

        4.5.2 Change Playback File

         This option allows you to change the playback file. To select a
        file, move the cursor down to the desired file and push the 'Enter'
        key. If you have more files than fit in the window, touch the 'PgDn'
        key to display another window full.


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        4.5.3 View Playback File

         This option allows you to view the contents of the playback file.

        4.5.4 Show Spacecraft Capture-to-disk Files

         This option shows you the names of the capture-to-disk files for
        the chosen spacecraft in the default directory path.

        4.5.5 Show Data Files

         This option shows you the names of ALL the capture-to-disk files in
        the default directory path.

        4.5.6 Show Files for 1 Spacecraft

         This option shows you the names of the capture-to-disk files for a
        particular chosen spacecraft in the default directory path. It will
        prompt you for the filetype associated with the spacecraft (e.g.
        O23, D17).

        4.6 Orbits Menu

         This menu presents you with the following typical options.

         A Pick AMSAT Format Element Set
         E Edit WHATS-UP.TLE
         L Load Element File
         M Set Ref S/C (Mutual Visibility)
         N Pick NASA 2 Line Element Set
         P Show next pass
         S Set Ref = Sun (Mutual Visibility)
         V View Spacecraft Orbit Elements
         Z Show/hide Sun Data

        4.6.1 Pick AMSAT Format Element Set

         This option allows you to change the AMSAT Format Keplerian Element
        file. To select a file, move the cursor down to the desired file and
        push the 'Enter' key. If you have more files than fit in the window,
        touch the 'PgDn' key to display another window full.




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        4.6.2 Edit Default Keplerian Element File

         This option lets you edit the default file containing Keplerian
        data.

        4.6.3 Load Element File

         This option loads the data in the element file into WHATS-UP. When
        you activate the option you will be prompted as follows.

         Which Element File ? WHATS-UP.TLE

         WHATS-UP will supply the default name, you may overwrite it to
        supply the name of another file. You use this option to load a file
        that is not located in the default directory.

        4.6.4 Set Ref S/C (Mutual Visibility)

         This option lets you set the spacecraft for which mutual visibility
        will be calculated (in the mutual visibility mode). The default is
        the Sun. To select a spacecraft, move the cursor down to the desired
        name and push the 'Enter' key. If you have more spacecraft than fit
        in the window, touch the 'PgDn' key to display another window full.

        4.6.5 Pick NASA 2 Line Element Set

         This option allows you to change the 2 Line Format Keplerian
        Element file. To select a file, move the cursor down to the desired
        file and push the 'Enter' key. If you have more files than fit in
        the window, touch the 'PgDn' key to display another window full.

        4.6.6 Show next pass

         This option allows you to view the future passes of a spacecraft.
        When you activate this option, you will be presented with a menu
        window containing a list of spacecraft designators. Move the cursor
        to the one of interest and touch the 'Enter' key to select it.

         An * will be shown next to the MA column, if the spacecraft will be
        in sunlight at the time. A + will be shown if the spacecraft will be
        visible. Touch the space key to view a subsequent pass, touch the
        'Esc' key to return to the spacecraft choice menu.




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        4.6.7 Set Ref = Sun (Mutual Visibility)

         This option lets you reset the Sun as the spacecraft for which
        mutual visibility will be calculated (in the mutual visibility
        mode).

        4.6.8 View Spacecraft Orbit Elements

         This option lets you view the data associated with the spacecraft.
        When you activate this option, you will be presented with a menu
        window containing a list of spacecraft designators. Move the cursor
        to the one of interest and touch the 'Enter' key to select it.

         If the default element file is in AMSAT format (*.AMS) the two line
        display is not shown.

         A typical display is shown below :-

        1 20440U 90  5  E 91059.65616971  .00001077  00000-0  44042-3 0  2017
        2 20440  98.6806 140.0431 0012003 123.1299 237.1040 14.29083383 57498

        Catalog ID:               20440   Apogee:                 803.312
        Element Set:                201   Perigee:                786.093
        Epoch Year:                1991   Period:                  100.76
        Epoch Day:           59.6561697   Semi Major Axis:       7172.862
        Drag:                0.00001070
        Inclination:            98.6806   Epoch Age:               22.263
        RAAN:                  140.0431   Current Date:            81.919
        Eccentricity:         0.0012003   Current Orbit #:           6067
        Argument of Perigee:   123.1299
        Mean Anomaly:          237.1040
        Mean Motion:         14.2908338
        Epoch Orbit #:             5749


        4.6.9 Show/hide Sun Data

         This option allows you to display the position of the Sun in the
        last row of the orbit display window. It will replace any spacecraft
        in that position. The option as an on/off toggle, i.e. push once to
        turn on the display, push again to turn it off.





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        4.7 Radio Menu

         This menu is only present if you have a Kenwood Radio defined as
        your Radio Receiver for the spacecraft or are using the printer
        port. The Radio menu presents you with the following typical
        options.

          D Turn Doppler Tracking ON
          F Set New Frequency
          I Change Doppler Interval
          M Set Radio Modulation
          R Read VFO A Frequency
          S Set Default Frequency
          V Select VFO A/B

        The Radio printer port menu presents you with the following typical
        options.

         C Set Current Radio Memory
         D Step Radio Memory Down
         E Set Radio Memory Scan Delay
         K Set Scan Radio Memory ON
         M Select Radio Memory
         U Step Radio Memory Up

        The following options are valid for a Radio.


        4.7.1 Turn Doppler Tracking ON/OFF

         This option lets you turn the Doppler tracking on and off.

        4.7.2 Set New Frequency

         This option lets you set a new (default) frequency into the radio
        and tune to it.

        4.7.3 Change Doppler Interval

         This option lets you change the time interval (in minutes) between
        successive samples of the radio VFO frequency.





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        4.7.4 Set Radio Modulation

         This option lets you change the modulation mode in the radio.
        Options are FM, USB, LSB and CW.

        4.7.5 Read VFO A Frequency

         This option lets you read back the frequency that VFO A is tuned
        to, and displays it in the status window.

        4.7.6 Set Default Frequency

         This option lets you set the radio back to the default frequency
        and tune to it.

        4.7.7 Select VFO A/B

         This option lets you select between the two VFOs in the radio and
        tune to it.

        4.7.8 Spare - Not used
        4.7.9 Spare - Not used

                                           WARNING
        There is no way for WHATS-UP to read back the memory positions from
        the radio. WHATS-UP consequently assumes synchronization.

        4.7.10 Set Current Radio Memory

         This option lets you set the radio memory number into WHATS-UP to
        synchronize the radio to the software. Set this to the same number
        as the memory channel of the radio.

        4.7.11 Step Radio Memory Down

         This option lets you set the radio memory down one position.

        4.7.12 Set Radio Memory Scan Delay

         This option lets you change the dwell time the radio waits on each
        channel when scanning through WHATS-UP.





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        4.7.13 Set Scan Radio Memory ON/OFF

         This option lets you start and stop scanning through the radio
        memories using WHATS-UP to control the scan. When the scan is turned
        off, you will be prompted to synchronize the channels (in case of a
        slippage). If WHATS-UP is in the scanning mode when a satellite pass
        occurs, WHATS-UP will select the appropriate memory channel and
        remain on that channel until the pass is over. At that time, it will
        resume scanning.

        4.7.14 Select Radio Memory

         This option lets you step to a memory. You will be prompted to for
        the memory number. Once the memory is reached, you will be prompted
        for a new number. Enter 0 to remain at the current position.

        4.7.15 Step Radio Memory Up

         This option lets you set the radio memory up one position.

        4.8 Spacecraft Menu

         This menu presents you with the following options.

          C Show DOVE.CNF
          D Default Spacecraft
          K picK Spacecraft
          M Change Spacecraft
          P Pick Ops. Schedule
          S Show Ops. Schedule

         4.8.1 Show Spacecraft Configuration File

         This option allows you to display the spacecraft configuration file
        default settings.

        4.8.2 Default Spacecraft

         This option allows you to override the default spacecraft. WHATS-UP
        will select this one when the current pass is over.

        4.8.3 picK Spacecraft

         This option allows you to choose another spacecraft from a list. To


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        select one, move the cursor down to the desired one and touch the
        'Enter' key. For example, amongst the default files supplied are
        DOVE.CNF and FUJI.CNF. To select the DOVE or the Fuji-20 spacecraft,
        move the cursor down to the 'DOVE.CNF' or 'Fuji.CNF' line and touch
        the 'Enter' key.

        4.8.4 Change Spacecraft

         This option allows you to choose another spacecraft. To select a
        another one, enter the name of the spacecraft.sys file. For example,
        amongst the default files supplied are DOVE.CNF and FUJI.CNF. To
        select the DOVE or the Fuji-20 spacecraft, type 'DOVE' or 'Fuji'

        4.8.5 Pick Ops. Schedule

         This option allows you to pick an operations schedule. (A file with
        the default extension of "OPS".) You would use it to look at the
        schedule for a spacecraft other than the one currently selected.

        4.8.6 Show Ops. Schedule

         This option allows you to look at the schedule the spacecraft
        currently selected.

        4.9 TNC Menu

         This menu presents you with the following typical options. The
        actual ones will depend on which TNC you have.

          A UoSAT ASCII Beacon
          B Phase 3 RTTY Beacon
          C Set Morse Code (CW)
          M Fuji/MicroSat ASCII Packet
          O Select AO-13 PSK
          P 1200 Baud FM Packet
          R Select MFJ 1278 Radio Port
          S SARA ASCII Beacon
          T Configure PK232
          U 9600 Baud Packet

         If you select an option that your TNC cannot perform, you will get
        an error message.




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        4.9.1 UoSAT ASCII Beacon

         This option will configure the PK-232 to copy the UoSAT-2
        telemetry. Note: you require a hardware change in the PK-232 to make
        sense of the received data (Section 7.2). You should not use WHATS-
        UP to capture AMSAT/UoSAT binary telemetry because WHATS-UP filters
        the ^J and ^M (carriage return and line feed characters) from the
        incoming datastream.

        4.9.2 Phase 3 RTTY Beacon

         This option will configure the Multi mode TNC to copy the UoSAT-
        OSCAR 13 Baudot Beacon.

        4.9.3 Set Morse Code (CW)

         This option will configure the Multi mode TNC to copy morse code.
        You use this if you want to copy morse code telemetry. Note the
        decoding formats are not provided in this program, so you will have
        to decode the telemetry in some other way, such as by hand or by
        means of a spreadsheet.

        4.9.4 Fuji/MicroSat ASCII Packet

         This option will configure the Multi mode TNC to copy the Fuji
        ASCII format PACKET telemetry. You should not use WHATS-UP to
        capture AMSAT/UoSAT binary telemetry because WHATS-UP filters the ^J
        and ^M (carriage return and line feed characters) from the incoming
        datastream.

        4.9.4 Configure TNC

         This option configures the TNC to copy the UI packets transmitted
        by the Packet spacecraft or any other configuration defined by the
        parameters at the end of the *.CNF file.

        4.9.5 FM Packet

         This option will configure the Multi mode TNC to copy the DOVE
        ASCII format PACKET telemetry. You should not use WHATS-UP to
        capture AMSAT/UoSAT binary telemetry because WHATS-UP filters the ^J
        and ^M (carriage return and line feed characters) from the incoming
        datastream.



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        4.9.6 SARA ASCII Beacon

         This option will configure the PK-232 to copy the SARA ASCII format
        300 baud binary telemetry. The option is left in WHATS-UP for
        possible future use.

        4.9.6 Select MFJ-1278 Radio Port (if TNC is an MFJ 1278)

         This option lets you change the MFJ Radio port. WHATS-UP doesn't
        change it at any other time.

        4.9.7 Select AO-13 PSK (if TNC is a DSP-2232)

         This option lets you select 400 baud PSK demodulation.

        4.9.8 Select 9600 Baud Packet (if TNC is a DSP-2232 or PK-900)

         This option lets you select 9600 baud FM packet demodulation.

        4.10 Utilities Menu

         This menu presents you with the following typical options.

          A Change Directory Path
          D Show Space on Disk
          E Enable/Disable RS-232 Port to TNC
          M Turn MET Window ON/OFF
          R Reset Header Counters
          S Show Defaults
          Z Show Files
          * Show Color Chart
          ! Reconfigure WHATS-UP

        4.10.1 Change Directory Path

         This option allows you to temporarily change the directory path to
        the spacecraft capture-to-disk, configuration and schedule files.

        4.10.2 Enable/Disable RS-232 Port

         This option allows you to temporarily enable or disable the serial
        port to the TNC. This feature is for the time you want to use WHATS-
        UP in the Orbit Dynamics mode and another program to access the TNC.



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        4.10.3 Enable/Disable TNC Port

         This option lets you enable and disable the PC serial port to the
        TNC. Use it to stop WHATS-UP taking control of the port in multi-
        tasking environments, so you can run LAN-LINK in one window, and the
        Orbit Dynamics display of WHATS-UP in another.

        4.10.4 Turn MET Window ON/OFF

         This option allows you to temporarily enable or disable the
        (Mission Elapsed Time) MET display. The default MET value for each
        spacecraft is stored in the spacecraft.CNF file. When you activate
        the display you will be prompted to enter the time. Push the 'Enter'
        key to accept the default, overwrite the default with any value in
        the format YYYY:MM:DD:HH:mm:ss. For example, 06:38:00 on March 2,
        1995 is 1995:03:02:06:38:00.

        If you enter a '0' the timer will start from 0.

        Use the MET counter to display the launch time for a SAREX mission,
        or the last memory load time for DO-17 and other microsats.

        4.10.5 Show Space on Disk

         This option allows you to see how much space is left on a disk with
        exiting from the program.

        4.10.6 Reset Header Counters

         This option applies to spacecraft transmitting packetized
        telemetry. When activated, the option resets the packet counters to
        zero. Use this before a pass to see how many packets of each type
        are received during the pass.

        4.10.7 Show Defaults

         This option allows you to display the WHATS-UP default settings.

        4.10.8 Show Files

         This option lets you display the files in the default directory
        path. Use this if WHATS-UP tells you that a file does not exist and
        you are sure that it does.



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        4.10.9 Show Color Chart

         This option allows you to display the color combinations. Use this
        to see what how the different color combinations appear on your
        screen, note the numbers associated with each color, then exit from
        the program and edit the WHATS-UP.SYS file using your editor in its
        ASCII (non document)mode to change the colors to those you desire.

        4.10.10 Reconfigure WHATS-UP

         This option reloads the configurations from the WHATS-UP.SYS file.
        Use it after editing the file to see the effect of your changes.

        4.11 Debug Menu

         This menu is only active when the debug flag is enabled (Alt +=
        key). The menu presents you with the following typical options.

          C Sound CW String
          D Turn Debug OFF
          F Set Frequency
          I Interrogate Radio
          S Show Defaults
          T Command Radio
          V Speak Frequency
          W Identify Radio

        4.11.1 CW Tone Test

         This option asks you to enter some characters at the keyboard. When
        you do so, it then sounds them off in morse code. You use this
        option to adjust the speed of the morse code used in the AOS, LOS
        and EWT warning signals.

        4.11.2 Turn Debug OFF

         This option lets you turn the debug flag off.

        4.11.3 Set Frequency

         This option lets you enter a frequency into the selected VFO.





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        4.11.4 Interrogate Radio

         This option lets you enter a manual command into the radio and see
        the reply returned by the radio.

        4.11.5 Show Defaults

         This option allows you to display the WHATS-UP default settings.

        4.11.6 Command Radio

         This option lets you enter a manual command into the radio.

        4.11.7 Speak Frequency

         This option commands the voice module in the radio to announce the
        frequency on which it is tuned.

        4.11.8 Identify Radio

         This option lets you enter the 'identify' command into the radio
        and see the reply returned by the radio.

        4.12 Log Menu

         WHATS-UP automatic logging Packet mode Connects, and satellite
        Acquisitions. The Log files are in dBASE 3 format and can be
        processed by the LAN-LINK and DBASE Log book Package in PC-HAM for
        indexed listings, tracking of DXCC and other AWARDS, etc. This is
        ideal for special event stations and DX-peditions, for the whole QSL
        process and further statistical analyses of their operation. The
        structure of the logbook files are as shown below.

            Field     Field Name       Type         Length
            1              DATE      Character      8
            2              TIME      Character      4
            3              BAND      Character      3
            4              CALL      Character      10
            5              RX        Character      3
            6              TX        Character      3
            7              MODE      Character      4
            8              POWER     Character      4
            9              QSLSENT   Character      1
            10             QSLRX     Character      1


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            11             COMMENTS  Character      20

         The size of the COMMENTS field is a compromise. Each field is a
        fixed size so that each log entry takes up a minimum of 62
        characters worth of space on the disk even if all the character
        space is unused. You may change the size of the field if you wish,
        but to do that you will have to use dBASE. Note also, that if you do
        make the comments field longer, the display will be screwed up.

         For the logging feature to work, the logbook files must be present
        on the disk. You may create a logbook by accessing the Log menu.

         When you bring up the Logbook you will be shown the last screen or
        page of log entries. The last entry will be highlighted. At this
        time a number of function keys can be used, or you may depress the
        "Escape" key to bring up the Log Help Menu. The following functions
        are available.

          A       Append Entry
          E       Edit Log Entry
          H       Scan for Log Entry
          L       Pack Logbook
          S       Scan for Call
          U       Toggle Delete Mark
          X       eXit Log Menu
         Ins      Toggle Insert Mode
         End      Show Last Page
         Home     Show First Page
         PgUp     Page Up
         PgDn     Page Down
         Up       One Entry
         Down     One Entry

        4.12.1 Alt-A Append Entry

         This function key allows you to manually append an entry to the
        log. You can also use this command to enter the odd SSB contact into
        the logbook file. If you do, use the characters "SSB" or "FM" for
        those voice modes to remain compatible with the rest of the DBASE
        logbook package.

         When appending or editing an entry, LAN-LINK will automatically
        enter the date, time, callsign of the other station, band, mode and
        QSL information in upper case.


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         The comments field in the LAN-LINK logbook file is restricted to a
        maximum of 20 characters. If you try and enter more than 20, the
        surplus will be ignored.

        4.12.2 Alt-E Edit Log Entry

         This function key allows you to edit the highlighted entry. Move
        the cursor with the arrow keys, and end the edit process by
        depressing the "Escape" key. You may use the "QSL" entry to tag the
        fact that you have written out or received a QSL card.

        4.12.3 Alt-H Scan Log by Call

         This function key allows you to scan the logbook by callsign prefix
        for the callsign in the highlighted entry in the logbook. This
        command displays the contents of the logbook file in a formatted
        manner on the screen. It requests the callsign of the log entry to
        be displayed. If you want to see entries for particular callsigns or
        parts of a callsign, enter those callsigns or the front parts of the
        callsign. Valid entries are G, G3, G3Z etc. If you want to see every
        entry in the log, don't use this command, use the Page Up and Page
        Down keys from the Main Log menu.

        4.12.4 Pack Logbook

         This function key allows you to remove the logbook entries flagged
        for deletion.

        4.12.5 Alt-S Scan Log by Call

         This function key allows you to scan the logbook by callsign prefix
        for the callsign entered with the Alt-C or Alt-E keys. This command
        displays the contents of the logbook file in a formatted manner on
        the screen. It requests the callsign of the log entry to be
        displayed. If you want to see entries for particular callsigns or
        parts of a callsign, enter those callsigns or the front parts of the
        callsign. Valid entries are G, G3, G3Z etc. If you want to see every
        entry in the log, don't use this command, use the Page Up and Page
        Down keys from the Main Log menu.

        4.12.6 Alt-U Toggle Delete Mark

         This function key allows you to mark an entry for deletion, or


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        unmark it in case you change your mind. Entries marked for deletion
        will be flagged by an "*" character next to the record number.

        4.12.7 Alt-X eXit Log

         This function key lets you exit from the Logbook.

        4.12.8 Ins Toggle Insert Mode

         This function key allows you to turn the insert mode ON and OFF for
        the edit/append functions.

        4.12.9 End Show Last Page

         This function key moves you to the last callsign on the last page
        of the logbook.

        4.12.10 Home Show First Page

         This function key moves you to the first callsign on the first page
        of the logbook.

        4.12.11 PgUp Move Up One Page

         This function key moves the display up one page of the logbook.

        4.12.12 PgDn Move Down One Page

         This function key moves the display down one page of the logbook.

        4.12.13 Up Arrow Move Up One Entry

         This function key moves the highlight up one entry in the logbook.

        4.12.14 Down Arrow Move Down One Entry

         This function key moves the highlight down one entry in the
        logbook.

        4.13 SAREX Menu

         This menu is designed for use with the Shuttle Amateur Radio
        Experiment (SAREX), MIR, and the packet radio Microsats, or any
        terrestrial station you want to connect with as soon as they appear


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        on frequency.

          A Set Attack Mode ON/OFF
          C Set SAREX Call
          M Attack Mode [QCB]
          R Reset SAREX Flags
          Z Turn Zap R0MIR-1 ON/OFF
          0 Multiple User Connects

        4.13.1 Set Attack Mode ON/OFF

         If the Attack Mode is set, this option will cause WHATS-UP to issue
        a connect request/beacon to the SAREX Call whenever a packet sent to
        or from it is heard. The mode, is cleared when the connect is made
        (and does not retry out) or when the "A" option is selected a second
        time. If this mode is enabled, the Alert/SAREX Call prefix shown in
        the Status Window will indicate accordingly.

         A happy face will be displayed in the status window before the call
        once the connect has been achieved.

          Be careful using this feature, as it has the potential to cause a
        great deal of QRM. It can also be cleared by another station
        connecting to you and telling you to ":QRT:".

         In the SAREX configuration you are listening on one channel while
        transmitting on an other. If this feature is used on a simplex
        channel (everyone transmits and listens on the same channel) aimed
        at a DX-pedition or the MIR space station, there is a potential
        lockout mode, in which any one station sending a connect request to
        the desired/SAREX call will trigger the other ones on frequency who
        will in turn trigger the first. If this pile up situation occurs, I
        hope the DX-station will QSY and leave the automatic stations to do
        their thing. IN any event, if you use this feature and cause QRM,
        anyone can connect to you with the callsign of the DX station (as a
        pirate) and shut you down. You will then not get the coveted DX QSL.

        4.13.2 Change SAREX Call

         This option lets you temporarily change the SAREX call.

        4.13.3 Set Attack Mode Attack Mode [QCB]

         This option allows you to configure the SAREX Attack mode to:


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         Q   digipeat or call CQ via the SAREX station
         C   connect to the SAREX Callsign
         B   both at the same time

         Use the CQ and beacon features to digipeat via MIR while attempting
        a connect, and the connect alone for the Space Shuttle (SAREX). If
        the Attack Mode is set, WHATS-UP will either try for a connect or
        send an unproto packet containing the CQ text. If you want it to go
        through the SAREX Callsign you must configure the UNPROTO parameter
        in the TNC. For example, to attempt a digipeat via R2MIR, set
        'UNPROTO CQ via R2MIR' from the command mode.

        4.13.4 Reset SAREX Flags

         This option lets you reset the SAREX Connect Status indicators in
        the status window.

        4.13.5 Turn Zap R0MIR-1 ON/OFF

         This option turns the Zap feature ON and OFF.

        4.13.6 Single/Multiple User Connects

         This option configures the TNC for single or multiple users. Use
        single when trying for a SAREX QSO and Multiple when beaconing
        through MIR.

        4.14 CW Menu

        This menu provides you with a smart CW transmit terminal. The
        keyboard will transmit letter, numbers and the following special
        characters:

                   Keystroke Abbreviation   Meaning

                   *         SK        End of QSO
                   &         AS        Wait
                   +         AR        End of Message
                   (         KN        Go ahead designated station
                   =         BT        Break or pause
                   >         AA        New line
                   !         SN        Understand
                   %         KA        Attention


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        The following punctuation characters are supported

                   ?   IMI       .   AAA        ,   MIM        -   DU
                   :   OS        ;   KR         )   KK         /   DN
                   "   AF        $   SX         '   WG         _   IQ

        The CW menu presents you with the following typical options.

         A Sound Text
         D Set CW Speed
         K Turn CW keyboard ON
         N Set CW Note
         S Show CW Memories
         T Transmit Text
         - Slow CW Down
         + Speed CW Up
         1..0 Change CW Memory 1..10

         WHATS-UP uses timing loops in software to produce the sounds and
        key the transmitter. If you have time accessed multi-task switching
        on your system, the sounds/key times will be wrong.

        The menu options are as follows:

        4.14.1 Sound Text

         This option asks you to enter a line of text, then sounds it in
        morse code. Use this option to test the audio note and speed.

        4.14.2 Set CW Speed

         This option allows you to change the default morse speed. The
        higher the number you enter, the lower the speed. The number you
        enter is the delay time of a single bit ("dot" or "space between
        dots") in milliseconds.

        4.14.3 Turn CW keyboard ON/OFF

         This option allows you to turn the morse keyboard on and off. When
                  the CW keyboard is active:
                  the greek letter 'µ' will be seen flashing in the Status
                  window.
                  any letter or number typed at the keyboard will be output


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                  to the parallel port keyer bit as well as to the TNC port.

        4.14.4 Set CW Note

         This option lets you set the audio cw tone used in the computer.

        4.14.5 Show CW Memories

         This option displays the contents of the CW memories as loaded from
        the WHATS-UP.SYS file, or temporarily overridden by the "change
        memory contents" option described in Section 4.14.9.

        4.14.6 Transmit Text

         This option asks you to enter a line of text, then transmits it in
        morse code.

        4.14.7 Slow CW Down

         This option slows the CW rate by 5 milliseconds, each time it is
        activated.

        4.14.8 Speed CW Up

         This option speeds the CW rate by 5 milliseconds, each time it is
        activated.

        4.14.9 Change CW Memory 1..10

         When you enter a number between 1 and 9, or 0, this option asks you
        to enter a line of text, and stores it in the CW memory associated
        with the number. 0 is Memory number 10. The change is temporary and
        will be lost when you terminate the program. For permanent changes,
        edit the change into the appropriate line in the WHATS-UP.SYS file.












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        5.0 Orbital Elements

        5.1 Basics

         As an object moves in space it is subject to gravity. The object
        itself has mass and attracts other objects and is at the same time
        attracted by the mass in the other objects. Sir Isaac Newton
        formulated the law of gravity, which can be described in the
        following manner.

         All bodies attract each other with a force called gravitational
        attraction. The strength of the mutual attraction between two bodies
        is dependent on their masses, and the distance between the bodies.
        In fact the closer together that the two bodies are, the greater is
        the mutual attraction. Mathematically this can be expressed as the
        gravitational attraction between two bodies is directly proportional
        to their masses and is inversely proportional to the square of the
        distance between them.

         Planet Earth is an object moving in space and exerts a
        gravitational force. It pulls anything close to it towards the
        center of the Earth at an increasing speed. An increasing speed is
        known as acceleration. The acceleration due to gravity at the
        surface of the Earth is given the value of 1 Gravity (G).

        5.2 Orbital Trajectories

         If the Planet pulls everything towards itself, what keeps things in
        orbit around it? For example, if you throw a rock up into the air,
        gravity and air resistance (drag) slow it down and it falls back to
        Earth. If you shoot a bullet towards the horizon it will travel much
        further than the stone did, but will still fall to Earth (unless it
        hits something first).

         If you launch a rocket towards the horizon, the rocket will
        accelerate as long as the fuel lasts. When the rocket fuel is
        exhausted, the rocket will continue to travel in a straight line
        until other forces alter its path. If the rocket is low enough, the
        molecules of air or the atmospheric drag tends to slow it down. At
        any height it will still be pulled back by gravity. The force of
        gravity always acts towards the center of the Earth. On its own the
        rocket will travel in a straight line. Gravity acting downwards will
        curve the path of the rocket around the Earth.



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         The force of gravity will pull the rocket away from its horizontal
        path and cause it to fall in a downwards direction. Now the surface
        of the Earth is also curved and also curves away in a downwards
        direction. If speed of the rocket is such that the rate of descent
        (due to the gravitational attraction of the Earth) is equal to the
        curvature of the Earth, the rocket will always remain at the same
        height , namely, it will be in a circular orbit. If the rocket does
        not have enough speed it will gradually fall back to Earth, and if
        it has more speed, it will tend to rise above the Earth.

         If the rocket continues to burn fuel the speed of the rocket
        increases and the path it takes rises away from the surface of the
        Earth. When the fuel is exhausted, gravity is still there and still
        slows down the rocket. As it slows down its path curves more sharply
        until at its furthest point (apogee) it is traveling parallel to the
        surface of the Earth. It is however traveling slower than the speed
        necessary to maintain a circular orbit at that altitude and starts
        to curve back towards the Earth. The force of gravity now acts in a
        downward and (slightly) forward direction and speeds up the rocket
        until at its lowest point (perigee) it once again is traveling
        parallel to the surface of the Earth but now has enough speed to
        rise away the surface. This process repeats each time around and
        produces an elliptical orbit.(In this orbit, the center of the Earth
        is one focus of the ellipse.

         To place a satellite into an orbit, it must be given the right
        amount of speed for the desired orbital altitude so that the orbital
        velocity at apogee is such that it just balances the gravitational
        pull of the Earth. Since the force of gravity decreases with
        altitude, the orbital velocity is also different at different
        altitudes. Any rocket can lift a small mass to a much higher
        altitude than it can lift a large mass. How much and how high will
        depend on the rocket itself.

        5.3 Types of orbits

         Different orbits are used for different purposes. Circular and
        elliptical orbits come in various forms depending on the angle that
        the plane of the orbit makes with the equator of the Earth. This
        angle is known as the angle of inclination of the orbit (with
        respect to the equator). A polar orbit has an angle of inclination
        such that the spacecraft in that orbit can see the polar regions of
        the Earth. A geostationary orbit is one which has an angle of
        inclination parallel to the equator and an altitude of 22,240 miles


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        (35,790 km) and the spacecraft moves in its orbit at the same speed
        as a point on the surface of the Earth below it. The spacecraft thus
        appears to be stationary with respect to the Earth below it.

         The direction in which the satellite moves around the Earth
        determines the type of orbit. One which travels along its orbit in
        the same direction as the rotation of the Earth (eastwards) is said
        to be in a direct or prograde orbit. One which travels against the
        rotation of the Earth (westwards) is said to be in a retrograde
        orbit.

         The movement of an object in space can be described mathematically.
        In the early 17th century, the only known objects in space were the
        Sun, the Moon, the Planets, a few comets and the stars. It was then
        that Johannes Kepler formulated three laws that first described the
        movement of the Planets about the Sun.

        5.3.1 Kepler's Laws

         Kepler's Laws are stated in the following paragraphs.

         1. Each Planet revolves about the Sun in an orbit that forms a
            circumference of an ellipse with the Sun at one focus of the
            ellipse.
         2. The line from the center of the Sun to the center of the Planet
            (called the radius vector) sweeps out equal areas in equal
            periods of time as the Planet travels along the circumference of
            the ellipse.
         3. The square of the time taken for a Planet to travel around the
            circumference of the ellipse (period of revolution of the orbit
            of a Planet) is proportional to the cube of the mean distance of
            the Planet from the Sun.

         In the first law, the focus within the Sun is actually at the
        center of mass of the Earth-Sun system and not at the center of the
        Sun.

         5.4 Orbital Elements

         The position of an object in space can be expressed in terms of its
        relationship with other bodies. Each orbit can be described in terms
        of a number of parameters which supply enough information to
        accurately locate the satellite. Six basic parameters are used to
        describe the position of a satellite in an elliptical orbit are


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        described in the following paragraphs. They are Angle of
        inclination, Right Ascension of Ascending Node (RAAN), Eccentricity,
        Semimajor Axis, Argument of Perigee and Epoch time of Ascending
        Node.

        Consider each one in turn.

         5.4.1 Angle of Inclination

         The angle of inclination of an orbit is the angle between the plane
        of the orbit and the equator of the Earth. A satellite moving in a
        direct orbit has an angle of inclination between 0 and 90 degrees,
        one moving in a retrograde orbit has an angle of inclination of
        between 90 and 180 degrees.

         The maximum northern and southern latitudes reached by a satellite
        are equal to the angle of inclination of its orbit.

        5.4.2 Right Ascension of Ascending Node (RAAN)

         While the spacecraft is moving around the Earth, the Earth is at
        the same time rotating on its own axis, and is itself traveling in
        an orbit about the Sun. The Right Ascension of Node is needed as a
        fixed reference point in the sky.

         Astronomers use the term celestial sphere to describe the sky for
        two reasons. First, from where we are standing on the surface of the
        Earth, the sky seems to be painted on the inside surface of a sphere
        (with the stars in fixed positions on the sphere). Second, have you
        ever known scientists to use a short commonly used word when they
        can use long ones?

         The orbital plane of a spacecraft intersects the equatorial plane
        of the Earth in two places (one on each side of the globe). A line
        drawn between these two points and continued out to the celestial
        sphere is called the line of nodes. The two points on the line of
        nodes where the planes intersect are called the point of nodes. Most
        globes (and maps) show the north pole upwards. When the spacecraft
        crosses the equatorial plane (passes above the equator) going
        northward it is ascending from south to north and that node point is
        known as the ascending node. Conversely when the satellite continues
        on its way and travels half way around the world it crosses the
        other node on the equatorial plane descending to the southern
        hemisphere. This second node is called the descending node.


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         The Earth is in an inclined orbit around the Sun, just like a
        satellite is in orbit around the Earth. The Earth has an ascending
        and descending node around the Sun, in a similar manner to a
        spacecraft in orbit around the Earth. The orbital plane of the Earth
        is known as the Ecliptic. The direction in space from the center of
        the Earth through the intersection of the ecliptic and the Earth's
        equatorial plane out to the celestial sphere is called the vernal
        equinox or the First Point of Aries because it points to the
        constellation of Aries (which is so far away that (for all practical
        purposes) it is in fixed direction).

         The angle between the line of nodes for the ascending node of the
        orbit of the spacecraft continued out to the celestial sphere and
        the vernal equinox when measured in an easterly (right as opposed to
        westerly/left) direction along the earth's equator is defined as the
        Right Ascension of the Ascending Node (RAAN).

        5.4.3 Eccentricity and Semimajor Axis

         In a circle, the radius of the circumference is constant. This
        means that an object traveling along the circumference is always at
        a constant distance from the center or focus of the circle. The
        general shape of an orbit is an ellipse. Unlike a circle, an ellipse
        has two focal points. The distance between each of the focal points
        of the ellipse and an object on the circumference is constant. A
        line through the two focal points and the circumference is called
        the Semimajor Axis. The longest line perpendicular (at 90 degrees
        to) the semimajor axis passing through the circumference of the
        ellipse is called the Semiminor Axis.

         The mathematical term describing the overall shape of an ellipse is
        called Eccentricity. When the eccentricity of an ellipse is 0 the
        length of the semimajor axis is equal to the length of the semiminor
        axis and the shape being described is a circle. A value of
        eccentricity greater than 0 means that there is a difference between
        the lengths of the axes and the shape of the ellipse flattens out.
        Eccentricity describes the shape of the orbit and the length of the
        semimajor axis describes the size of the orbit. If these two
        parameters are known, the apogee and perigee values for the orbit
        can be calculated.





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        5.4.4 Decay Rate

         The Earth has an atmosphere. It is dense at ground level and thins
        out with increasing altitude. The Earth's gravity attracts the
        molecules of gas in the atmosphere and stops them from escaping. As
        the satellite travels along its elliptical orbit around the Earth,
        its altitude changes. When it is close to perigee, it bumps into
        molecules of air. The lower it gets the greater the drag on it by
        the air. When the orbital radius decreases as a result of drag, the
        potential energy of the spacecraft also decreases as it comes closer
        to the earth. This decrease in potential energy reappears in the
        form of heat energy imparted to the atmosphere and to the skin of
        the spacecraft, and in an increase of the kinetic energy of the
        spacecraft. It is this latter that causes the velocity of the
        spacecraft to speed up.

         The rate of change of speed through the atmosphere at the perigee
        pass will depend on the type of orbit and on the altitude of the
        perigee point. In general, satellites with low perigee points will
        be more affected than satellites with higher perigee points. The
        effect of this over the long term is to lower the apogee point. Over
        the long term, the satellite tends to spend more time in the denser
        parts of the atmosphere which then tends to circularize the orbit
        (at the perigee) at which point the air drag acts continuously on
        the spacecraft and the orbit disintegrates. The rate of change of
        the orbit measured at a particular epoch is called the decay rate.

        5.4.5 Argument of Perigee

         A line drawn between the perigee of an elliptical orbit and the
        center of the Earth is called the line of perigee. This line also
        passes through the apogee and is the semimajor axis of the orbit.
        The angle between the line of perigee and the line of nodes is
        called the argument of perigee. It is a measurement of the angular
        distance between them and is measured in the ascending direction
        from the line of nodes. The argument of perigee thus establishes the
        position of the ellipse itself within the orbital plane.

        5.4.6 Epoch Time (of Ascending Node) and Revolution Number

         The Epoch time is a time when the satellite crosses its perigee
        point. This time is given as a Julian date, and is the reference
        time for when the orbital elements are valid. The Epoch Revolution
        or orbit number is the orbit number (since first perigee crossing)


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        for which the element set is valid.

        5.4.7 The Mean Motion

         The mean motion a satellite is a measurement of the number of
        orbits completed in a day. It is equal to twice the value of PI
        divided by the time that the spacecraft takes to complete one
        revolution of its orbit (orbital period).

        5.4.8 The Catalog Number

         The catalog number is the number given to the object.

        5.4.9 Mean Anomaly

         As the satellite travels along its orbit, its position changes. The
        angle (measured in the direction of forward rotation) between the
        position of the spacecraft and the line of perigee is called the
        true anomaly. The speed of the spacecraft is different at different
        parts of the orbit. Calculations are simpler if the speed is
        considered to be constant. The constant value is the average speed
        of the spacecraft in its orbit. The mean anomaly is the hypothetical
        position of the satellite in its orbit (along the ellipse) if it is
        assumed to be traveling at its average speed.

        5.5 Anticipated Spacecraft Lifetimes

         There is not much point in setting up equipment to receive data
        from these spacecraft if they are not going to be around for a
        reasonable amount of time. Past experience points to three main
        factors limiting the operational life of an OSCAR, namely orbital
        decay, battery life, and total radiation dosage.

        5.5.1 Orbital Decay

         The last OSCAR to plunge back into the earth's atmosphere while
        still active was UO-1. It was launched into a 500km orbit, and
        lasted eight years. A chart in the Satellite Experimenter's Handbook
        shows a lifetime of 40000-50000 days for spacecraft at the Microsat
        altitude, or somewhere around 120 years; so orbital decay is not our
        main worry. There has been some concern about AO-13's orbit, which
        is expected to decay somewhere between 1994 and 1996. AMSAT however
        are currently building Phase 3D as a replacement spacecraft so the
        investment in receiving equipment will not be in vain.


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        5.5.2 Battery lifetime

         Battery breakdown has caused the demise of all amateur spacecraft
        except UO-1. OSCARs 1, 2 and 3 were limited to whatever charge was
        in the batteries when launched. Once Solar cells and nickel-cadmium
        batteries were flown, the limiting factor became the number of times
        the battery cells could be charged and discharged.

         The batteries in OSCAR spacecraft in low earth orbit have lasted
        between five and eight years. UO-1 was still looking good when it
        re-entered the earth's atmosphere after 8 years. UO-2, launched in
        March, 1984, has batteries with the same part number as those used
        in the Microsats. These latter batteries were procured in much the
        same manner, and were matched and tested by the same group of VITA
        volunteers in Canada that performed the function for UO-2. The
        batteries on UO-2 have shown no signs of weakening after almost six
        years in orbit, so the prognosis for UO-2 and the Microsats looks
        good.

        5.5.3 Radiation Damage

         Anything above the protection of the atmosphere is subjected to
        exposure to the radiation due to the direct and secondary effects of
        high energy particles, from the sun and elsewhere. The part of the
        spacecraft most susceptible to such damage is the memory in the on-
        board-computer (OBC). Such damage manifests itself as a bit flipping
        from a 0 to a 1 or from a 1 to a 0, which is correctable. Since the
        memory chips used are byte-wide, many types of single-chip failures
        can be avoided in a manner analogous to locking out bad sectors on a
        hard disk. UO-2, which uses somewhat similar technology chips, has
        survived almost six years despite a failure of one small section of
        memory several years ago.

         Another part of the OBC is the controller itself which is
        susceptible to a particle hitting it in a place that causes
        uncorrectable errors, such as a wrong operation internal to the
        microprocessor, or a CMOS latchup which can result in a high current
        being drawn which overheats the part and destroys it.

         The spacecraft are more likely to fail due to the cumulative
        effects of this constant bombardment, which is known as total dose.
        Once the total dose reaches a certain point, the gates in the
        transistors that make up the computer and its memories will no


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        longer switch. This situation has occurred in AO-10. Predicting when
        this might occur is difficult because of lack of knowledge
        concerning two things; the total radiation dose in this orbit and
        the tolerance limits for the parts used.

         The MicroSats are in a much more benign orbit than AO-10 which with
        its 4000 km perigee, spends more time in the Van Allen radiation
        belts than was planned. AO-10's memories therefore failed sooner
        than hoped, but the other electronics, the transponders, batteries,
        and solar arrays live on. Through no-longer actively attitude
        controlled, its transponders are still usable many weeks of the year
        when its batteries are being charged by the sun.

         AO-13 is in a better orbit with a lower perigee, and should not
        suffer radiation degradation before other effects shorted its
        lifespan.






























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        6.0 The Spacecraft

         OSCAR spacecraft downlink signals in the amateur 145 MHz and 430
        MHz bands modulated by means of Frequency Shift Keying (FSK),
        Frequency Modulation (FM) or Phase Shift Keying (PSK). Some of the
        characteristics of the downlinks of suitable OSCARs currently
        operational are shown in Table 6-1. UO-2 and AO-13 send back BAUDOT
        or ASCII data while AO-16, DO-17, WO-18, LU-19 and FO-20 downlink
        packetized telemetry.

         Table 6-1 Some of the Characteristics of OSCAR Downlinks.
         Spacecraft  Beacon     Modulation      Data    Note
                     Frequency  Type            Rate
                       (MHz)
         UO-2        145.825     FM    ASCII  1200 Baud   1
                     435.025     FM    ASCII  1200 Baud   1
         AO-13       145.812    FSK    BAUDOT   50 Baud   2
                                PSK    ASCII   400 Baud   2
                     435.651    FSK    BAUDOT   50 Baud   2
                                PSK    ASCII   400 Baud   2
         AO-16       437.025    PSK    AX.25  1200 Baud   3
                     437.025    PSK    AX.25  1200 Baud   3
         DO-17       145.825    FM     ASCII  1200 Baud
         WO-18       437.100    PSK    AX.25  1200 Baud   3
                     437.075    PSK    AX.25  1200 Baud   3
         LO-19       437.150    PSK    AX.25  1200 Baud   3
                     437.125    PSK    AX.25  1200 Baud   3
         FO-20       435.912    PSK    AX.25  1200 Baud
         AO-21       145.987    FM     AX.25  1200 Baud   5,6
         SO-23       145.955    FM     ASCII   300 Baud   4,6

         Notes
         1. Spacecraft also broadcasts bulletins and Various Telemetry
            formats.
         2. Spacecraft downlink modulation is changed according to a pre-
            published schedule.
         3. Alternate (back up) beacon frequency, may be used on Wednesdays.
         4. Binary telemetry with ASCII identification.
         5. Spacecraft also transponds FM signals uplinked on 435.016 MHz
            and broadcasts voice bulletins from time to time.
         6. Spacecraft no longer active.

         Before discussing the equipment needed to receive signals from the
        spacecraft, a brief word about the spacecraft themselves is in


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        order. Since these OSCARs rode into space as secondary payloads, the
        orbits that they are in are close to those of the primary payload
        and are not optimized for amateur radio communications. The
        exception is AO-13 which contained a motor which was used by radio
        amateurs to boost the spacecraft from the orbit the rocket placed it
        in into its operational orbit. The ones that are in low earth orbits
        can be received with simple equipment, but are in range for short
        periods of time, AO-13 in an elliptical orbit is in range for many
        hours each day, but needs more sophisticated receiving equipment.
        The orbital parameters of the OSCARs under discussion are shown in
        Table 6-2.

             Table 6-21 Orbital Parameters of the OSCARs
        Spacecraft       Apogee   Perigee Inclination  Period
                          (km)     (km)    (Degrees)   (Minutes)
        UoSAT-2            699     670     98.0          98.3
        AMSAT-OSCAR 13  39,000   2,500     26.1         686.65  [1]
        AMSAT-OSCAR 16     804     780     98.7         100.8
        DOVE-OSCAR 17      804     780     98.7         100.8
        WEBER-OSCAR 18     804     780     98.7         100.8
        LUSAT-OSCAR 19     804     780     98.7         100.8
        FUJI-OSCAR 20    1,745     912     99.05        112.0
        AMSAT-OSCAR 21   1,010     956     82.9         104.7
        SARA-OSCAR 23      774     768     98.5         100.3

         Notes
         1 686.65 minutes is 11 hrs, 26 min.

        6.1 Receiving system components

         Consider the different components or building blocks that are used
        in the different receiving configurations.

        6.1.1 Antennas

         Antennas receive signals, and each kind of antenna has some degree
        of directive and polarization. When the spacecraft rises above the
        local horizon, the ground station experiences acquisition of signals
        (AOS). At this time the groundstation is receiving signals coming
        from a particular direction (azimuth). As the spacecraft rises in
        the sky, the elevation angle of the received signals changes, until
        the spacecraft drops below the observer's horizon and the ground
        station experiences loss of signals (LOS). As seen from the ground,
        the spacecraft rises from a horizon in one direction, travels in an


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        arc across the sky and sets at a different horizon in a different
        direction. Each pass for each spacecraft is different. Antennas for
        receiving signals from spacecraft must thus be able to receive
        signals coming in from almost any angle.

         Antennas in this context, fall into two categories, omnidirectional
        and rotatable. The simple turnstile antenna is horizontally
        polarized and has a good response to signals arriving from high
        angles and can be built for about $2.00. The ground plane and J Pole
        antennas are vertically polarized and have a good response to
        signals arriving from low angles. These antennas however do not have
        much gain. Yagi Beam Antennas however have gain with respect to the
        turnstile or ground plane, but only in specific directions. You can
        think of the gain in some directions as being moved into the
        direction that the antenna is pointed at. The gain of the antenna
        depends on the number of elements in the antenna, and the higher the
        gain, the narrower the area of the gain (lobe) is. Consequently,
        these beam antennas must be moved to keep the spacecraft in the main
        lobe of the antenna. Since the need for keeping the antenna pointed
        at the spacecraft depends on the beam width of the antenna, the
        lower the gain of the antenna the less accurate the tracking need
        be. Luckily the orbits help out in this respect. UO-2 in low earth
        orbit, which means it is fast moving, needs only a small amount of
        gain, so TV style rotators can be employed to point antennas with
        between 2 and 4 elements, while AMSAT-OSCAR 13 which is in an
        elliptical orbit, moves so slowly for nearly 8 of its 11 hour orbit,
        that again, TV style rotators can be used to point higher gain
        antennas with between 8 and 11 elements.

         Building your own antennas is an easy and worthwhile project.
        Antennas for these OSCARS are simple and not very critical with
        respect to the materials used. They can in fact be built from
        recycled junk.

        6.1.2 Receivers

         There are two kinds of Receivers, namely FM and linear. FM
        receivers are used for reception of the FM signals from DOVE and UO-
        2, while linear receivers are needed for reception of the FSK and
        PSK signals from the other spacecraft. All vhf/uhf scanner radios
        are FM receivers. The linear receivers need single side band (SSB)
        capability, something normally found in short wave communication
        receivers. As a result of the growing popularity of amateur
        satellite communications, suitable vhf/uhf transmitter-receivers


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        (transceivers) have been on the market for several years, however
        these transceivers are expensive listing in the $800 to $1200 range.
        An alternative approach to reception is to use a short wave
        communications receiver listing around $500 together with a front
        end downconverter which lists at under $100. The short wave radio
        can also be used to tune in, not only the world of amateur radio,
        but news broadcasts from overseas; a totally different are of
        classroom activity.

         "Expensive" is a relative term. These days, many people think
        nothing of spending $1000 on a stereo system or on equipment for
        photography or other hobbies.

        6.1.3 Terminal Units and Modems

         Digital radio links work much in the same way as digital signals
        are transferred over the telephone line. However in this case,
        instead of a phone wire, a radio link is used. Both links use modems
        to convert the serial input/output digital RS-232 signals of the
        computer to the audio tones used on the communications link.

         Packet radio signals are demodulated by a radio modem known as a
        Terminal Node Controller (TNC). The device is connected in between
        the radio and the computer and provides hams with two way digital
        communications. A packet only TNC lists for between $120 and $200.
        For reception of the PSK signals from AO-16, WO-18, LO-19 and FO-20,
        PSK Modems are available either as add-ons to a regular TNC or as
        stand alone units, listing between $150 and $700.

         The BAUDOT Radio Teletypewriter (RTTY) signals from AO-13 can be
        demodulated by an RTTY Terminal Unit. These devices are listed at
        between $100 and $300. On the other hand a multi-mode communications
        controller listing between $250 and $700 can be used for AO-13 as
        well as DOVE and the other spacecraft. AO-13 downlinks BAUDOT
        because that is the most commonly used digital communications mode
        used by radio amateurs at high frequencies (short waves)

         The modem for UO-2 is a little more difficult, as its ASCII
        encoding is the reverse of the standard used in the U.S.A. This is
        because the spacecraft was built in the UK and its use of tones to
        represent data reflects the encoding used in a popular tape
        interface (in the UK) at the time the spacecraft was built (1982-
        1984).



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         Still a do-it-yourself circuit needs a few integrated circuits, is
        simple to build, easy to test, and very low cost (under $50).
        Summarizing the costs of the items mentioned above, the list prices
        fall between a low and high cost depending on the amount you wish to
        pay. The summary is shown in Table 6-3. It should be noted that the
        high price items may not be better than the cheaper ones,
        particularly in the educational environment. This table is of course
        only a guide, since you will probably end up with something in
        between.

              Table 6-3 Range of Equipment List Prices
        Item                     Low Price       High Price

        Antenna                       $2.00        $100.00
        Receiver                    $100.00       $1200.00
        Radio Modem (TU/TNC)        $150.00        $700.00
        Tracking Software            $25.00        $350.00
        Telemetry Decoding Software  $35.00         $35.00
        ---------------------------------------------------
        TOTAL                       $312.00       $2385.00

         Consider the equipment needed to receive signals from each of the
        spacecraft in turn.

        6.2 Receiving Signals from DOVE

         DOVE (DO-17) which transmits on a frequency 145.825 MHz and AO-21
        which transmits on a frequency of 145.987 MHz are the easiest
        spacecraft to receive usable signals from. The frequencies are is
        available on most hand held scanners, and signals are strong enough
        to be heard on nothing more than the simple antenna provided with
        the scanning radio when it is purchased. However, the thrill of
        receiving satellite signals wears off very quickly without any means
        to know what those signals mean.

         A somewhat better system is needed for reliable regular reception
        of usable signals. A basic receiving system for DOVE/AO-21 is shown
        in Figure 6.1. Signals are strong enough that the ground station
        does not need a tracking antenna; an omnidirectional antenna is
        sufficient. The antenna can be a ground plane, a turnstile or a J-
        pole design. A preamplifier should be used to compensate for any
        losses in the cable between the antenna and the receiver, or any
        fades in the strength of the received signals. Any scanning radio
        which receives narrow band FM can be used as the receiver. This is


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        the same type of modulation used on the public service channels. If
        the scanner can hear the police and other services and can tune to
        145.825 MHz, then it is capable of receiving signals from DOVE. The
        digital signals from DOVE are encoded as audio tones and need a
        modem to convert them to the RS-232 digital signals that can be
        interfaced to the serial port of a PC. This type of modem is known
        in Radio Amateur circles as a Terminal Unit (TU).

         Figure 6.1 Basic Receiving System for DO-17/AO-21

           OMNIDIRECTIONAL
           ANTENNA
             |
             |
            \|/
         SCANNER
         RECEIVER ---------> TNC ---------> COMPUTER

         The signals are sent as packets using a modified version of the
        X.25 protocol called AX.25. Radio Amateurs use this protocol for
        communications, and DOVE employs it for telemetry transmission
        purposes so that any Radio Amateur equipped for packet radio
        communications is also equipped for receiving signals from DOVE.

        6.3 Receiving Signals from UO-2

         The same basic radio receiving system used to receive signals from
        DOVE can be used to copy the telemetry from UO-2. This spacecraft
        however has a lower powered transmitter than that of DOVE and
        consequently has a weaker signal strength on the ground. This lower
        signal level, coupled with the fact that the modulation is plain
        ASCII data means that errors will be seen in the received data due
        to signal fades. Better antennas are needed for reliable reception,
        and antennas that track or move and always point at the spacecraft
        are desirable.

         The TU used for UO-2 is different to that used for DOVE due to the
        different data encoding (ASCII instead of AX.25).

        6.4 Receiving Signals from AO-13

         So far all the spacecraft considered have been low earth orbits.
        AO-13 however is in an elliptical orbit with a high apogee. It also
        downlinks telemetry as BAUDOT and ASCII data. While signals from


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        this spacecraft can be heard on the simple DOVE type of receiving
        configuration with an omnidirectional receiving antenna, the signals
        are weak and barely audible, i.e. they are in the noise and cannot
        be received in usable form without a tracking antenna.

        6.5 Receiving PSK Modulated Signals in the 70 cm Band

         Receiving signals from AO-16, WO-18 and LU-19 as well as from FO-
        requires somewhat more complex equipment. These spacecraft transmit
        on downlink frequencies in the 70 cm or 430 MHz band. As they use
        PSK, the receiver has to be a conventional communications receiver.
        This can be either a communications receiver designed for that
        frequency range, or a conventional short wave receiver with a front
        end down converter. A PSK modem attached to the TU is also required.
        Typical receiving configurations for these satellites are shown in
        Figures 6-2 and 6-3.

         Figure 6-2 Basic Receiving System for PSK Modulation.

         OMNIDIRECTIONAL
         ANTENNA
           |
           |
           |
           \|/             PSK MODEM
         VHF/UHF             | |
         COMMUNICATIONS      | |
          RECEIVER --------> TNC ----> COMPUTER

         The difference between the two approaches is that the first uses a
        communications receiver designed for the 70 cm band; the second
        approach uses a general short wave receiver and a front end down
        converter.













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         Figure 6-3 Alternate Basic Receiving System for PSK Modulation.

         OMNIDIRECTIONAL
            ANTENNA
               |
               |
         DOWNCONVERTER
               |
               |
           SHORT WAVE                 PSK MODEM
         COMMUNICATIONS                  | |
            RECEIVER                     | |
               |                         | |
               |-----------------------> TNC --------------> COMPUTER
































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        7.0 Decoding Spacecraft Telemetry

         Apart from UO-2, WO-18 and SO-23, none of the OSCAR spacecraft are
        designed for "Science" purposes. Their telemetry consists of
        spacecraft housekeeping parameters, monitoring on-board
        temperatures, voltages and currents. While much use can be made of
        these data, there isn't much real science data available. Even the
        scientific spacecraft are in the main unusable by the average
        listener because information about the scientific payload is not
        readily available. Let's make a start with these spacecraft, then
        look to a follow on activity. An OSCAR does not have to be a
        separate spacecraft. The Soviet Union has provided their amateurs
        with payload space aboard two of their weather satellites [8]. NASA
        could do the same for an amateur scientific spacecraft which would
        monitor radiation, the earth's magnetic field and solar activity;
        such data being of use to radio amateurs for predicting propagation
        and providing schools with data about the earth's environment. NASA
        has a 'Mission to Planet Earth' project to provide an Earth
        Observation Platform in 1997. An attached secondary payload to that
        platform, transmitting packetized scientific telemetry data (with
        well publicized formats) in the 145 MHz amateur band or in the 136
        MHz scientific band could really bring not only the space program,
        but the educational and scientific use of space, into every
        educational institution in the country. In the mean time, this
        section discusses the usable OSCAR spacecraft and their telemetry
        and the corresponding decoding equations.

         The satellites have been built by different organizations at
        different times and each uses different data formats. SARA used a
        300 baud ASCII format. DOVE and FO-20 transmit in an ASCII Packet
        format, yet while DOVE transmits the data in Hexadecimal format, FO-
        20 uses Decimal Format. AO-16, WO-18 and LO-19 transmit their
        telemetry in pure binary format. By using packetization, the data
        quality is checked in the link itself and bad packets are not
        normally passed to the computer from the TNC. AO-13 does not have
        any error checking at all, so it is up to the receiving station to
        visually inspect the data before trying to convert it to engineering
        units. UO-2 also transmits its telemetry as ASCII text, but the
        designers of the spacecraft recognized that the downlink was prone
        to error and incorporated a checksum in its data format. This
        section discusses the data formats and decoding equations associated
        with several of the OSCAR spacecraft.




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        7.1 DOVE (DO-17)

         DO-17 was launched January 22, 1990. Its prime mission is to
        provide an easily received Digital Orbiting Voice Encoded beacon for
        educational and scientific use. Dr. Torres 'Junior' de Castro,
        PY2BJO sponsored the DOVE experiment. DO-17 is licensed in Brazil
        with the callsign PT2PAZ. DO-17 was built by AMSAT, occupies less
        than a cubic foot of space, masses 8.5 kg and contains a V40
        microprocessor and 8 Megabytes of RAM. Essentially it is a loaded PC
        Clone in orbit. AO-16, DO-17, WO-18 and LO-19 are commonly known as
        Microsats and were constructed as a set by AMSAT during 1989. Each
        of the Microsats contains bar magnets which align them along the
        earth's magnetic field and is spun around that axis by photon
        pressure from the sun acting on the communication antennas which are
        painted white on one side and black on the other.

         Unfortunately a combination of two on-board hardware failures and
        lack of available manpower in AMSAT (a volunteer organization for
        all practical purposes) have kept DOVE's voice off the air. At this
        time DOVE only transmits packet telemetry. DO-17 transmits telemetry
        in several different transfer packets as shown in Figure 7-1.

         Figure 7-1 A typical example of a DO-17 Telemetry Frame.
        23-Jan-91  02:49:23  DOVE-1*>TIME-1:
        PHT: uptime is 173/00:36:26. Time is Wed Jan 23 02:47:30 1991

        23-Jan-91  02:49:26  DOVE-1*>TLM:
        00:59 01:59 02:87 03:31 04:59 05:5A 06:6E 07:52 08:6D 09:72 0A:A2
        0B:DC 0C:E9 0D:D8 0E:02 0F:26 10:CC 11:A8 12:01 13:04 14:AD 15:94
        16:98 17:94 18:96 19:98 1A:94 1B:91 1C:9B 1D:98 1E:25 1F:5F 20:BA

        23-Jan-91  02:49:27  DOVE-1*>TLM:
        21:95 22:82 23:24 24:1E 25:2A 26:01 27:02 28:02 29:01 2A:02 2B:02
        2C:01 2D:29 2E:02 2F:9E 30:CA 31:9E 32:11 33:CE 34:C4 35:9A 36:A8
        37:A6 38:B6

        23-Jan-91  02:49:28  DOVE-1*>STATUS:
         80 00 00 8F 00 18 CC 02 00 B0 00 00 0C 0E 3C 05 0B 00 04 04

        23-Jan-91  02:49:28  DOVE-1*>LSTAT:
        I P:0x3000 o:0 l:13081 f:13081, d:0

        23-Jan-91  02:49:28  DOVE-1*>WASH:
        wash addr:0680:0000, edac=0xd6


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         Telemetry data are transmitted in 57 (3A hex) channels in two
        segments in the TLM packets. The format is AA:BB where 'AA' is the
        hexadecimal channel number and 'BB' the hexadecimal value of the
        telemetry at the time it was sampled.

        The telemetry decoding equations for DOVE are shown in Table 7.1-1.

        The Equations are in the form of a quadratic equation,

        Y = A*N^2 + B*N + C  where: N = Telemetry Count (00 - FF);
         A, B, C = Equation Coefficients;
         Y = Result (In Specified Units).

        Note N must be converted from hexadecimal to decimal units before
        performing the calculation. A sample decoded page is shown in Table
        7.1-2.

         Table 7.1-1 DOVE Telemetry Decoding Equations

         Spacecraft:  DOVE-1:                Rev: 1 Date: 1/7/90
         HEX   Description:     C:           B:          A:        Units:
                            cccccccccc   bbbbbbbbbb   aaaaaaaaaa  uuuuuu
         0    Rx E/F Audio(W)+0.000       +0.0246      0.000       V(p-p)
         1    Rx E/F Audio(N)+0.000       +0.0246      0.000       V(p-p)
         2    Mixer Bias V:  +0.000       +0.0102      0.000       Volts
         3    Osc. Bias V:   +0.000       +0.0102      0.000       Volts
         4    Rx A Audio (W):+0.000       +0.0246      0.000       V(p-p)
         5    Rx A Audio (N):+0.000       +0.0246      0.000       V(p-p)
         6    Rx A DISC:     +10.427      -0.09274     0.000       kHz
         7    Rx A S meter:  +0.000       +1.000       0.000       Counts
         8    Rx E/F DISC:   +9.6234      -0.09911     0.000       kHz
         9    Rx E/F S meter:+0.000       +1.000       0.000       Counts
         A    +5 Volt Bus:   +0.000       +0.0305      0.000       Volts
         B    +5V Rx Current:+0.000       +0.000100    0.000       Amps
         C    +2.5V  VREF:   +0.000       +0.0108      0.000       Volts
         D    8.5V BUS:      +0.000       +0.0391      0.000       Volts
         E    IR Detector:   +0.000       +1.000       0.000       Counts
         F    LO Monitor I:  +0.000       +0.000037    0.000       Amps
        10    +10V Bus:      +0.000       +0.05075     0.000       Volts
        11    GASFET Bias I: +0.000       +0.000026    0.000       Amps
        12    Ground REF:    +0.000       +0.0100      0.000       Volts
        13    +Z Array V:    +0.000       +0.1023      0.000       Volts
        14    Rx Temp:       +101.05      -0.6051      0.000       Deg. C


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        15    +X (RX) temp:  +101.05      -0.6051      0.000       Deg. C
        16    Bat 1 V:       +1.7932      -0.0034084   0.000       Volts
        17    Bat 2 V:       +1.7978      -0.0035316   0.000       Volts
        18    Bat 3 V:       +1.8046      -0.0035723   0.000       Volts
        19    Bat 4 V:       +1.7782      -0.0034590   0.000       Volts
        1A    Bat 5 V:       +1.8410      -0.0038355   0.000       Volts
        1B    Bat 6 V:       +1.8381      -0.0038450   0.000       Volts
        1C    Bat 7 V:       +1.8568      -0.0037757   0.000       Volts
        1D    Bat 8 V:       +1.7868      -0.0034068   0.000       Volts
        1E    Array V:       +7.205       +0.07200     0.000       Volts
        1F    +5V Bus:       +1.932       +0.0312      0.000       Volts
        20    +8.5V Bus:     +5.265       +0.0173      0.000       Volts
        21    +10V Bus:      +7.469       +0.021765    0.000       Volts
        22    BCR Set Point: -8.762       +1.1590      0.000       Counts
        23    BCR Load Cur:  -0.0871      +0.00698     0.000       Amps
        24    +8.5V Bus Cur: -0.00920     +0.001899    0.000       Amps
        25    +5V Bus Cur:   +0.00502     +0.00431     0.000       Amps
        26    -X Array Cur:  -0.01075     +0.00215     0.000       Amps
        27    +X Array Cur:  -0.01349     +0.00270     0.000       Amps
        28    -Y Array Cur:  -0.01196     +0.00239     0.000       Amps
        29    +Y Array Cur:  -0.01141     +0.00228     0.000       Amps
        2A    -Z Array Cur:  -0.01653     +0.00245     0.000       Amps
        2B    +Z Array Cur:  -0.01137     +0.00228     0.000       Amps
        2C    Ext Power Cur: -0.02000     +0.00250     0.000       Amps
        2D    BCR Input Cur: +0.06122     +0.00317     0.000       Amps
        2E    BCR Output Cur:-0.01724     +0.00345     0.000       Amps
        2F    Bat 1 Temp:    +101.05      -0.6051      0.000       Deg. C
        30    Bat 2 Temp:    +101.05      -0.6051      0.000       Deg. C
        31    Baseplt Temp:  +101.05      -0.6051      0.000       Deg. C
        32    FM TX#1 RF OUT:+0.0256      -0.000884    +0.0000836  Watts
        33    FM TX#2 RF OUT:-0.0027      +0.001257    +0.0000730  Watts
        34    PSK TX HPA Temp+101.05      -0.6051      0.000       Deg. C
        35    +Y Array Temp: +101.05      -0.6051      0.000       Deg. C
        36    RC PSK HPA Temp+101.05      -0.6051      0.000       Deg. C
        37    RC PSK BP Temp:+101.05      -0.6051      0.000       Deg. C
        38    +Z Array Temp: +101.05      -0.6051      0.000       Deg. C
        39    S band TX Out: -0.0451      +0.00403     0.000       Watts
        3A    S band HPA Temp+101.05      -0.6051      0.000       Deg. C








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         Table 7.1-2 Sample Decoded (General Housekeeping) Page of DOVE
        Telemetry

        PHT: uptime is 177/12:34:12. Time is Sun Jan 27 14:45:16 1991

        -X Array Cur   : 0.174 A             Array V        :22.829 V
        +X Array Cur   : 0.000 A             +Z Array V     :23.836 V
        -Y Array Cur   : 0.000 A             Ext Power Cur  : 0.000 A
        +Y Array Cur   : 0.000 A             BCR Input Cur  : 0.480 A
        -Z Array Cur   : 0.000 A             BCR Output Cur : 0.314 A
        +Z Array Cur   : 0.251 A             BCR Set Point  :   119
        IR Detector    :    56               BCR Load Cur   : 0.241 A
        +Z Array Temp  :   3.0 C
        +Y Array Temp  :   4.8 C              Battery 1 V  : 1.330 V
                                              Battery 2 V  : 1.346 V
        +2.5V  VREF    : 2.506 V              Battery 3 V  : 1.337 V
        Ground REF     : 0.020 V              Battery 4 V  : 1.325 V
                                              Battery 5 V  : 1.350 V
         Bat 1 Temp   :   3.0 C               Battery 6 V  : 1.431 V
         Bat 2 Temp   : -24.8 C               Battery 7 V  : 1.343 V
         TX#1 RF OUT  :   0.0 W               Battery 8 V  : 1.344 V
         TX#2 RF OUT  :   3.7 W

         The TIME-1 packets identify the time that the data were downlinked.
        The Uptime value in the time packet tells you how long the software
        has been running (since last upload).

         The STATUS packets contain information about spacecraft on-board
        status. These bytes, have in the past, been changed by AMSAT without
        prior or post notification to the radio amateur community. The LSTAT
        packet contains engineering status information which has not been
        published other than that the last value "d:0" means the spacecraft
        is not set up as a digipeater.

        The WASH packets provide engineering information about the on-board
        RAM memory.

        7.2 UoSAT-2

         UoSAT-2 (UO-2) which was launched March 1, 1984, is similar to and
        is a follow on to the now re-entered UO-1. It was designed and built
        at the Department of Electronic and Electrical Engineering at the
        University of Surrey, England. It was built to develop scientific
        experimentation and space education. While much invaluable


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        experience has been received by the UoSAT people, not much has been
        published in the general educational and radio amateur press about
        its on-board experiments and telemetry data formats. As such, apart
        from a small group of dedicated users, UO-2 seems to have been
        ignored by the majority of radio amateurs and educational
        institutions.

         UO-2 carries four on-board experiments:- a Digital Communications
        Experiment, a Space Dust Experiment, a Charge Coupled Device (CCD)
        Video Camera Experiment and a Digitalker Experiment.

         The Digital Communications Experiment demonstrated the concept of
        store-and-forward digital communications using spacecraft in low
        earth orbit. The Space Dust Experiment measures the impact of dust
        particles, and calculates the momentum of the particles. The CCD
        Video Camera Experiment takes pictures of the earth at a resolution
        of 384 x 256 pixels with 128 gray levels. This exper-
         iment does not seem to have returned any usable pictures. The
        Digitalker Experiment provides clear digitized voice using a fixed
        vocabulary and is switched on from time to time.

         UO-2 transmits a number of different types of telemetry. WHATS-UP
        can only decode and display the real-time telemetry. Should you tune
        in signals from UO-2, you may get anything. Hang in there, sooner or
        later it will transmit real-time telemetry, if not on one pass, then
        on the next. The real-time telemetry is transmitted as 1200 baud
        ASCII data using FSK. The sense of the modulation is inverted with
        respect to convention due to the wide popularity of a BBC computer
        tape interface (which used the inverted modulation) in England at
        the time the spacecraft was built. This means that either a special
        modem has to be built to receive the data or the PK-232 has to be
        modified before it will copy signals from UO-2. This modification is
        needed because the PK-232 RXR parameter does not work above 300 baud
        due to a hardware limitation. This modification performs the
        equivalent of the RXR operation in hardware by taking advantage of
        an unused inverter inside the PK-232.

         What has to be done is to wire U15 pins 1 and 2 to a switch in
        series with the output to JP4. Adding a green LED to show the state
        of the switch (at a glance) is optional. The steps are as follows:

         1. Drill a 1/4 inch hole in the front panel of the PK-232 above the
            red DCD LED.
         2. Mount a Double Pole Double Throw (SPDT) switch on the front


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            panel of the PK-232 where it will not interfere with other
            components (near the upper left corner by the AEA logo above the
            threshold control).
         3. Carefully cut the circuit board trace connecting U15's pin 6 to
            the inside pin of JP4. This trace is easiest to cut where it
            comes out from under R20 on the top (component side) of the PC
            board. Be sure to double check that this is the correct trace
            with an ohm meter. Cut with care (with a sharp X-acto knife) so
            adjacent traces are not touched.
         4. Solder a jumper wire between U15's pins 1 and 6.
         5. Connect the center of one pole on this switch to the inner pin
            of JP4 or the trace that goes to it (which was cut to disconnect
            it from U15 pin 6).
         6. Connect the corresponding switch contact which will be hardware
            "RXR OFF" to U15 pin 6.
         7. Connect the corresponding switch contact which will be hardware
            "RXR ON" to U15 pin 2.
         8. Mount a green LED on the front panel of the PK-232 above the red
            DCD LED.
         9. Wire one leg of the LED to the other pole of the switch, the
            other end to a 1K ohm resistance (test the LED first to make
            sure you wire it the correct way).
         10. Wire the other end of the resistance to +12V near the voltage
            regulator. Do not wire it to the battery back up voltage (if the
            LED stays lit when you turn the PK-232 off, you wired it
            wrongly).
         11. Wire one side of the switch to ground so the green LED lights
            when the REVERSE position is selected.

         To copy the UO-2 FM AFSK ASCII Telemetry on 145.825 Mhz set the new
        hardware RXR switch in the "reverse" position. Be sure to return
        your RXR switch to "normal" when you want to return to regular
        operation, as this switch is in the signal path in all modes when
        the PK-232's internal modem is used.

         A typical telemetry frame starts with a non printing ASCII
        character (1E hexadecimal) followed by the identification and date.
        The date code can be deciphered using the following YYMMDDWHHMMSS
        format where YY is the last two digits of the year, MM, the month,
        DD, the day of the month, W, the day of the week (Sunday = 0), the
        remainder being hours,minutes and seconds. All times are given in
        UTC. A blank line follows, then follow seven lines worth of ten
        channels per line. The format of each line is as shown below.



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         NNDDDCNNDDDCNNDDDCNNDDDCNNDDDCNNDDDCNNDDDCNNDDDCNNDDDCNNDDDC

         where NN is the channel number, DDD the data and C a checksum to
        validate the data. The checksum is needed because there is no error
        checking built into the link. Each channel thus comprises six
        digits. The checksum is computed for each channel by 'exclusive
        or'ing (XOR) each nibble (4 bits) of each of the 6 characters in
        that channel. A zero result means that the data was received
        correctly, a non-zero result means the data was corrupted. Figure
        7.2-1 contains an example of the raw UO-2 data showing some of the
        errors due to noise on the downlink.

         Figure 7.2-1 Example of a Received Raw UO-2 Telemetry Data Frame

         00519D0141370267650361400404660503;4 6019E07045608040C08036C
         10519C11298312000313056114069A15529A!6188;175452185905195058
         20519F21220322662223000124001725000726093E27541528564D294681
         30519E31041732287C33568B34007035217236276637393D38426B39455E
         40649F41117242647343061044162545000146000247444748454949422x
         50456251108D52634653284p54663215000056p00357451258447A59460E
         60826A615FC1625F4A63334164440265160466174267700668000E69000F
         UOSAT-2           9101281004625

        7.3 AO-13

         AO-13 which was launched June 15, 1988 was built as a joint venture
        between radio amateurs in the U.S.A. and in Germany organized as the
        Radio Amateur Satellite Corporation (AMSAT). AO-13 is a spin
        stabilized long life long range radio amateur communications
        satellite which provides daily intercontinental communications
        capability for hours at a time. It contains a number of analog and
        digital transponders with communications links on several
        frequencies. An on-board computer based on the RCA 1802
        microprocessor controls the spacecraft and generates the downlink
        telemetry. Schedules are published in the amateur radio press which
        provide information as to which transponder is active at any time
        during the orbit. AO-13 also contains a motor which was used by
        radio amateurs to boost the spacecraft from the orbit the rocket
        placed it in into its operational orbit.

         AO-13 transmits telemetry in a number of ways on two beacons. The
        two meter beacon is on a frequency of 145.812 MHz and carries CW, 50
        baud RTTY, and 400 baud PSK telemetry according to a published
        schedule. WHATS-UP can only decode and display the 50 baud RTTY


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        telemetry which is transmitted in the form of Z blocks shown in
        Table 7.3-1. The block is identified as a 'Z' block by the letter
        'Z' before the words "HI. THIS IS AMSAT OSCAR 13" which identify the
        spacecraft.

         The block starts with the letter 'Z' in the first line. Time and
        status information follows, then the first telemetry channel begins
        several lines down and is shown with the value of 193. Six lines of
        telemetry, each line containing ten values are transmitted, with a
        blank line separating the two halves. Following the telemetry lines,
        the spacecraft may transmit plain text information of general
        interest. Although the Z block only contains 60 channels, the
        equations for decoding all 128 of the telemetry channels are
        presented in Table 7-3.2 in which the Channel Numbers are shown in
        Hexadecimal.

         The Bytes in the block are identified in the followings ways:

             C  - unsigned count (0 to +255)
             Cs - signed count (-128 to +127, 2s complement)
             Cx - signed count (+63 to -192, #3F=+63, #FF=-1, #80=-128,
                                #7F=-129, #40=-192, modified 2s complement)

         All temperature channels are decoded identically using the equation
        T = (C-120)/1.71 (in Degrees Centigrade). All channels measuring
        currents use a linear equation with different calibrations
        constants. Three equations are used providing maximum current values
        of 1A, 2.5A and 5A, as follows:

           1A:  I = (C-15)*4.854 mA
         2.5A:  I = (C-15)*12.135mA
           5A:  I = (C-15)*24.27 mA

         Table 7.3-1 AO-13 RTTY Telemetry Block

            Z  HI. THIS IS AMSAT OSCAR 13
                 05.02.54  8661
            .0086   .0000   .07B9

            64  6   0   1   16  218 1


            193 170 158 143 181 144 147 140 200 7
            147 7   7   7   165 29  100 7   149 7


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            10  7   145 115 34  7   153 129 122 180

            152 73  7   145 137 55  7   183 136 151
            7   154 137 169 211 142 127 100 9   140
            161 7   173 149 150 154 14  131 127 210
            HI THIS IS AMSAT OSCAR 13 08SEP90
            NEW AO13 SCHEDULE FROM 17OCT90 AFTER MOVE TO LON 180  LAT 0
            MODE B  MA 000 TO 095
            MODE JL MA 095 TO 125
            MODE LS MA 125 TO 130
            MODE S MA 130 TO 135
            MODE BS MA 135 TO MA 140
            MODE B  MA 140 TO 256

         Table 7.3-2 AO-13 Telemetry Decoding Equations

        #    Label          Equation             Remarks

        00   Uin-BCR        U=(C-10)*167mV   U-Panel: +0.6V @ 0.35A
                                                      +0.7V @ 1A
        01   Tx-PWRout-L    Average power=(261-C)^2 / 724 Watts rectified
                                             envelope voltage.
        02   T-Rx-U         Temp             Mode-B receiver temperature.
        03   ---
        04   Uout-BCR       U=(C-10)*79.5mV  BCR output voltage.
        05   ---
        06   T-TX-U         Temp             Mode-B transmitter temperature.
        07   I-14V-ST       5A               Transponder separation bus.
        08   U-10V-C        U=(C-10)*53.2mV  Computer supply
        09   Press He-Hi    off              Helium tank pressure.
        0A   T-IHU          Temp             Integrated Housekeeping Unit
        0B   I-14V-S        1A               Separation bus, 14V that
                                             supplies torquer and LIU.
        0C   BCR-Oscill1    >~6=OK           BCR status. No count = not
                                             working. Typically C=80.
        0D   Press He-Lo    off              Helium regulator output.
        0E   T-BCR          Temp             Battery Charge Regulator.
        0F   I-10V-C        1A               10V continuous power supply.
        10   BCR-Oscill2    As channel 0C
        11   Press Tank     off              N2O4 tank pressure.
        12   T-SEU          Temp             Sensor Electronics Unit
        13   IbatCharge     2.5A             Positive Current to battery.
        14   L-Sensor (A)   U=(C-10)*8.53mV  Light-Sensor Antenna Side.
        15   Motor Valve    off


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        16   T-ABAT1        Temp             Auxiliary battery 1
        17   I-BCR-OUT      5A               14V line to battery and other
                                             consumers.
        18   L-Sensor (M)   U=(C-10)*8.53mV  Light-Sensor Motor Side.
        19   ---
        1A   T-ABAT2        Temp             Auxiliary battery 2
        1B   I-BCR-IN       Equivalent to total current of all panels,
                            not available due to sensor failure.
        1C   Spin rate      C>131,  Spin rate=479/(C-109)-2 rpm
                            C<=131, Spin rate=(131-C)*0.85+20 rpm Sensor
                                             angular position oscillator.
                                             Lock indication channel #47.
        1D   Rx-L-AGC       Gain reduction=(C-75)^2 / 1125 dB
        1E   T-MBAT         Temp             Mean battery (normally in use)
        1F   I-Panel6       1A               Solar panel 6
        20   Tx-PWRout-U    Average power=(287-C)^2 / 1796 Watts As channel
                                             01.
        21   T-He-Tank      Temp
        22   T-Panel1       Temp
        23   I-Panel5       1A
        24   Rx-U-AGC       Gain reduction=(C-71)^2 / 2465 dB
        25   T-Tx-L         Temp             Mode-JL transmitter.
        26   T-Panel3       Temp
        27   I-Panel4       1A
        28   ---
        29   T-Rx-L         Temp             Mode-L receiver.
        2A   T-Panel5       Temp
        2B   I-Panel3       1A
        2C   U-14V-ST       U=(C-10)*66.8mV  Transponder separation bus.
        2D   T-RUDAK        Temp             RUDAK temperature.
        2E   T-top          Temp             Arm 1, Antenna side.
        2F   I-Panel2       1A
        30   U-9V-U         U=(C-10)*54mV    Internal 9 volt bus from Mode-B
                                             transponder.
        31   T-wall-arm2    Temp
        32   T-bottom       Temp             Arm 1, Motor side.
        33   I-Panel1       1A
        34   ---
        35   T-wall-arm1    Temp
        36   T-N2O4         Temp
        37   ---
        38   U-ABAT         U=(C-10)*78.5mV  Auxiliary battery.
        39   T-S-xpnder     Temp             Mode-S transponder.
        3A   T-L-Sensor     Temp             Light sensor antenna side.


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        3B   ---
        3C   U-9V-L         U=(C-10)*45.4mV  As channel 30, Mode-L
        3D   T-AZ50-Tank    Temp
        3E   T-nutation damper  Temp         Arm 3.
        3F   ---
        40   ES-Sensitivity 2MUX0            Earth Sensor sensitivity
                                             threshold. Bit significance
                                             0 LSB  20mV
                                             1      37mV      Hysteresis
                                             200mV
                                             2      75mV      Threshold
                                             600mV
                                             3     150mV
                                             4     300mV
                                             5     600mV
                                             6     1.2V
                                             7 MSB 2.4V
        41   Antenna/SERI   2MUX1            Antenna relays and SERI
                                             resistors.
                                             bit   significance
                                             0 LSB Hi-gain  2m  to U
                                             1     Hi-gain 70cm to L
                                             2     --+ SERI-1  load resistor
                                             for
                                             3     -+! SERI-2  both Light-
                                             Sensors       !! resistance
                                             00                7.5 Ohm
                                             01                3.9 Ohm
                                             10                2.3 Ohm
                                             11                5.9 Ohm
        42   RUDAK-Status   2MUX2            IN-B (ex Motor-PWR).
                            C=82, Standard-ROS  (S)
                            C=78, Emergency-ROS (N, Not-ROS)
                            C=80, Primitive-ROS (P)
        43   S&RUDAK-CNTL   2MUX3            Mode-S and RUDAK interface.
                            bit   significance
                            0 LSB RUDAK OFF
                            1       "   NMI/
                            2       "   Byte Clock
                            3       "   Byte count reset
                            4      ---
                            5     Mode-S Beacon ON
                            6       "    Squelch defeated
                            7 MSB   "    Squelch Hi Sensitivity


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        44   BCR-Sin        2MUX4            Array voltage offset.
                            U=29.1+(Cs*100)mV  (16.3V...41.8V)
        45   BCR-Sout       2MUX5            Battery knee voltage offset.
                            U=14.98+(Cx*20)mV  (11.14...16.2V = 192...63)
        46   BCR-relays     2MUX6
                            bit   significance
                            0 LSB BCR-2 ON
                            1     Auxiliary battery charging
                            2     Auxiliary battery connected,
                                  Main battery disconnected.

        47   SS-1           C=255 or C=0, PLL locked
                                             Sun-Sensor angular position
                                             oscillator, Slit antenna
                                             side.
        48   SS-2           Time offset from SS-1
        49   Flag-SS        C=1, SS-1        Sun sensor data.
                            C=2, SS-2
        4A   SPIN-RAW                        Raw spin count (1/256).

        4B   Sensor-control bit   significance  (OUT4)
                            0 LSB --+ MUX-CTRL for sensor elec. module
                            1     -+!
                                   !!
                                   00 - Sun data
                                   01 - spin ref./spin counter
                                   10 - ES lower beam
                                   11 - ES upper beam
                            2     Earth sensor positive edge select.
                                  (Strobes value of spin count at
                                  transition.)
                            3     Motor Instrumentation ON.
                                  (Pressure sensors, motor valve
                                  indicator.)
                            4     0.3V Sun Sensor Sensitivity
                            5     0.6V  "    "         "
                            6     1.2V  "    "         "
                            7 MSB 2.4V  "    "         "
                                  (Max. threshold #F = 1 solar constant)
        4C   SS-correction
        4D   Last ES-A      Z                last ES-pulse Antenna side.
        4E     "            O#               (Orbit number and MA value)
        4F   Last ES-M      Z                last ES-pulse Motor side.
        50     "            O#               (Orbit number and MA value)


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        51   Lockoutrange   Within +- C counts from sun sensor pip, earth
                            sensor handler ignores data (Spin count 1
                            circle = 256 counts.)
        52   ES-A           Strobed spin count at edge selected,
                                              Antenna Side beam.
        53   Update Flag1   Indicates update, Antenna Side beam.

        54   ES-M           As channel 52     Motor Side beam.
        55   Update Flag2   As channel 53      "    "    "
        56   S/C STATUS     bit   significance
                            0 LSB LIU power ON
                            1     S/A plug status 0=Safe, 1=Arm
                            2     RUDAK-out (lock)
                            3     Mode-S Squelch open
                            4     ---
                            5     Memory Soft error Counter
                            6       "         "      "
                            7 MSB   "         "      "
        57   ---
        58   ---
        59   ---
        5A   ---
        5B   N              no of 20ms per dot, morse speed.
        5C   n              running count of units for morse.
        5D   ---
        5E   TRANSPONDER    bit   significance  (OUT7)
                            0 LSB GB OFF
                            1     GB FSK (1=+170Hz)
                            2     DPSK OFF
                            3     EB ON
                            4     --+ PSK source
                            5     -+! for GB (EB: don't care)
                                   !!
                                   00 - no PSK
                                   01 - ranging
                                   10 - EB source
                            6     Low power transponder ON
                            7 MSB Passband OFF (Beacons and Mode-J +3dB)
        5F   ---
        60   MODUS          bit   significance  (magnet control)
                            0     magnet system ON
                            1     underspin magnet
        61   M-Soll         magnet vector desired angle to the despun sun
                            (clockwise as seen from top, 1 circle = 256)


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        WHATS-UP.DOC Release 1.40 Page 82


        62   M-Out          bit significance (OUT3, also L,S,J control)
                            0 LSB polarity Arm 1
                            1     polarity Arm 2
                            2     polarity Arm 3
                            3     Magnet power ON
                            4     Mode-J ON
                            5     ---
                            6     Mode-S ON
                            7 MSB Mode-L ON
        63   O-FRAC-lo      Fractional Z increment in 20ms
        64   O-FRAC-hi                       Counts down to 0 from preset
                                             value. 255th Z has different
                                             value of O-FRAC. ~7000
                                             counts/Z.
        65   O/256          Z from perigee
        66   O#-lo          Orbit number
        67   O#-hi
        68   UHR            10ms             UTC
        69                  sec
        6A                  min
        6B                  hour
        6C                  day              1 January 1978 = AMSAT day 0.
        6D                  256day
        6E   SU0            10ms             IPS stopwatch 0.
        6F                  sec
        70                  min
        71                  min*256
        72   SU1            10ms             IPS stopwatch 1.
        73                  sec
        74                  min
        75                  min*256
        76   SU2            10ms             IPS stopwatch 2.
        77                  sec
        78                  min
        79                  min*256
        7A   SU3            10ms             IPS stopwatch 3.
        7B                  sec
        7C                  min
        7D                  min*256
        7E   Event-Lo                        Used as event ID word in
        7F   Event-Hi                        intermediate buffer.





        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 83


        7.4 AO-16, WO-18 and LO-19

         AO-16, WO-18 and LO-19 were launched January 22, 1990 together with
        DO-17. AO-16 and LO-19 are designed to provide a platform for
        experiments with digital store-and-forward communications techniques
        as a follow-on to the Digital Communications Experiment of UO-2 11.
        LO-19 is sponsored by AMSAT in Argentina. WO-18 is an engineering
        project of the Center for Aerospace Studies at Weber State
        University in Utah. It has the capability for digital communications
        but is not used as such. It contains an on-board video camera which
        has returned pictures of the earth using a non standard format
        picture transmission format. WO-18 also carries a number of
        experiments. The Spectrometer experiment is designed to observe the
        spectrum of sunlight reflected off the earth's atmosphere and
        surface. The Particle Impact Detector is a piezoelectrical crystal
        mounted on the side of the spacecraft which produces an output
        voltage each time a microparticle impact occurs. The Magnetometer
        Experiment contains two orthogonal flux gate magnetometers. As they
        were not calibrated they can only provide information about relative
        changes in the magnetic environment of the spacecraft. As in the
        case of UO-2, data about the experiments and their telemetry
        calibrations is lacking in the general amateur radio press.

         These spacecraft downlink telemetry in the 437MHz band similar to
        that of DOVE but using a BINARY format in an unpublished and
        apparently "changeable at any time without notice" sequence. WHATS-
        UP intercepts the binary telemetry and converts it to a pseudo DOVE
        format as shown in Table 7.4-1 before decoding and displaying the
        information. The decoding equations first published by AMSAT in The
        AMSAT Journal are given in Tables 7.4-2, 7.4-3 and 7.4-4.


         Table 7.4-1 Example of Pseudo DOVE Display of Intercepted Binary
        Telemetry and other intercepted Microsat Packets

              27-Jan-91  17:04:22  LUSAT-1*>AMARG:
              Jan 23, 1600Z.

              AART driver loaded.
              Reload will continue in a short time

              73, LU7XAC
              AMARG Control Team



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        WHATS-UP.DOC Release 1.40 Page 84


              27-Jan-91  16:41:50  PACSAT-1*>TIME-1:
              PHT: uptime is 004/10:14:01. Time is Sun Jan 27 16:40:51 1991

              27-Jan-91  16:41:54  PACSAT-1*>AMSAT:
              Jan  22, 8:03 UTC - Reload in progress. Digi on. No BBS till
              the weekend. NK6K

              27-Jan-91  16:41:54  PACSAT-1*>LSTAT:
              I P:0x3000 o:0 l:13884 f:13884, d:1 st:0
              27-Jan-91  16:42:48  N8ITP>PACSAT-1*>N8ITP [C]
              27-Jan-91  16:42:50  N8ITP>PACSAT-1*>N8ITP (UA)
              27-Jan-91  16:42:55  N8ITP>PACSAT-1*>N8ITP:
              test1122334455

              27-Jan-91  17:04:22  LUSAT-1*>BCRXMT:
              vmax=762169 battop=766771 temp=218292

              27-Jan-91  17:06:31  LUSAT-1*>LSTAT:
              I P:0x3000 o:0 l:13417 f:13417, d:0 st:2

              27-Jan-91  17:06:38  LUSAT-1*>TIME-1:
              PHT: uptime is 005/14:48:41. Time is Sun Jan 27 17:05:33 1991

              27-Jan-91  17:06:41  LUSAT-1*>TLM:
              00:DC 01:0E 02:30 03:0F 04:3A 05:10 06:DE 07:11 08:84 09:12
              0A:00 0B:13 0C:E4 0D:14 0E:A9 0F:15 10:A8 11:16 12:6C 13:17
              14:64 15:18 16:69 17:19 18:69 19:1A 1A:66 1B:1B 1C:6D 1D:1C
              1E:5F 1F:1D 20:62 21:1E 22:D9 23:1F 24:62 25:20 26:BA 27:21
              28:B0 29:22 2A:79 2B:23 2C:2C 2D:24 2E:24 2F:25 30:28 31:00

              14-Feb-91  03:02:48  N4HY>LUSAT-1*>N4HY [D]
              14-Feb-91  03:02:49  N4HY>LUSAT-1*>N4HY (UA)
              14-Feb-91  03:03:09  LUSAT-1*>COMLUS:
              COMMAND 9 ACK

              14-Feb-91  03:06:51  LUSAT-1*>STATUS:
              31 34 2D 46 65 62


         Table 7.4.2 AO-16 Telemetry Decoding Equations

         Spacecraft:  PACSAT-1:                            Rev:
                                                           Date: 7/25/91



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        WHATS-UP.DOC Release 1.40 Page 85


         Equations are in the form: Y = A*N^2 + B*N + C

                                    where:

                                       N = Telemetry Count (00 - FF)
                                       A, B, C = Equation Coefficients
                                       Y = Result (In Specified Units)

         HEX   Description:        C:           B:        A:      Units:
                              cccccccccc   bbbbbbbbbb   aaaaaaaaaa  uuuuuu

          0    Rx D DISC:     +9.202       -0.08990     0.000       kHz
          1    Rx D S meter:  +0.000       +1.000       0.000       Counts
          2    Rx C DISC:     +9.179       -0.09277     0.000       kHz
          3    Rx C S meter:  +0.000       +1.000       0.000       Counts
          4    Rx B DISC:     +9.837       -0.08838     0.000       kHz
          5    Rx B S meter:  +0.000       +1.000       0.000       Counts
          6    Rx A DISC:     +9.779       -0.09144     0.000       kHz
          7    Rx A S meter:  +0.000       +1.000       0.000       Counts
          8    Rx E/F DISC:   +10.817      -0.09911     0.000       kHz
          9    Rx E/F S meter:+0.000       +1.000       0.000       Counts
          A    +5 Volt Bus:   +0.000       +0.0305      0.000       Volts
          B    +5V Rx Current:+0.000       +0.000250    0.000       Amps
          C    +2.5V  VREF:   +0.000       +0.0108      0.000       Volts
          D    +8.5V Bus:     +0.000       +0.0391      0.000       Volts
          E    IR Detector:   +0.000       +1.000       0.000       Counts
          F    LO Monitor I:  +0.000       +0.000037    0.000       Amps
         10    +10V Bus:      +0.000       +0.0500      0.000       Volts
         11    GASFET Bias I: +0.000       +0.000026    0.000       Amps
         12    Ground REF:    +0.000       +0.0100      0.000       Volts
         13    +Z Array V:    +0.000       +0.1023      0.000       Volts
         14    Rx Temp:       +101.05      -0.6051      0.000       Deg. C
         15    +X (RX) temp:  +101.05      -0.6051      0.000       Deg. C
         16    Bat 1 V:       +1.8225      -0.0038046   0.000       Volts
         17    Bat 2 V:       +1.9418      -0.0046890   0.000       Volts
         18    Bat 3 V:       +1.8699      -0.0041641   0.000       Volts
         19    Bat 4 V:       +1.7403      -0.0032880   0.000       Volts
         1A    Bat 5 V:       +1.8792      -0.0042492   0.000       Volts
         1B    Bat 6 V:       +2.0499      -0.0054532   0.000       Volts
         1C    Bat 7 V:       +1.9062      -0.0045331   0.000       Volts
         1D    Bat 8 V:       +1.7536      -0.0033192   0.000       Volts
         1E    Array V:       +8.055       +0.06790     0.000       Volts
         1F*   +5V Bus:       +2.864583    4.090715E-2 -1.930042E-4 Volts
         20*   +8.5V Bus:     +7.720951    +8.25979E-3 -1.76254E-5  Volts


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        WHATS-UP.DOC Release 1.40 Page 86


         21*   +10V Bus:      +8.882535    +1.39771E-2  0.000       Volts
         22    BCR Set Point: -6.1130      +1.1270      0.000       Counts
         23    BCR Load Cur:  -0.0477      +0.00767     0.000       Amps
         24    +8.5V Bus Cur: -0.00179     +0.000894    0.000       Amps
         25    +5V Bus Cur:   -0.00104     +0.00406     0.000       Amps
         26    -X Array Cur:  -0.00995     +0.00243     0.000       Amps
         27    +X Array Cur:  -0.02370     +0.00254     0.000       Amps
         28    -Y Array Cur:  -0.02220     +0.00273     0.000       Amps
         29    +Y Array Cur:  -0.01810     +0.00259     0.000       Amps
         2A    -Z Array Cur:  -0.02230     +0.00221     0.000       Amps
         2B    +Z Array Cur:  -0.02000     +0.00232     0.000       Amps
         2C    Ext Power Cur: -0.02000     +0.00250     0.000       Amps
         2D*   BCR Input Cur: -2.103334E-2 +3.382738E-3 0.000       Amps
         2E*   BCR Output Cur:-7.146611E-3 -5.247935E-5 4.878499E-5 Amps
         2F    Bat 1 Temp:    +101.05      -0.6051      0.000       Deg. C
         30    Bat 2 Temp:    +101.05      -0.6051      0.000       Deg. C
         31    Baseplt Temp:  +101.05      -0.6051      0.000       Deg. C
         32    PSK TX RF Out: -0.0291      +0.00361     +0.0000869  Watts
         33    RC PSK TX Out: +0.0055      +0.00172     +0.0001180  Watts
         34    PSK TX HPA Temp+101.05      -0.6051      0.000       Deg. C
         35    +Y Array Temp: +101.05      -0.6051      0.000       Deg. C
         36    RC PSK HPA Temp+101.05      -0.6051      0.000       Deg. C
         37    RC PSK BP Temp:+101.05      -0.6051      0.000       Deg. C
         38    +Z Array Temp: +101.05      -0.6051      0.000       Deg. C
         39    S band HPA Temp:  0.00       1.0000      0.000       Counts
         3A    S band TX Out: -0.0088      +0.00435     0.000       Watts

         * Revised in this release

         Table 7.4.3 WO-18 Telemetry Decoding Equations

          Spacecraft:  WEBER-1:                            Rev: 1
                                                               Date: 1/7/90

                Equations are in the form: Y = A*N^2 + B*N + C

                                           where:
                                           N = Telemetry Count (00 - FF)
                                           A, B, C = Equation Coefficients
                                            Y = Result (In Specified Units)






        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 87


          HEX   Description:        C:           B:          A:      Units:
                               cccccccccc   bbbbbbbbbb   aaaaaaaaaa  uuuuuu

           0    Rx D DISC:     +11.087      -0.08949     0.000       kHz
           1    Rx D S meter:  +0.000       +1.000       0.000       Counts
           2    Rx C DISC:     +10.322      -0.09448     0.000       kHz
           3    Rx C S meter:  +0.000       +1.000       0.000       Counts
           4    Rx B DISC:     +10.348      -0.09004     0.000       kHz
           5    Rx B S meter:  +0.000       +1.000       0.000       Counts
           6    Rx A DISC:     +11.387      -0.09535     0.000       kHz
           7    Rx A S meter:  +0.000       +1.000       0.000       Counts
           8    Rx E/F DISC:   +10.746      -0.09348     0.000       kHz
           9    Rx E/F S meter:+0.000       +1.000       0.000       Counts
           A    +5 Volt Bus:   +0.000       +0.03523     0.000       Volts
           B    +5V Rx Current:+0.000       +0.000234    0.000       Amps
           C    +2.5V  VREF:   +0.000       +0.0133      0.000       Volts
           D    8.5V BUS:      +0.000       +0.0524      0.000       Volts
           E    IR Detector:   +0.000       +1.000       0.000       Counts
           F    LO Monitor I:  +0.000       +0.000033    0.000       Amps
          10    +10V Bus:      +0.000       +0.0767      0.000       Volts
          11    GASFET Bias I: +0.000       +0.000026    0.000       Amps
          12    Ground REF:    +0.000       +0.0100      0.000       Volts
          13    +Z Array V:    +0.000       +0.1023      0.000       Volts
          14    Rx Temp:       +100.01      -0.5980      0.000       Deg. C
          15    +X (RX) Temp:  +100.01      -0.5980      0.000       Deg. C
          16    Bat 1 V:       +1.8292      -0.0037196   0.000       Volts
          17    Bat 2 V:       +1.8202      -0.0036943   0.000       Volts
          18    Bat 3 V:       +1.8050      -0.0036721   0.000       Volts
          19    Bat 4 V:       +1.8576      -0.0038979   0.000       Volts
          1A    Bat 5 V:       +1.8095      -0.0037439   0.000       Volts
          1B    Bat 6 V:       +1.8979      -0.0041754   0.000       Volts
          1C    Bat 7 V:       +1.8246      -0.0038126   0.000       Volts
          1D    Bat 8 V:       +1.7486      -0.0030475   0.000       Volts
          1E    Array V:       +7.800       +0.06790     0.000       Volts
          1F    +5V Bus:       +1.838       +0.0312      0.000       Volts
          20    +8.5V Bus:     +5.793       +0.0184      0.000       Volts
          21    +10V Bus:      +7.650       +0.0250      0.000       Volts
          22    BCR Set Point: -6.1963      +1.1277      0.000       Counts
          23    BCR Load Cur:  -0.0405      +0.00620     0.000       Amps
          24    +8.5V Bus Cur: +0.00384     +0.000830    0.000       Amps
          25    +5V Bus Cur:   -0.00763     +0.00394     0.000       Amps
          26    -X Array Cur:  -0.00140     +0.00210     0.000       Amps
          27    +X Array Cur:  +0.00946     +0.00226     0.000       Amps
          28    -Y Array Cur:  -0.01018     +0.00224     0.000       Amps


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        WHATS-UP.DOC Release 1.40 Page 88


          29    +Y Array Cur:  -0.01168     +0.00239     0.000       Amps
          2A    -Z Array Cur:  -0.01516     +0.00237     0.000       Amps
          2B    +Z Array Cur:  -0.02111     +0.00239     0.000       Amps
          2C    Ext Power Cur: -0.02000     +0.00250     0.000       Amps
          2D    BCR Input Cur: -0.02189     +0.00332     0.000       Amps
          2E    BCR Output Cur:-0.03019     +0.00327     0.000       Amps
          2F    Bat 1 Temp:    +100.01      -0.5980      0.000       Deg. C
          30    Bat 2 Temp:    +100.01      -0.5980      0.000       Deg. C
          31    Baseplate Temp:+100.01      -0.5980      0.000       Deg. C
          32    PSK TX RF Out: +0.2104      -0.01203     +0.0001786  Watts
          33    RC PSK TX Out: +0.0340      -0.00969     +0.0002198  Watts
          34    PSK TX HPA Temp+100.01      -0.5980      0.000       Deg. C
          35    +Y Array Temp: +100.01      -0.5980      0.000       Deg. C
          36    RC PSK HPA Temp+100.01      -0.5980      0.000       Deg. C
          37    RC PSK BP Temp:+100.01      -0.5980      0.000       Deg. C
          38    +Z Array Temp: +0.0000      +1.0000      0.000       Counts

         Table 7.4.5 LO-19 Packet Telemetry Decoding Equations
                Spacecraft:  LUSAT-1:                             Rev: 1
                                                               Date: 1/7/90

                Equations are in the form: Y = A*N^2 + B*N + C
                                           where:
                                         N = Telemetry Count (00 - FF)
                                         A, B, C = Equation Coefficients
                                         Y = Result (In Specified Units)

          HEX   Description:        C:           B:         A:       Units:
                               cccccccccc   bbbbbbbbbb   aaaaaaaaaa  uuuuuu

           0    Rx D DISC:     +9.802       -0.08779     0.000       kHz
           1    Rx D S meter:  +0.000       +1.000       0.000       Counts
           2    Rx C DISC:     +8.429       -0.09102     0.000       kHz
           3    Rx C S meter:  +0.000       +1.000       0.000       Counts
           4    Rx B DISC:     +9.291       -0.08317     0.000       kHz
           5    Rx B S meter:  +0.000       +1.000       0.000       Counts
           6    Rx A DISC:     +9.752       -0.08310     0.000       kHz
           7    Rx A S meter:  +0.000       +1.000       0.000       Counts
           8    Rx E/F DISC:   +10.110      -0.08610     0.000       kHz
           9    Rx E/F S meter:+0.000       +1.000       0.000       Counts
           A    +5 Volt Bus:   +0.000       +0.0305      0.000       Volts
           B    +5V Rx Current:+0.000       +0.000250    0.000       Amps
           C    +2.5V  VREF:   +0.000       +0.0108      0.000       Volts
           D    8.5V BUS:      +0.000       +0.0391      0.000       Volts


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           E    IR Detector:   +0.000       +1.000       0.000       Counts
           F    LO Monitor I:  +0.000       +0.000037    0.000       Amps
          10    +10V Bus:      +0.000       +0.0508      0.000       Volts
          11    GASFET Bias I: +0.000       +0.000026    0.000       Amps
          12    Ground REF:    +0.000       +0.0100      0.000       Volts
          13    +Z Array V:    +0.000       +0.1023      0.000       Volts
          14    Rx Temp:       +93.24       -0.5609      0.000       Deg. C
          15    +X (RX) Temp:  +93.24       -0.5609      0.000       Deg. C
          16    Bat 1 V:       +1.7343      -0.0029740   0.000       Volts
          17    Bat 2 V:       +1.7512      -0.0032113   0.000       Volts
          18    Bat 3 V:       +1.7790      -0.0034038   0.000       Volts
          19    Bat 4 V:       +1.7286      -0.0030036   0.000       Volts
          1A    Bat 5 V:       +1.8114      -0.0036960   0.000       Volts
          1B    Bat 6 V:       +1.7547      -0.0032712   0.000       Volts
          1C    Bat 7 V:       +1.7151      -0.0030739   0.000       Volts
          1D    Bat 8 V:       +1.6846      -0.0028534   0.000       Volts
          1E    Array V:       +8.100       +0.06790     0.000       Volts
          1F    +5V Bus:       +2.035       +0.0312      0.000       Volts
          20    +8.5V Bus:     +5.614       +0.0184      0.000       Volts
          21    +10V Bus:      +7.650       +0.0250      0.000       Volts
          22    BCR Set Point: +3.7928      +1.0616      0.000       Counts
          23    BCR Load Cur:  -0.0244      +0.00628     0.000       Amps
          24    +8.5V Bus Cur: +0.00412     +0.000773    0.000       Amps
          25    +5V Bus Cur:   +0.02461     +0.00438     0.000       Amps
          26    +X Array Cur:  -0.01614     +0.00232     0.000       Amps
          27    -X Array Cur:  -0.01158     +0.00238     0.000       Amps
          28    -Y Array Cur:  +0.00278     +0.00206     0.000       Amps
          29    +Y Array Cur:  +0.00136     +0.00218     0.000       Amps
          2A    -Z Array Cur:  +0.00370     +0.00209     0.000       Amps
          2B    +Z Array Cur:  -0.00793     +0.00216     0.000       Amps
          2C    Ext Power Cur: -0.02000     +0.00250     0.000       Amps
          2D    BCR Input Cur: -0.00901     +0.00283     0.000       Amps
          2E    BCR Output Cur:+0.00663     +0.00344     0.000       Amps
          2F    Bat 1 Temp:    +93.24       -0.5609      0.000       Deg. C
          30    Bat 2 Temp:    +93.24       -0.5609      0.000       Deg. C
          31    Baseplt Temp:  +93.24       -0.5609      0.000       Deg. C
          32    PSK TX RF Out: +0.1059      +0.00095     +0.0000834  Watts
          33    RC PSK TX Out: +0.0178      +0.00135     +0.0000833  Watts
          34    PSK TX HPA Temp+93.24       -0.5609      0.000       Deg. C
          35    +Y Array Temp: +93.24       -0.5609      0.000       Deg. C
          36    RC PSK HPA Temp+93.24       -0.5609      0.000       Deg. C
          37    RC PSK BP Temp:+93.24       -0.5609      0.000       Deg. C
          38    +Z Array Temp: +93.24       -0.5609      0.000       Deg. C
          39    LU Bcn Temp A: +93.24       -0.5609      0.000    *  Deg. C


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          3A    LU Bcn Temp D: +93.24       -0.5609      0.000    ** Deg. C
          3B    Coax Rly Stat: +0.000       +1.0000      0.000       Counts
          3C    Coax Rly Stat: +0.000       +1.0000      0.000       Counts

        *  Note 1: Thermistor located near box center adjacent to LU
                   thermistor channel no. 5.
        ** Note 2: Thermistor located near -X face of box on the experiment
                   baseplate.

         LO-19 also transmits 8 channels of CW telemetry, at 12 W.P.M. with
        reduced morse code (to save about 44% power). The format of the
        telemetry is:

         E LUSAT HI HI NL 111 222 333 444 555 666 777 888

         where:
                E is a calibration point to measure the output power.

                NL:N is the EPROM version number. There are 7 copies of the
                     program in the EPROM, to prevent crashes or hang ups
                     due to degradation effects. The on board computer
                     automatically loads a valid version, and N indicates
                     which version was loaded.

                L is the result of an internal RAM memory test by the 6805
                     microprocessor. If L=0, the RAM is "OK". If L=E, an
                     Error was detected.

         The telemetry decoding equations for the LO-19 CW are shown in
        Table 7.4.6.

                   Table 7.4.6 LO-19 CW Telemetry Decoding Equations

                CH# 1 = N1 +5 Reg Volts  :     636/N1         (Volts)
                CH# 2 = N2 +10 Volts Battery   0.064*N2       (Volts
                CH# 3 = N3 CW TX Temperature   0.354(134.7-N3) (Deg. C)
                CH# 4 = N4 CW TX Power Output  (10.9+N)^2/40.1 (Watts)
                CH# 5 = N5 Temp. BOX No. 4     0.356(136-N5)  (Deg. C)
                CH# 6 = N6 +10 V Current       0.7*N6         (mAmps.)
                CH# 7 = N7 Panel +Z Volts      0.15*N7        (Volts)
                CH# 8 = N8 Reg. +8.5 Volts     0.056*N8       (Volts)

         A typical example of a CW telemetry frame is shown below.



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                E LUSAT HI HI 1O 128 167 042 162 040 148 045 156

        decoding it, We have: E LUSAT HI HI

                NL = 1O :  N=1 (first version) ; L=O (Memory 6805 RAM  "OK")

                N1=128: 636/128          = + 4.97  V. REG.
                N2=167: 0.064*167        = +10.69  V. BATTERY
                N3=042: 0.354(134.7-042) =  32.81  Deg. C
                N4=162: (10.9+162)^2/40.1= 745.5   mW.
                N5=040: 0.356(136-040)   =  34.17  Deg. C
                N6=148: 0.7*148          = 103.6   mA. (over 10 V)
                N7=045: 0.15*045         = + 6.75  V. +Z
                N8=156: 0.056*156        = + 8.736 V. REG.

        NOTE: the reduced cw code is USED ONLY for the numeric data, and
        AFTER the "HI HI" as in the following example.

          L     U     S     A      T       H    I     H   I      1   O

                1: .-      (A)       6: -.... (6)
                2: ..-     (U)       7: -...  (B)
                3: ...-    (V)       8: -..   (D)
                4: ....-   (4)       9: -.    (N)
                5: .       (E)       0: -     (T)

        7.5 Fuji-OSCAR 20

         FO-20 which was launched on February 7, 1990 is a communications
        satellite in low earth orbit providing simultaneous analog and
        digital communications capability. FO-20 was built in Japan for
        Japanese radio amateurs and is the second Japanese built OSCAR.

         On February 7 1990, the National Space Development Agency of Japan
        (NASDA) put the Marine Observation Satellite (MOS) 1b into orbit.
        The launch vehicle also carried two secondary payloads, FO-20 and
        the Deployable Boom and Umbrella Test (DEBUT) spacecraft which is
        similar in shape and weight to FO-20. MOS-1b was placed into a
        circular polar orbit, then DEBUT and Fuji-OSCAR 20 separated from
        the launch vehicle at 0233, above Santiago, Chile. First signals
        from the spacecraft were received in Tokyo around 0309 UTC.

         FO-20 is similar in construction to FO-12. In fact, much of it was
        originally constructed as a backup to FO-12 and designated as JAS-


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        1B. It has since been modified and improved as a result of the
        lessons learned during the flight of FO-12. FO-12 was known as Fuji-
        1 in Japan, so this spacecraft is known by the Japanese as Fuji-2
        and as FO-20 by the rest of the world.

         FO-20's planned service life is 5 years. It is in a sunsynchronous
        elliptical polar orbit, having a perigee of about 900 km and an
        apogee of about 1740 at an inclination of 99 degrees. The Period of
        the orbit is about 105 minutes. This orbit is optimal for MOS-1b
        which is to study oceanographic resources and observe agricultural
        environmental conditions. In this orbit, the spacecraft passes over
        a given line of latitude at approximately the same time each day. In
        this orbit, the spacecraft is shielded from the sun by the earth for
        about 33% of the time. This eclipse means that the solar cells can
        only provide power for about 70 minutes in each orbit and that the
        on-board nickel cadmium storage batteries have to power the
        spacecraft for the remaining 35 minutes.

         FO-20 weighs about 50 kg. and is a polyhedron shaped spacecraft
        440mm in diameter and 470mm in height covered by approximately 1500
        gallium arsenide solar cells which provide about 11 Watts of power
        to keep the 11 series-connected NiCad cells (rectangular) with a
        capacity of 6 AH charged. There are 26 sides to the polyhedron which
        almost makes it spherical for all practical purposes other than
        sticking solar cells to it. FO-12 was the same shape but only
        carried about 600 cells. This larger number of cells means that FO-
        20 has a positive power budget and should not need to be switched
        off to recharge.

         The Power supply converts the raw bus voltage of +11 to +18 V (+14
        V average) to the three regulated voltages (+10 V, +5 V, -5 V) used
        by the rest of the satellite with an efficiency greater than 70%.

         The attitude of the satellite is maintained by using the torque
        generated by the interaction of two permanent magnets with the
        earth's magnetic field. This is a fairly conventional technique used
        in the OSCAR series. Temperature stability is achieved by using
        thermal insulation.

         FO-20 carries two Mode J transponders, both of which may be
        operational at the same time. One transponder is analog (Mode JA),
        the other is digital (Mode JD).

         The frequencies and capabilities of the analog transponder are


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        similar to those of FO-12. It consists of an inverted heterodyne
        linear translator with a passband 100 kHz wide, operating with a
        mode J Uplink passband of 145.9 to 146.00 MHz, and a corresponding
        Downlink Passband of 435.9 to 435.8 MHz. The spacecraft has a
        Transmitter Output of approximately 1 watt. A ground station needs
        an Uplink EIRP of about 100 W to communicate through the
        transponder. The JA telemetry beacon is on the nominal frequency of
        435.795 MHz with a power output of about 100 mW and can use CW or
        PSK modulation. FO-20 is using the callsign 8J1JBS and the beacons
        transmit telemetry in the same manner as FO-12.

         The digital transponder provides store-and-forward packet
        communication using AX.25 link level protocol, version 2. Stations
        who used FO-12 are able to use FO-20 without making any
        modifications to their equipment. The uplink requires Bi-phased
        Manchester code on an FM signal, at a bit rate of 1200 bps. There
        are four Uplink Frequencies: 145.85 MHz, 145.87 MHz, 145.89 MHz,
        145.91 MHz. The necessary ground station Uplink EIRP is also about
        100 W. The transponder has an output power of about 1 W on a
        downlink frequency of 435.91 MHz and uses NRZI PSK at 1200 bps. The
        same PSK modem used to copy FO-12 or the Microsats is needed to copy
        FO-20. The downlink channel also carries packet telemetry.

         The on-board 144 MHz receiving antenna is a ring turnstile mounted
        at the bottom of the side panels. The 435 MHz transmitting antenna
        is a turnstile antenna mounted at the top of satellite. Both
        antennas are circularly polarized. Ground tests have shown that the
        transmitting antenna is more omnidirectional than that of FO-12,
        however due to the structure of the hybrid circuitry which allow
        both transponders to share the same antenna, the sense of the
        circular polarization on the downlink is different for each mode. As
        the apparent polarization is different depending on the geometry
        between the spacecraft and the groundstation, you will probably have
        to change between left hand and right hand circular polarization
        during a pass. The spacecraft is designed so that you can usually
        keep the uplink and downlink polarization the same.

         Mode JA has provided strong transatlantic signals and many CW and
        SSB QSOs. Mode-JD was switched on for the first time during Orbit
        #95. To Digipeat via FO-20 you don't need to use a digipeater call.
        With the present version of the software, all AX.25 frames with a
        valid CRC heard by the spacecraft will be digipeated.

         The spacecraft also carries a BBS which is accessed by means of the


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        same commands used to access a terrestrial WA7MBL/W0RLI/AA4RE type
        of BBS. You access the BBS by connecting to 8J1JBS on any of the
        four uplink channels. When you do connect to it, make sure that you
        disconnect before LOS because FO-20 only allows 16 simultaneous
        connections. Stations that hang in there after the satellite drops
        below their local horizon block access by other stations and have
        been christened 'Zombies'. The BBS program is a modified version of
        the BBS program written for FO-12 and allows the use of 4 banks
        (1Mbyte) of memory. A typical list of messages copied by KI6QE is
        shown in Figure 7.5-1.

         Figure 7.5-1 Typical Message Listing from the BBS (copied by KI6QE)

                Fuji-OSCAR 20/JAS1b Mailbox ver. 2.00
                commands [B/F/H/M/R/U/W]
                Use H command for Help
                JAS>JAS>NO. DATE   UTC    FROM    TO      SUBJECT
                0086 04/13 05:15  WB6GFJ  W6SHP   Welcome
                0085 04/13 05:14  WB6LLO  KI6QE   SOFTWARE
                0084 04/13 05:14  WB6GFJ  W9FMW   Our Chat
                0082 04/13 03:38  W9FMW   WA4EJR  MESSAGE ON CIS
                0080 04/13 03:36  KG6EX   N1GCR   From Ashley
                0078 04/13 03:32  KG6EX   KD8SI   From Ashley
                0077 04/13 03:31  KG6EX   N8AM    From Ashley
                0076 04/13 03:30  KG6EX   DD4YR   From Ashley
                0075 04/13 03:27  KG6EX   DL1CR   From Ashley
                0074 04/13 03:25  KG6EX   G3RUH   From Ashley

         The spacecraft telemetry is transmitted either as CW or as PSK. The
        CW telemetry monitors 12 analog data points and 33 status points,
        the PSK telemetry monitors 29 analog data points and 33 status
        points. Telemetry data from Fuji-OSCAR 20 is transmitted on both the
        mode JA and JD beacons. Mode JA sends data by Morse code on the
        beacon signal of 435.795 MHz, repeating one frame every one minute.
        Mode JD sends a telemetry packet every 2 seconds on the digital
        downlink channel of 435.91 MHz when the telemetry mode is operating,
        otherwise, one frame is downlinked every one minute. The spacecraft
        can downlink up to 30 items of data and 31 items of status in the
        telemetry. The Mode JA beacon however only carries 12 data elements
        and most of status bytes.

         Mode JA Telemetry Data The Mode JA beacon transmits the telemetry
        data in the format shown below. These data are sent by Morse code
        with a "HI HI" at the beginning of each frame, with a speed of about


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        100 characters every minute, and always in this format repeatedly.

                 HI  HI  1A  1B  1C  1D
                         2A  2B  2C  2D
                         3A  3B  3C  3D
                         4A  4B  4C  4D
                         5A  5B  5C  5D

         The number identifies the group, the letters A through D are
        decimal values expressed in two digits. Let this two-digit be N, for
        each item, true value or engineering value is obtained by decoding N
        as shown below. For example, a value of 123 for 1A means group 1 and
        23 is the measured value of the solar array current. Groups 4 and 5
        contain status information about the bird, where A, B, C and D
        represent octal two-digit combinations of 00 through 37. This
        corresponds to a combination of five binary digits. Each bit shows
        status of each designated item in the order from MSB (Most
        Significant Bit) to LSB (Least Significant Bit). The decoding
        equations for the CW Mode JA telemetry are shown in Figure 7.5-2.

         Figure 7.5-2 Fuji-OSCAR 20 Mode JA Telemetry Conversion Equations

                CH  DESCRIPTION                       CALIBRATION   UNITS

                1A  total solar array current          19x(N+0.4)   mA
                1B  battery charge/discharge current  -38x(N-50)    mA
                1C  battery voltage                   (N+4)x0.22    V
                1D  center tap voltage of battery     (N+4)x0.1     V
                2A  bus voltage                       (N+4)x0.2     V
                2B  +5 V regulator voltage            (N+4)x0.062   V
                2C  JTA output power                  2.0x(N+4)^1.618mW
                2D  calibration voltage               (N+4)/50      V
                3A  battery temperature               1.4x(67-N)  deg. C
                3B  baseplate temperature #1          1.4x(67-N)  deg. C
                3C  baseplate temperature #2          1.4x(67-N)  deg. C
                3D  baseplate temperature #3          1.4x(67-N)  deg. C

         The status byte conversions are shown in Figure 7.5-3. This method
        is used because all items whose status is represented in this manner
        only have two possible situations, either ON or OFF, or binary
        values 0 or 1. For example, if the first item of status 4A were 423,
        the 4 identifies group 4, and the 23 should be thought of as its
        equivalent binary code (10011). This shows  the status in the order
        of MSB to LSB, or bit 4 to bit 0. Using the decoding data 423 can be


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        decoded as follows.

                1: Beacon is PSK,
                0: Engineering data #2 is blank,
                0: Engineering  data  #1 is blank,
                1: JTD power is ON,
                1: JTA power is ON.

                Figure 7.5-3 Fuji-OSCAR 20 Mode JA System Status Bytes

                CH BIT  DESCRIPTION     STATE
                                        1     0

                4A  0   JTA power       ON    OFF
                4A  1   JTD power       ON    OFF
                4A  2   Eng. data #1    ---   ---
                4A  3   Eng. data #3    ---   ---
                4A  4   Beacon          PSK   CW

                4B  0   UVC             ON    OFF
                4B  1   UVC level       1     2
                4B  2   Battery         tric  full
                4B  3   Battery logic   tric  full
                4B  4   Main relay      ON    OFF

                4C  0   PCU             bit 1 (LSB)
                4C  1   PCU             bit 2 (LSB)
                4C  2   PCU             manual  auto
                4C  3   Eng. data #3    ---   ---
                4C  4   Eng. data #4    ---   ---

                4D  0   Memory bank #0  ON    OFF
                4D  1   Memory bank #1  ON    OFF
                4D  2   Memory bank #2  ON    OFF
                4D  3   Memory bank #3  ON    OFF
                4D  4   Computer power  ON    OFF

                5A  0   Memory select   bit 1 (LSB)
                5A  1   Memory select   bit 2 (MSB)
                5A  2   Eng. data #5    ---   ---
                5A  3   Eng. data #6    ---   ---
                5A  4   Eng. data #7    ---   ---
                5B  0   Solar panel #1  lit   dark
                5B  1   Solar panel #2  lit   dark


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                5B  2   Solar panel #3  lit   dark
                5B  3   Solar panel #4  lit   dark
                5B  4   Solar panel #5  lit   dark
                5C  0   JTA CW beacon   CPU   TLM
                5C  1   Eng. data #8    ---   ---
                5C  2   Eng. data #9    ---   ---
                5C  3   Eng. data #10   ---   ---
                5C  4   Eng. data #11   ---   ---
                5D  0   Eng. data #12   ---   ---
                5D  1   Eng. data #13   ---   ---
                5D  2   Eng. data #14   ---   ---
                5D  3   Eng. data #15   ---   ---
                5D  4   Eng. data #16   ---   ---

        Telemetry data are downlinked on Mode JD by means of packets. These
        data are transmitted the ASCII format shown in Figure 7.5-4. In the
        ASCII telemetry (RA and RB) XXX is a 3 digit decimal number with a
        range between 000 to 999. This number represents the value of N in
        Table 5 for channels denoted #00 - #26.

         Figure 7.5-5 contains the equations for converting the received
        data into engineering values. The YYY bytes are three hexadecimal
        bytes of system status data, denoted #27a - #29c and can be decoded
        as shown in Figure 7.5-6. The SSS byte in the last row are binary
        status data, denoted #30a - #39c. Figure 7.5-7 provides the
        information needed to decode them in a manner similar to the Mode JA
        status points shown in Figure 7.5-3.

         Figure 7.5-4. Fuji-OSCAR 20 Mode JD PSK telemetry data format

                 JAS-1b FF YY/MM/DD HH:MM:SS
                 XXX XXX XXX XXX XXX XXX XXX XXX XXX XXX
                 XXX XXX XXX XXX XXX XXX XXX XXX XXX XXX
                 XXX XXX XXX XXX XXX XXX XXX YYY YYY YYY
                 SSS SSS SSS SSS SSS SSS SSS SSS SSS SSS

        where, FF is the Frame Identifier, which may contain the following
        types:
                 RA: Realtime telemetry, - ASCII
                 RB: Realtime telemetry, - Binary
                 SA: Stored telemetry, - ASCII
                 SB: Stored telemetry, - Binary
                 M0: Message #0
                 M1: Message #1


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                   ...........
                 M9: Message #9

        YY/MM/DD is year/month/day, and HH:MM:SS is hour/minute/second, all
        in UTC.

         Figure 7.5-5. Fuji-OSCAR 20 Mode JD Telemetry Decoding Equations
                CH   DESCRIPTION                  CALIBRATION/UNITS

                #00  total solar array current     1.91x(N-4)mA
                #01  battery charge/discharge     -3.81x(N-508)mA
                #02  battery voltage              Nx0.022V
                #03  battery center voltage       Nx0.009961V
                #04  bus voltage                  Nx0.02021 V
                #05  +5 V regulator voltage       Nx0.00620 V
                #06  -5 V regulator voltage      -Nx0.00620 V
                #07  + 10 V regulator voltage     Nx0.0126  V
                #08  JTA output power             5.1x(N-158)mW
                #09  JTD output power             5.4x(N-116)mW
                #10  calibration voltage #2       N/500 V
                #11  offset voltage #1            N/500 V
                #12  battery temperature          0.139x(669-N)deg. C
                #13  JTD temperature              0.139x(669-N)deg. C
                #14  Baseplate Temperature #1     0.139x(669-N)deg. C
                #15  Baseplate Temperature #2     0.139x(669-N)deg. C
                #16  Baseplate Temperature #3     0.139x(669-N)deg. C
                #17  Baseplate Temperature #4     0.139x(669-N)deg. C
                #18  temperature calibration #1   N/500 V
                #19  offset voltage #2            N/500 V
                #20  Solar Cell Panel Temp   #1   0.38x(N-685)deg. C
                #21  Solar Cell Panel Temp   #2   0.38x(N-643)
                #22  Solar Cell Panel Temp   #3   0.38x(N-646)
                #23  Solar Cell Panel Temp   #4   0.38x(N-647)
                #24  -------------------------
                #25  temperature calibration #2   N/500 V
                #26  temperature calibration #3   N/500 V
                ---------------------------------------------------------

                Figure 7.5-6. Fuji-OSCAR 20 Mode JD HEX System Status Bytes

                CH   DESCRIPTION
                #27a  Spare (TBD)
                #27b  Spare (TBD)
                #27c  Spare (TBD)


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                #28a  Spare (TBD)
                #28b  Spare (TBD)

                #28c  error count of memory unit #0
                #29a  error count of memory unit #1
                #29b  error count of memory unit #2
                #29c  error count of memory unit #3

        Figure 7.5-7. Fuji-OSCAR 20 Mode JD BINARY System Status Bytes.

                CH    DESCRIPTION             STATE
                                            1      0

                #30a  JTA power             on     off
                #30b  JTD power             on     off
                #30c  JTA beacon            PSK    CW
                #31a  UVC status            on     off
                #31b  UVC level             1      2
                #31c  main relay            on     off
                #32a  engineering data #1     -----
                #32b  battery status        tric   full
                #32c  battery logic         tric   full
                #33a  engineering data #2     -----
                #33b  PCU status            bit 1 (LSB)
                #33c  PCU status            bit 2 (MSB)
                #34a  memory unit  #0       on    off
                #34b  memory unit  #1       on    off
                #34c  memory unit  #2       on    off
                #35a  memory unit           on     off
                #35b  memory select         bit 1 (LSB)
                #35c  memory select         bit 2 (MSB)
                #36a  engineering data #3     ------
                #36b  engineering data #4     ------
                #36c  computer power        on    off
                #37a  engineering data #5     ------
                #37b  solar panel #1        lit  dark
                #37c  solar panel #2        lit  dark
                #38a  solar panel #3        lit  dark
                #38b  solar panel #4        lit  dark
                #38c  solar panel #5        lit  dark
                #39a  engineering data #6     ------
                #39b  CW beacon source      CPU   TLM
                #39c  engineering data #7     ------



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         A typical set of raw PSK telemetry packets are those captured by
        KI6QE and shown in Figure 7.5-8. A typical decoded and display page
        from WHATS-UP is shown in Figure 7.5-9 for a different set of raw
        data.

         Figure 7.5-8 Fuji-OSCAR 20 PSK telemetry (as copied by KI6QE)

                              03-Apr-90  17:40:32  8J1JBS*>BEACON:
                              JAS1b RA 90/04/03 17:45:18
                              554 433 700 686 757 837 841 823 398 666
                              617 001 503 516 526 523 526 523 654 000
                              683 675 685 684 999 643 875 316 002 000
                              110 111 000 000 100 000 001 011 111 000

                              03-Apr-90  17:40:34  8J1JBS*>BEACON:
                              JAS1b RA 90/04/03 17:45:20
                              566 427 699 705 746 837 841 824 541 659
                              617 001 503 516 526 523 526 523 654 000
                              683 675 686 683 999 642 874 316 002 000
                              110 111 000 000 100 000 001 011 111 000


        Figure  7.5-9 Sample Decoded Display (General Housekeeping)
                         Page from Fuji-OSCAR 20.

                                        JAS1b RA 91/01/13 00:40:58

        Solar Panel Temp #1:  15.20 Deg.C Total Array Current:1105.89 mA
        Solar Panel Temp #2:  31.92 Deg.C Battery Charge     : 102.87 mA
        Solar Panel Temp #3:  32.68 Deg.C Battery Voltage    : 14.806 V
        Solar Panel Temp #4:  29.64 Deg.C Battery Center     :  6.744 V
        Baseplate Temp. #1 :  40.73 Deg.C Bus Voltage        : 17.259 V
        Baseplate Temp. #2 :  41.42 Deg.C   +5 V Regulator   :  5.214 V
        Baseplate Temp. #3 :  40.87 Deg.C   -5 V Regulator   :  0.000 V
        Baseplate Temp. #4 :  41.14 Deg.C  +10 V Regulator   : 10.471 V
        Temperature Cal. #1:   1.30 V     Offset Voltage #1  :  0.000 V
        Temperature Cal. #2:   1.29 V     Offset Voltage #2  :  0.000 V
        Temperature Cal. #3:   1.75 V     Calibration Volt #2:  1.230 V
        Battery Temp.     :  45.04 Deg.C JTA TX Output Power:   0.46 W
        JTD Temperature   :  42.12 Deg.C JTD TX Output Power:   3.52 W






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        8.0 Spacecraft No Longer Active

         This section is provided for post mission analysis of digital data
        from spacecraft that are no longer active in case you have access to
        data from those satellites and wish to the tools in WHATS-UP to view
        and analyze the data.

        8.1 Fuji-OSCAR 12

         The FO-12 PSK Telemetry Data Format. It is practically identical to
        the FO-20 format. The format is shown in Table 8.1-1, the decoding
        equations are presented in Table 8.1-2.

         Table 8.1-1 Fuji-OSCAR 12 PSK Telemetry Frame Format

                Table 8.1-1 Fuji-OSCAR 12 PSK Telemetry Frame Format

                JAS-1 FF YY/MM/DD HH:MM:SS
                xxx xxx xxx xxx xxx xxx xxx xxx xxx xxx
                xxx xxx xxx xxx xxx xxx xxx xxx xxx xxx
                xxx xxx xxx xxx xxx xxx xxx xxx yyy yyy
                sss sss sss sss sss sss sss sss sss sss

          FF := Frame Identifier   RA: Realtime Telemetry - ASCII
                                   RB: Realtime Telemetry - Binary
                                   SA: Stored Telemetry - ASCII
                                   SB: Stored Telemetry - Binary
                                   M0: Message #0
                                   M1: Message #1
                                   .......
                                   M9: Message #9

          YY/MM/DD  =  Date

          HH:MM:SS  =  Time (The command station attempts to keep the clock
                       as close as possible to UTC)

          [ Following is valid only for RA and SA frames ]

          xxx =  000 - 999  Format:  3  digit  decimal  (Analog  Data)   28
                       samples  in  row 0 column 0 through row 2  column  7
                       (denoted #00 - #27 below)

            y =  0 - F one byte Hex (System Status Data)


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                       9 samples in row 2 column 8  through  row 2 column 9
                       (denoted #28a - #29c below)

            s =  0 or 1  Binary Status Data
                               30 samples in row 3  through  row 3 column 9
                               (denoted #30a - #39c below)

         Table 8.1-2 Fuji-OSCAR 12 Telemetry Calibration Equations

         Ch.    Item                          Equation    Units

         #00     Total Solar Array Current     1.91 * ( N - 4 )    mA
         #01     Battery Charge/Discharge      3.81 * ( N - 528 )  mA
         #02     Battery Voltage               N * 0.0210    V
         #03     Half-Battery Voltage          N * 0.00937   V
         #04     Bus Voltage                   N * 0.0192    V
         #05     + 5 V. Regulator Voltage      N * 0.00572   V
         #06     - 5 V. Regulator Voltage      N * -0.00572  V
         #07     +10 V. Regulator Voltage      N * 0.0116    V
         #08     JTA Power Output              5.1 * ( N  - 158 )  mW
         #09     JTD Power Output              5.4 * ( N - 116 )   mW
         #10     Calibration Voltage #2        N / 500  V
         #11     Offset Voltage #1             N / 500  V
         #12     Battery Temperature           0.139 * ( 689 - N )  Deg. C
         #13     JTD Temperature               0.139 * ( 689 - N )  Deg. C
         #14     Baseplate Temperature #1      0.139 * ( 689 - N )  Deg. C
         #15     Baseplate Temperature #2      0.139 * ( 689 - N )  Deg. C
         #16     Baseplate Temperature #3      0.139 * ( 689 - N )  Deg. C
         #17     Baseplate Temperature #4      0.139 * ( 689 - N )  Deg. C
         #18     Temperature Calibration #1    N / 500  V
         #19     Offset Voltage #2             N / 500  V
         #20     Facet Temperature #1          0.38 * ( N - 684 )  Deg. C
         #21     Facet Temperature #2          0.38 * ( N - 684 )  Deg. C
         #22     Facet Temperature #3          0.38 * ( N - 690 )  Deg. C
         #23     Facet Temperature #4          0.38 * ( N - 683 )  Deg. C
         #24     Facet Temperature #5          0.38 * ( N - 689 )  Deg. C
         #25     Temperature Calibration #2    N / 500  V
         #26     Temperature Calibration #3    N / 500  V
         #27     Depth of Battery discharge    ( N - 500 ) / 189   AH







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         Fuji-OSCAR 12 System Status Telemetry Bytes

         Ch.    Item

         #28a    Spare (TBD)
         #28b    Spare (TBD)
         #28c    Memory Unit #0 error count

         #29a    Memory Unit #1 error count
         #29b    Memory Unit #2 error count
         #29c    Memory Unit #3 error count

         Fuji-OSCAR 12 Binary Status Data Points

         Ch.   Item                       1         0

         #30a   JTA Power                On        Off
         #30b   JTD Power                On        Off
         #30c   JTA Beacon               PSK       CW

         #31a   UVC Status               On        Off
         #31b   UVC Level                1         2
         #31c   Main Relay               On        Off

         #32a   Engineering Data #1      ----      ----
         #32b   Battery Status           Tric      Full
         #32c   Battery Logic            Tric      Full

         #33a   Engineering Data #2      ----      ----
         #33b   PCU Status                Bit 1 (LSB)
         #33c   PCU Status                Bit 2 (MSB)

         #34a   Memory Unit #0           On        Off
         #34b   Memory Unit #1           On        Off
         #34c   Memory Unit #2           On        Off

         #35a   Memory Unit #3           On        Off
         #35b   Memory Select             Bit 1 (LSB)
         #35c   Memory Select             Bit 2 (MSB)

         #36a   Engineering Data #3      ----      ----
         #36b   Engineering Data #4      ----      ----
         #36c   Computer Power           On        Off



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         #37a   Engineering Data #5      ----      ----
         #37b   Solar panel #1           Lit       Dark
         #37c   Solar panel #2           Lit       Dark

         #38a   Solar panel #3           Lit       Dark
         #38b   Solar panel #4           Lit       Dark
         #38c   Solar panel #5           Lit       Dark

         #39a   Engineering Data #6      ----      ----
         #39b   CW beacon source         CPU       TLM
         #39c   Engineering Data #7      ----      ----

        8.2 SARA-OSCAR 23

         On 17 July 1991, the attention of AMSAT and the rest of world's
        amateur radio satellite communicators was focused on UoSAT-F. UoSAT-
        F became UoSAT 5 when it separated from the launcher and another
        OSCAR carrying a packet amateur communications payload was in orbit.
        The University of Surrey calls the spacecraft UO-5, AMSAT and radio
        amateurs call it OSCAR 22 or UO-22. UO-5/UO-22 is a scientific
        satellite similar to UO-4, launched in 1990.

         Hardly anyone noticed that the same Ariane launch vehicle carried
        the SARA spacecraft, which became OSCAR 23 a few seconds after
        UoSAT-F became UoSAT-5. SARA-OSCAR 23 (SO-23) was built at
        ESIEESPACE, an aerospace club at the Ecole Superieure d'Ingenieurs
        en Electrotechnique et Electronique (ESIEE), in France. SARA is the
        culmination of six years of development work which included building
        payloads for balloon and sub orbital rocket launches.

         SARA is not an amateur radio communications satellite. Although not
        as complex, it is also an educational and experimental satellite
        similar to the spacecraft built at the University of Surrey in
        England, (UO-1, UO-2, UO-3, UO-4 and UO-5). It holds (and identifies
        using) the callsign FX0SAT. SARA stands for "Satellite for Amateur
        Radio Astronomy".

         Radio astronomy was born in 1932 with the discovery by Karl Jansky
        at the Bell Telephone Laboratories in New Jersey that radio waves
        were coming from a source in the sky. SARA is not amateur radio's
        first connection with radio astronomy. In 1937, Grote Reber, W9GFZ,
        designed and built the world's the first radio telescope, a 31ft.
        (9.4m) dish antenna, in his own backyard in Wheaton, IL. Using this
        antenna, he discovered the first discrete radio sources in the sky


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        and mapped the distribution of radio emissions in the Milky Way.
        Grote Reber was the only person doing research in Radio Astronomy
        before World War II and single-handedly brought radio astronomy to
        the attention of professional astronomers. Like Grote Reber, SARA is
        also a pioneer, albeit with a two fold mission.

        8.2.1 The Primary Mission

         SARA's primary mission was a Radio Astronomy Experiment to listen
        for hf radio signals from Jupiter's radio-electric activities in the
        decametric wavelengths. Jupiter is known to be emitting radio noise
        in the hf frequency bands. This Jovian DX cannot be investigated by
        a terrestrial station because for much of the time, either the Earth
        or its atmosphere blocks the signals. In the past, a few other
        satellites have measured the Jovian emissions, but not for a long
        enough period of time to achieve meaningful results.

         Jupiter's radio emissions in the decametric band is powerful enough
        to wipe out all other natural extra terrestrial signal sources under
        normal conditions. In the vicinity of the earth, the flux received
        from Jupiter ranges from 10.E-20 to 5.10.E-19 W.m^-2.Hz^-1 which is
        much stronger than the galactic background noise. During the Sun's
        calm period, the flux received from the sun is about 10.E-24 W.m^-
        2.Hz^-1. During periods of high solar activity it increases to 10.E-
        17 W.m^-2.Hz^-1. The solar eruptions can be distinguished from the
        Jovian signals by their signal strength, length of time, and by
        correlation with signals received on other wavelengths. Jupiter's
        radio activity in the decametric band is partially known: above 15
        MHz the ionosphere sometimes becomes transparent and makes it
        possible to do some measurements, which can then be extrapolated to
        the 2 to 15 MHz band.

         The Jovian decametric emission is irregular. It occurs mostly
        during storms that last from periods ranging from one minute to an
        hour. Depending on the type of storm, radio-electrical energy is
        concentrated into peaks of 1 to 50 mS or 1 to 10 S, in frequency
        bands about 50 KHz wide sweeping across the spectrum. These storms
        are closely related to the rotation of Jupiter's satellite Io and to
        Jupiter's own rotation. Solar eruptions may also influence them.

         Voyager 1 carried out reception tests in the vicinity of Jupiter,
        but because of electromagnetic interference from its own instruments
        in the decametric band, it could only detect the strongest peaks of
        the Jovian emissions. To date, no measurements have yet been made in


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        WHATS-UP.DOC Release 1.40 Page 106


        the 2 to 15 MHz band during a period of high solar activity. SARA is
        a pioneer following a voyager.

         The radio-electrical waves are received by means of three pairs of
        aerials placed perpendicularly to each other. This configuration
        allows computation of the intensity of the field regardless of its
        direction and polarization.

         As the received electromagnetic field is quite strong, three pairs
        of short aerials, five meters long are used. One of the pairs is
        also used to downlink telemetry data to earth in the 2 m band. The
        aerials are made of 100 mm wide steel tape. They were rolled up for
        the launch and unrolled themselves as soon as they were freed in
        orbit.

         The Jovian emissions between 2 and 15 MHz are measured on eight
        channels, each of them 100 KHz wide. The on board equipment averages
        their amplitude over a time interval of 150 S. The average amplitude
        produces the envelope of the storms but hides the peaks, which
        represent the internal structure of the storms. A single receiver is
        switched between the channels and between the three pairs of
        aerials. The receiver thus gets in succession the three
        polarizations of each of the eight channels. This cycle is executed
        several times during the 150 S to prevent the measurements on the
        different channels from being separated in time.

         The receiver has a 40 dB dynamic range in order to detect the
        Jovian peaks as well as certain solar ones without saturating the
        receiver. This allows for enough sensitivity to detect the galactic
        background noise which is constant at a known level, and which will
        serve as a reference standard when Jupiter and the sun are silent.

        8.2.2 The Secondary Mission

         Consider the reliability of the electronic components in a
        spacecraft. SARA uses consumer-made components, rather than military
        or space qualified parts, for reasons of cost and availability. Why
        do professional satellites use the most expensive components, and
        why did SARA do otherwise? The launch causes vibrations amounting to
        10 g. Once the payload gets into orbit, outer space is a favorable
        environment for electronic equipment. As a result, SARA is made from
        components that have been tested and burnt in.

         Commercial mass produced components are just as reliable as


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        conventional space qualified parts. For instance, a TV set that can
        work for 10 years or more without needing repairs has to be built
        out of very reliable components. While SARA doesn't use hardened
        components, it doesn't use risky components either. Chemical
        capacitors are banished, the Power Amplifier transistors are
        oversized and well cooled, the PROMs are debugged after programming,
        as advised by the manufacturer. SARA's equipment is simple and
        conservatively designed and that is why, statistically, a long
        operational life can be anticipated for the satellite.

        8.2.3 The Downlink

         The satellite circles the earth in 100 minutes on its low, sun
        synchronous, quasi-polar orbit at an altitude of about 770 km
        downlinking its data continuously. One telemetry transfer frame
        cycle takes 2 minutes 48 seconds. An uplink command capability can
        shut the beacon down if it causes QRM.

         The downlink transmitter power of the satellite was about 1 W at
        145.955 MHz. The carrier wave was modulated in amplitude with a +/-
        3400 Hz spectrum using AFSK coding at frequencies of 1200 and 2200
        Hz at a speed of 300 bits/s. The aerial polarization was linear.

        8.2.4 The Onboard Electronics

         The electronics are controlled by a sequencer because data
        acquisition and transmission are made at different rates and times.
        All the logic state machines required for the experiment are built
        on a single printed circuit card, the remaining cards being analog
        or combinational logic. This approach simplified the design of the
        equipment and testing.

         The sequencing card manages the measurements: it specifies the
        frequency and the pair of aerials to be used by the receiver,
        digitizes and stores the data, interprets received commands, and
        prepares the telemetry. Data stored during a 24 hour time period is
        time-tagged and downlinked in telemetry cycles lasting a few
        minutes.

         The functions described above are performed by a microcontroller.
        As the program must operate over a period of years in spite of
        errors that could occur due to interference or ionizing particles,
        it will be reset regularly.



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        8.2.5 The Power System

         The power system supplies power to the electronics equipment, and
        also started the satellite up after the launch, having detected the
        separation from the launcher. After a proper time delay, the energy
        system freed the aerials and started supplying power to the
        equipment. The equipment needs about 3 W and uses a non-regulated
        voltage bus that is locally regulated to 5 V.

         During certain times of the year, the satellite is eclipsed by the
        earth for up to a third of each orbit. A storage battery is thus
        used as a permanent power supply. The battery is charged when sun
        shines on the photovoltaic cells. The battery is protected against
        overloading.

         Because the satellite does not have an attitude control system,
        sunlight can hit it from any direction. Solar cells were placed on
        each side of the space craft, which is in the form of a cube. Its
        size was calculated so that each side is able to supply power for
        the whole experiment. This means 60% of the surface of the 470 mm
        cube was covered with high quality cells.

         Separation from the launcher was detected by a push button that
        directly controlled the power supply for the on-board experiment and
        the cutter to free the aerials. In addition, the power supply is
        controlled by a security circuit.

        8.2.6 Mechanical integration

         Integration is based on a single plate 400 mm by 400 mm, on which
        everything else is mounted; the electronic equipment, the aerials,
        the solar cells, the interface with the launcher and the manual
        controls.

         The solar cells are placed on two half shells made of aluminum
        sheets that constitute the case when they are brought together. The
        integration plate is easily accessible when they are removed. Each
        piece of equipment is a box. The cables are directly connected to
        the pieces they connect. The whole mechanical structure is made of
        aluminum pieces. The junctions that carry strains are soldered. The
        spacecraft when assembled is a cube measuring about 470 mm each
        side.




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        8.2.7 Thermal Control

         To accomplish their mission, the electronic equipment and the
        batteries need moderate temperatures. These temperatures can be
        achieved using passive controls. The internal temperature only
        depend on exterior conditions (Sun and Earth) and on the satellite's
        characteristics.

         The target temperature is an average of + 20 C, which can be
        achieved by choosing appropriate coatings for the external surfaces
        of the satellite. About 40% of the surface was not covered with
        solar cells and was thermally coated. The shape of the box was
        chosen so as to have a quasi-constant section in all directions,
        temperature being then independent from the orientation of the
        satellite relative to the sun. The equipment dissipates 3 W and does
        not modify the thermal balance of the structure.

         The heat must be able to pass easily from the lighted sides to the
        dark ones so that temperatures remain close to the average. The
        problem is simplified by the small size of the satellite, and by the
        use of aluminum shells 2 mm thick which are enough to limit the
        thermal gap to 30 degrees. The satellite then does not need to be
        spun to maintain thermal control.

        8.2.8 Educational Opportunities

         SARA provided a unique educational opportunity in orbital dynamics.
        The radio signals SARA monitored are generated by the interaction
        between Jupiter and and one of its moons (Io) as a beam of radio
        energy. Why? How? The signals are synchronized to sidereal time and
        appear roughly four minutes earlier successive day. Why? It takes
        about two hours for the beam to swing across the earth. Why?

         Ideally SARA should have been placed in an orbit in which the earth
        never gets between the spacecraft and Jupiter. SARA however took the
        orbit the Ariane rocket gave it, an orbit optimized for the primary
        payload, the Earth Resources Satellite (ERA-1). When the earth gets
        between SARA and Jupiter there will be breaks in reception of Jovian
        signals for up to 40 minutes each orbit.

         Plot the current positions of Jupiter and the Earth in the solar
        system. Look at the angles between Jupiter and the orbital plane of
        SARA around the Earth. Does the Earth eclipse SARA? If so, how long
        before the geometry is such that SARA will get uninterrupted viewing


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        of Jupiter? If SARA has uninterrupted viewing, how long will this
        condition last? If SARA receives signals when it is eclipsed by the
        earth, what are they and where are they coming from?

        8.3 ARSENE

         The ARSENE satellite was launched in the spring of 1993. It carried
        a conventional AX.25 digipeater using frequency modulated (FM)
        uplinks and downlinks. Unfortunately ARSENE's 2 meter downlink
        failed during launch. Several stations made contacts via the S Band
        transponder until it also failed several months later.

         ARSENE began in the early 1980's about the same time as Phase 3.
        The spacecraft is built from parts left over from other projects by
        students and apprentices. ARSENE was 3 axis stabilized and carried
        two transponders, Mode B (digital) and Mode S (analog). The Mode S
        downlink is linear on 2446.540 MHz (0.8W). The uplink was centered
        on 435.110 MHz with a 16 kHz Bandwidth. The mode B uplinks were
        digital at 435.050, 435.100 and 435.150 MHz, the downlink was on
        149.975 MHz (15/2W) using standard AX.25 FM equipment. The orbit is
        36000 km apogee with a 20000 km perigee at an inclination of 0
        degrees. This results in an orbit with an approximate 16 hour
        period.

        8.3.1 Arsene Telemetry Equations

         This information is provided in case anyone has any ARSENE
        Telemetry. The ARSENE packet beacon transmitted 30 analog telemetry
        channels providing information about the function of the different
        on-board modules on the satellite. The telemetry decoding equations
        for the analog telemetry channels are shown below.

        Channel Units   Parameter                               Equation

        A3      I    Battery unload current          y=1.664v +0.198
        A4      V    Battery end charge threshold    y=1.008v +12.94
        A5      V    Battery voltage                 y=2v +8.72
        A6      W    VHF PA output power             y=0.05v^3+0.531v^2+0.25v
        A7      V    Primary bus voltage             y=7.152v
        A8      I    VHF PA current (10 V)           y=0.365v +0.149
        A9      I    VHF PA current (26 V)           y=0.365v +0.149
        A11     V    RSSI voltage TC channel         y=v
        A13     I    Primary bus current             y=0.619v +0.019
        A15     V    First VHF PA voltage            y=9v


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        A17     I    Solar generator current         y=0.573v
        A18     I    Dc-dc converter input current   y=0.256v +0.02
        A19     I    Shunt regulator current         y=0.669v -0.185
        A21     I    Battery load current            y=0.174v -0.027
        A22     T    Battery temperature             y=14v
        A23     T    Solar generator #1 temper.      y= - 0.679033v^5 +
                                                      9.57784v^4 -
                                                      51.2412v^3 +
                                                      127.622v^2 - 170.345v
                                                      + 97.7918
        A24     T    Solar generator #5 temper.      y= - 0.679033v^5 +
                                                      9.57784v^4 -
                                                      51.2412v^3 +
                                                      127.622v^2 - 170.345v
                                                      + 97.7918
        A38     V    Fifth battery element voltage   y=0.982v + 3.258
        A42     T    Plateau temperature             y= - 0.337702v^5 +
                                                      4.60193v^4 -
                                                      25.4481v^3 +
                                                      71.3428v^2
                                                     -119.362v + 109.681
        A44     T    Shunt regulator temperature     y= - 0.337702v^5 +
                                                      4.60193v^4 -
                                                      25.4481v^3 +
                                                      71.3428v^2 - 119.362v
                                                      + 109.681
        A46     T    Solar generator #3 temperature  y= - 0.771085v^5 +
                                                      10.2258v^4 -
                                                      51.6250v^3+123.311v^2
                                                      - 154.219v + 62.7882
        A48     T    Electro gates 5-6 temperature   y= - 0.337702v^5 +
                                                      4.60193v^4 -25.4481v^3
                                                      + 71.3428v^2
                                                     - 119.362v + 109.681
        A53     P    Nitrogen tank pressure          y=69.463v
        A54     T    VHF PA temperature              y= - 0.337702v^5 +
                                                      4.60193v^4 -
                                                      25.4481v^3 +
                                                      71.3428v^2 - 119.362v
                                                      + 109.681
        A55     T    Nitrogen tank #4 temperature    y= - 0.337702v^5 +
                                                      4.60193v^4 -
                                                      25.4481v^3 + 1.3428v^2
                                                     -119.362v + 109.681


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        A58     V    RSSI voltage channel 1          y=v
        A60     V    RSSI voltage channel 2          y=v
        A62     V    RSSI voltage channel 3          y=v
        A69     T    Nitrogen tank #1 temperature    y= - 0.337702v^5 +
                                                      4.60193v^4 -
                                                      25.4481v^3 +
                                                      71.3428v^2 - 119.362v
                                                      + 109.681
        A71     V    Dosimetre 5 experiment          y=v

         The telemetry value of each channel is between 0-255. This
        corresponds to a voltage "v" between 0 - 5 Volts. The real value "y"
        of measured parameters is calculated from the formulas.

         - Voltage V in Volt.
         - Current I in Amp.
         - Temperature in Celsius.
         - Pressure P in Bars and power W in Watt.

         The next table gives the normal range and the alarm thresholds of
        different channels:

                                        Alarm threshold
        Channel Normal Values           Low     High            Parameter

        A3      0 - 6.954 A             0       7.054 A         Unload
                                                                battery
                                                                current
        A4      14.850 - 17.055 V       14.850  17.055 V        End charge
                                                                battery
                                                                threshold
        A5      12.089 - 16.386 V       12.011  16.503 V        Battery
                                                                voltage
        A6      0.859 - 20.539 W        0.859   20.539 W        VHF PA
                                                                output power
        A7      25.982 - 26.960 V       25.004  27.938 V        Primary bus
                                                                voltage
        A8      0 - 1.412 A             0       1.466 A         VHF PA
                                                                current
                                                                (10V)
        A9      0 - 1.412 A             0       1.466 A         VHF  PA
                                                                current
                                                                (26V)
        A11     0.195 - 4.688 V         0.039   4.883 V         RSSI voltage


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                                                                TC channel
        A13     0.055 - 2.002 A         0.043   2.098 A         Primary bus
                                                                current
        A15     9.668 - 26.895 V        9.141   27.949 V        First VHF PA
                                                                voltage
        A17     0.705 - 2.596 A         0.504   2.697 A         Solar
                                                                generator
                                                                current
        A18     0.050 - 0.760 A         0.030   0.915 A         Dc-dc
                                                                converter
                                                                input
                                                                current
        A19     0.102 - 1.801 A         0.050   2.206 A         Shunt
                                                                regulator
                                                                current
        A21     0.072 - 0.721 A         0.072   0.721 A         Battery load
                                                                current
        A22     7.227 - 31.563 .xC      6.680   31.836 .xC      Battery
                                                                temperature
        A23     -70.734 - 9.656 .xC     -80.688 19.609 .xC      Solar
                                                                generator #1
                                                                temperature
        A24     -69.969 - 9.656 .xC     -79.922 20.375 .xC      Solar
                                                                generator #5
                                                                temperature
        A38     5.502 - 7.401 V         5.406   7.497 V         Fifth
                                                                battery
                                                                element
                                                                voltage
        A42     -19.672 - 40.125 .xC    -21.016 40.797 .xC      Plateau
                                                                temperature
        A44     -19.672 - 40.125 .xC    -21.016 40.797 .xC      Shunt
                                                                regulator
                                                                temperature
        A46     -30.422 - 30.047 .xC    -31.766 40.125 .xC      Solar
                                                                generator #3
                                                                temperature
        A48     -19.672 - 40.125 .xC    -21.016 40.797 .xC      Electro gate
                                                                5-6
                                                                temperature
        A53     3.984 - 190.313 Bars    1.641   199.688         Nitrogen
                                                                tank
                                                                pressure
        A54     -17.988 - 41.809 .xC    -19.332 42.481 .xC      VHF PA


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                                                                temperature
        A55     -19.672 - 40.125 .xC    -21.016 40.797 .xC      Nitrogen
                                                                tank #4
                                                                temperature
        A58     0.195 - 4.688 V         0.039   4.883 V         RSSI voltage
                                                                channel 1
        A60     0.195 - 4.688 V         0.039   4.883 V         RSSI voltage
                                                                channel 2
        A62     0.195 - 4.688 V         0.039   4.883 V         RSSI voltage
                                                                channel 3
        A69     -19.672 - 40.125 .xC    -21.016 40.797 .xC      Nitrogen
                                                                tank #1
                                                                temperature
        A71     0.488 - 0.508 V         0.488   0.508 V         Dosimetre 5
                                                                voltage

        8.3.2 ARSENE Digital status telemetry

         ARSENE packet beacon also transmitted 9 status bytes containing
        status information of some of the modules aboard the vehicle.

         There are first two words STA and STB that give 15 status bits ST1
        to ST16, four words X1 to X4 for message handling and three words
        T1, T2 and T3 representing counters.

         The next table give the significance of bits ST1-ST16.

                                                         SIGNIFICANCE
         WORD    Bit     MODULE                  State 1         State 0

         STA     ST1     TNC 1                   On              Off
         STA     ST2     TNC 2                   On              Off
         STA     ST3     TNC 3                   On              Off
         STA     ST4     VHF transmission        CIM TLM         Packet
         STA     ST5     VHF power               Low             Normal
         STA     ST6     Experim. power supply   On              Off
         STA     ST7
         STA     ST8     Squelch                 Off             On

         STB     ST9     Battery regulator       On              Off
         STB     ST10    OK to load battery      Yes             No
         STB     ST11    Battery loading mode    Normal       Housekeeping
         STB     ST12    Packet transponder      On              Off
         STB     ST13    Mode B or S             B packet        S Linear


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         STB     ST14    10 Volts power supply   On              Off
         STB     ST15    High pressure gates     Open            Closed
         STB     ST16    ACS power supply        On              Off

         Here is an example of the packet beacon telemetry format that had
        been received at F6BVP during a test of the ARSENE packet
        transponder performed during winter 1991 to validate the circuits
        designed by Gerard F6FAO and to verify the software coded by Antoine
        F6DWJ.

         ARSENE-1>MESURE-3:
         1 1X10 2A53 3A69 4A38 5X20 6A54 7A22
         2 1X30 2A55 3A71 4A40 5X40 6A56 7A24
         3 1STA 2A90 3A17 4A42 5STB 6A58 7A18
         4 1A30 2A11 3A19 4A44 5A40 6A60 7T10
         ARSENE-1>MESURE-3:
         5 1A50 2A13 3A21 4A46 5A60 6A62 7T20
         6 1A70 2A15 3A23 4A48 5A80 6A64 7T30
         ARSENE
         ARSENE

        8.4 AO-21 (RM-1)

         AO-21 (AO-21) was launched in February 1991 from the North
        Cosmodrome at Plesetsk. The orbit is a slightly elliptical polar
        orbit with an apogee of 1000 km at an inclination of 83 degrees. The
        period of the orbit will be 105 minutes.

         AO-21 was the first international OSCAR in which radio amateurs
        from the Soviet Union took part. RM1 stands for "RADIO M-1", which
        is the official prelaunch name of AO-21, emphasizes that the
        spacecraft was built by, and for, Radio Amateurs around the world.

         The idea of a joint effort between the two groups, one in the USSR
        and the second, in Germany first appeared in the spring 1989. The
        discussions about what and how things had to be done lasted till the
        meeting of the representatives of the two groups in Surrey in July
        1989 when the preliminary agreement about the cooperation was
        signed. The final version of the cooperation agreement was later
        signed in the autumn of 1989 after much of the work had been
        completed.

         According to the mutual agreement, Amsat-U-Orbita developed and
        made the linear transponder, command radio link, telemetry system,


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        power supply system and decided all the problems with the official
        and other government organizations about the location of the
        equipment and launching.

         The RUDAK group of AMSAT-DL developed and built the digital part,
        called RUDAK-2 which contains a digipeater and an AX.25 mailbox. It
        also provides other possibilities for experiments in transmitting of
        information using modern digital methods. It also contains its own
        RF input and output circuits.

         The ground command station was developed by the Amsat-U-Orbita and
        Amsat-U-Sputnik groups. The Rudak group however provided some
        special digital part for it.

         During the launch and orbital test period ground, the command
        stations were UC1CWA situated in Molodechno and RK3KP in Moscow. The
        ground command stations for Rudak-2 are situated near Munich at
        DK1YQ and near Hanover, at DB2OS. The final agreement was signed on
        behalf of Amsat-U-Orbita by the technical director of project
        "RADIO-M1" - V.Chepyzhenko, RC2CA; and on behalf of AMSAT-DL, by
        their president, K. Meinzer, DJ4ZC. The Project Manager for the
        RUDAK-2 is Hanspeter Kuhlen, DK1YQ. The coordinators for the project
        are P. Guelzow, DB2OS and L. Labutin, UA3CR.

         AO-21 was an attached secondary payload (Piggy-back) aboard a USSR
        geological research satellite which provides a Mode B communications
        transponder in low earth orbit as well as an orbiting experimental
        digital communications capacity.

          The AO-21 Specifications are as listed below.

         Dimension and shape: Cylinder of height about 4 meters and
                                 diameter 1.8 meters
         System configuration: Professional geological research equipment,
             telemetry system, command link equipment, transponders and
             power supply, thermal control. Amateur linear and digital
             transponders, telemetry system, command link equipment, power
             supply.
         Attitude control: Satellite attitude will be maintained using a
             gravity gradient approach in the form of a rod 9 meters long
             pointing away from the earth.
         Planned service life: 3 years.

         Two sets of the equipment are installed aboard the satellite:


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        Linear transponder #1 is Mode B and contains the RUDAK-2 and other
        subsystems, while Linear transponder #2 mode B with subsystems The
        Primary transponder is Linear Transponder #1, the second one is a
        spare which can be put into operation in the event of a failure of
        the primary system. Mode B in low earth orbit provides a very good
        communications link as anyone who worked AO-7 Mode B will testify.

         The Transponder RF Frequency Assignments and Beacon Data for the
        Primary Payloads are shown in Table 8.4.1, and those for the Backup
        payload in Table 8.4-2. The 1100 bps is not a misprint, it is real.
        Apparently this data rate is used by a popular PC tape cassette
        interface in the Soviet Union. Because this PC is simple and cheap
        for the Hams in the USSR, the AMSAT-U-Orbita team decided to use it
        on this spacecraft, much in a similar manner to the use of reversed
        AFSK tones in UO-2 due to the wide availability of a popular
        interface for those tones in the United Kingdom. It is unclear as of
        the time of writing this, if the telemetry is HDLC or some
        proprietary synchronous PSK such as the 400 baud AO-13 downlink. As
        such you may not be able to copy this telemetry.

                           Table 8.4-1 Primary Payload

        Beacons and telemetry #1

        CW telemetry 8 channels  145.822 MHz 0.2 Watts
        Digital telemetry        30 channels 145.952 MHz 0.4 Watts
                                 1100 bps,BPSK/FM, deviation 2kHz
        Digital telemetry
        Rudak-2                  145.983 MHz 3.0 Watts
                                 BPSK 1200 bps AX.25 (like F-O 20)
        Transponders #1

        Linear transponder:      inversely heterodyned translator
        Uplink passband          435.102 to 435.022 MHz
        Downlink passband        145.852 to 145.932 MHz
        Transmitter output max. 10 Watts
        Bandwith (3db)           80 kHz
        Uplink EIRP required about 100 Watts

        Digital transponder Rudak-2: digipeater and store&forward packet
        communication (AX.25), telecommunications experiment with digital
        signal processing up to nearly 20 kHz, 1 MByte RAM disc, four
        separate uplink channels.



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        Uplink frequencies:

             RX-1  435.016 MHz 1200bps,FSK,NRZIC/Biphase-M
             RX-2  435.155 MHz (AFC) 2400 bps,BPSK, Biphase-S
             RX-3a 435.193 MHz (AFC) 4800 bps,RSM
             RX-3b 435.193 MHz (AFC) 9600 bps,RSM
             RX-4  435.041 MHz (digital AFC) RX for RTX-DSP

        Downlink frequency: 145.983 MHz 3 Watts

        The downlink can be switched to the following operating modes:

        Mode 1: 1200 bps, BPSK, NRZI,(NRZ-S) (like FO-20)
        Mode 2: 400 bps, BPSK, Biphase-S (Like AO-13 beacon)
        Mode 3: 2400 bps, BPSK, Biphase-S
        Mode 4: 4800 bps, RSM, NRZIC (Biphase-M) (like 4800 bps uplink)
        Mode 5: 9600  bps, RSM, NRZI (NRZ-S) +Scrambler (like 9600 bps
                uplink)
        Mode 6: CW keying (only for special events)
        Mode 7: FSK (F1 or F2B),e.g. RTTY, SSTV, FAX, etc.(for special
                events)
        Mode 8: FM modulated by D/A signals from DSP-RISC processor (speech)

                         Table 8.4-2 Secondary Payload

        Beacons and Telemetry #2

        CW telemetry 8 channels          145.948 MHz 0.2 Watts
        Digital telemetry 30 channels    145.838 MHz 0.4 Watts 1100 bps,
                                         BPSK/FM, deviation 2kHz
        Digital telemetry  30 channels   145.800 MHz 2.0 Watts 1100 bps
                                         BPSK/FM, deviation 2kHz

        Transponder #2

        Linear transponder:      inversely heterodyned translator
        Uplink passband          435.123 to 435.043 MHz
        Downlink frequencies     145.866 to 145.946 MHz
        Transmitter output max.  10 Watt max.
        Bandwith (3db)           80 kHz
        Uplink EIRP required about 100 Watts

         The spacecraft uses two antennas. The 435 MHz receiving antenna
        which is shared by the analog and digital modes is a Helix with up


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        to +3 db gain using Right Hand circular Polarization. The 145 MHz
        transmitting antenna is a Half wave dipole. AO-21 draws up to 100
        Watts from the main spacecraft's power supply system. The Primary
        RM-1 payload including the RUDAK draw up to 47 Watts, the secondary
        payload draws up to 40 Watts. The Primary AO-21 payload including
        the RUDAK weighs approximately 28 kg, the secondary payload weighs
        approximately 22 kg. Both payloads are about 480x400x300 mm^3.

         The CW telemetry started up as soon as the combined spacecraft
        separated from the launch vehicle and was powered by main satellite
        power system. A CW Morse-Code telemetry frame consists of the call
        RS14 and 8 channels of four digits in the following format:

         RS14 S0AB=S1AB=S2AB=S3AB=S4AB=S5AB=S6AB=S7AB

         Channels 0 to 6 contain analog telemetry data. Channel 7 contains
        engineering calibration parameters.

         The first digit (S) identifies which system the telemetry is from.
        A prefix of 7 identifies a general status, a prefix of 5 identifies
        a command status. The second digit (0 to 7) are the numbers of the
        line (channel). The remaining digits (A and B) are the analog
        telemetry data which can be decoded according to the equations shown
        in Table 8.4-3.

                Table 8.4-3 AO-21 CW Telemetry decoding parameters

                Channel        Parameter                Formula   Unit

                 0        Transponder power output      0.05*N    Watts
                 1        Transponder PA Temperature    N         Deg. C
                 2         +24 V Regulated              N         Volt
                 3         +16 V Regulated              N         Volt
                 4         +9  V Regulated              N         Volt
                 5         +24 V Regulated              N         Volt
                 6        Inside Temperature            N         Deg. C
                 7        Engineering Value             N         *


         A typical frame such as

         "RS14=7080=7137=7224=7316=7409=5524=5032=57PPRS14"

        may be decoded as shown below.


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                         RS14
                         7080 - 4 Watts   - general
                         7137 - 37 Deg. C - general
                         7224 - 24 Volts  - general
                         7316 - 16 Volts  - general
                         7409 - 9 Volts   - general
                         5524 - 24 Volts  - command
                         5032 - 32 Deg. C - command
                         57PP             - command (transponder #1)

                Examples of other frames copied and edited by G3ZCZ/W3 are

         28-Feb-91 01:40 RS14=7032=7121=7224=7316=7410=7500=7600=77PP
         01-Mar-91 02:19 RS14=7028=7121=7224=7316=7410=7500=7600=77PP

         The "PP" at the end of the frame identifies the telemetry as having
        come from transponder #1. Transponder #2 identifies its telemetry
        with the "PPPP" sequence.

         The AO-21 Digital PSK telemetry consists of 30 parameters
        monitoring on-board conditions and 2 calibration verification
        points. If you intend to receive, decode and display the digital
        telemetry you will need an FM receiver, a TNC, a PSK modem, and a
        computer or terminal. Even then you may not be able to decode the
        data since it may not be downlinked in HDLC format. The decoding
        equations for the digital telemetry are shown in Table 8.4-4. The
        raw digital telemetry is expected to show up on your screen in the
        format shown in Table 8.4-5.

          Table 8.4-4 Decoding Equations for AO-21 Digital Telemetry
                                 (Version 26-Dec-90)

          Line Parameter                  Formula     Unit  Hex-Format-Line

           1   "Zero" of the comparator      0C         N/A      0000
           2   Reference voltage             6D         N/A      0010
           3   Transponder #1 HF output pwr  0.2N^2    Watt      0020
           4   Transponder #1 PA temperature 0.8*N     Deg. C    0030
           5   DC/DC converter temperature   0.8*N     Deg. C    0040
           6   +14 V Regulated               10*N      Volt      0050
           7   +24 V Regulated               10*N      Volt      0060
           8   +16 V Regulated               10*N      Volt      0070
           9   +12 V Regulated               10*N      Volt      0080


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           10  +9 V Regulated                10*N      Volt      0090
           11  +7.5 V Regulated              10*N      Volt      00A0
           12  +5 V Regulated                10*N      Volt      00B0
           13  +9 V Regulated (linear)       10*N      Volt      00C0
           14  +9 V Regulated (digital)      10*N      Volt      00D0
           15  Service                          N      *         00E0
           16  Service                          N      *         00F0
           17  Transponder #2 HF output pwr  0.2*N^2   Watt      0100
           18  Transponder #2 PA temperature 0.8*N     Deg. C    0110
           19  +24 V Regulated               10*N      Volt      0120
           20  +16 V Regulated               10*N      Volt      0130
           21  +10 V Regulated               10*N      Volt      0140
           22  +9 V Regulated                10*N      Volt      0150
           23  +7.5 V Regulated              10*N      Volt      0160
           24  Status command link           1         *         0170
           25  Status command link           2         *         0180
           26  Status command link                     *         0190
           27  Status command link                     *         01A0
           28  RPC +5V for Rudak-1           2.47*N    Volt      01B0
           29  RPC +5V for Rudak-RTX         2.47*N    Volt      01C0
           30  RPC +5V for Ramdisk           2.47*N    Volt      01D0
           31  RPC +14V total supply current 627-289*N mA        01E0
           32  RPC module temperature        56.7*N-49.5 Deg. C  01F0

        Note: RPC - Rudak Power Conditioner. The Service and command link
        channels are reserved for use by the ground control team.

          Table 8.4-5 Expected Format of Raw AO-21 PSK Telemetry

           0000 0C E6 0C E6 0C E6 0C E6 0C E6 0C E6 0C E6 0C E6
           0010 6D E6 6D E6 6D E6 6D E6 6D E6 6D E6 6D E6 6D E6
           0020 i E6 i E6 i E6 i E6 i E6 i E6 i E6 i E6
           ....................................................
           01F0 j E6 j E6 j E6 j E6 j E6 j E6 j E6 j E6

        i...j - the value of the parameter in the hex format, repeated 8
        times E6 - separation

         The RUDAK system is a message store-and-forward package. Its
        downlink is not expected to contain any telemetry. An example of
        some RUDAK signals copied by W3/G3ZCZ a few days after launch is
        shown in Table 8.4-6.




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                Table 8.4-6 Example of AO-21 RUDAK Signals.

                26-Feb-91  02:31:36  RUDAK*>BEACON:
                * RUDAK-II / AMSAT OSCAR 21/RM1
                * Up: 435.016MHz (1200)
                *     435.155MHz (2400)
                * Mailbox=RUDAK Mheard=RUDAK-1
                26-Feb-91  02:32:37  RUDAK*>BEACON:
                RUDAK-Telemetry (91-02-25 23:03:00):
                Used stack entries: 0
                Uplink Carrier Detect (during last minute): 0%
                26-Feb-91  02:33:36  RUDAK*>BEACON:
                * RUDAK-II / AMSAT OSCAR 21/RM1
                * Up: 435.016MHz (1200)
                *     435.155MHz (2400)
                * Mailbox=RUDAK Mheard=RUDAK-1
                26-Feb-91  02:34:37  RUDAK*>BEACON:
                RUDAK-Telemetry (91-02-25 23:05:00):
                Used stack entries: 0
                Uplink Carrier Detect (during last minute): 0%
                26-Feb-91  02:35:09  RUDAK,*>WB5BZE (UA)
                26-Feb-91  02:35:11  RUDAK*>WB5BZE:
                +-------------------------------------------------------+
                +  Welcome to the RUDAK II Bulletin Board System V0.04  +
                +-----------
                26-Feb-91  02:35:13  RUDAK*>WB5BZE:
                --------------------------------------------+
                Logged in at 91-02-25 23:05:33,  1 User
                This is a preliminary release.
                Please rep
                26-Feb-91  02:35:15  RUDAK*>WB5BZE:
                ort deficiencies to DL2MDL.
                73 de AMSAT-UA/AMSAT-DL/RUDAK-Group.
                Enter H for help.
                WB5BZE de RUDAK>
                26-Feb-91  02:35:36  RUDAK*>BEACON:
                * RUDAK-II / AMSAT OSCAR 21/RM1
                * Up: 435.016MHz (1200)
                *     435.155MHz (2400)
                * Mailbox=RUDAK Mheard=RUDAK-1
                26-Feb-91  02:35:51  RUDAK*>WB5BZE [D]
                26-Feb-91  02:35:56  RUDAK*>WB5BZE [D]
                26-Feb-91  02:36:32  KF4WQ>RUDAK*>KF4WQ [C]
                26-Feb-91  02:36:37  RUDAK*>BEACON:


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                RUDAK-Telemetry (91-02-25 23:07:00):
                Used stack entries: 0
                Uplink Carrier Detect (during last minute): 0%
                26-Feb-91  02:37:35  RUDAK*>WB5BZE (UA)

         The AO-21 Packet Telemetry is formatted for display in the
        spacecraft and downlinked as ASCII packets. Typical packets are
        shown below.

           18-Jun-94  20:38:18  RUDAK2*>BEACON [UI]:
           ++ Hi, this is the RUDAK-II experiment on AMSAT OSCAR 21 ++
           18-Jun-94  20:38:21  RUDAK2*>TLM-2 [UI]:
           5V-RAM: 4.97 V    3-RNG    : off      AGC
            total current    4-soft:  0.2 V    RX3: 142   temperature
           14V-I :  307 mA                     RX4: 207    21.6 deg C
           chksum: 0   upcnt: 0   stack: 2   noint: 0
           18-Jun-94  20:38:23  RUDAK2*>TLM-3 [UI]:
           RAMDISK:
           wash sectors memory errors audio sectors picture sectors
           start: 3100  single: 215    start: 165     start: 3100
           end  : 4095  multi : 0      end  : 2412    end  : 3452
           ptr  : 3785           sample freq: 8000   chksum: -19652 (-19652)
           18-Jun-94  20:38:24  RUDAK2*>BEACON [UI]:
           RUDAK-II Schedule: (down 145.987, up 435.016)
           min/10  Beacon Mode
            0..8   FM Repeater
              9    AFSK TLM

           The same information seen without the headers is shown below.

           5V-RAM: 4.97 V    3-RNG    : off      AGC
            total current    4-soft:  0.2 V    RX3: 142   temperature
           14V-I :  307 mA                     RX4: 207    21.6 deg C
           chksum: 0   upcnt: 0   stack: 2   noint: 0
           RAMDISK:
           wash sectors memory errors audio sectors picture sectors
           start: 3100  single: 215    start: 165     start: 3100
           end  : 4095  multi : 0      end  : 2412    end  : 3452
           ptr  : 3785           sample freq: 8000   chksum: -19652 (-19652)

           RUDAK-II Schedule: (down 145.987, up 435.016)
           min/10  Beacon Mode
            0..8   FM Repeater
              9    AFSK TLM


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        9.0 File formats

         This section contains details of the contents of the different
        files used by WHATS-UP.

        9.1 Configuration File (WHATS-UP.SYS)

         The contents of the Configuration file (WHATS-UP.SYS) are as
        follows:

         1 Your callsign (e.g. G3ZCZ)
         2 Default spacecraft configuration file (e.g. Dove)
         3 station latitude (e.g. 35.00)
         4 station longitude (e.g. 74.00)
         5 station altitude (e.g. 100)
         6 station minimum antenna elevation for acquisition (e.g. 0)
         7 default Kepler file (e.g. whats-up.TLE)
         8 UTC offset (e.g. EST = 5)
         9 default directory path (e.g. C:)
         10 default extracted data file (e.g. whats-up.txt)
         11 default file name with list of telemetry parameters to extract
           file (e.g. ARRAYS)
         12 TNC Type (e.g. PK-232)
         13 PC serial port to TNC (e.g. 1)
         14 PC serial TNC port baud rate (e.g. 1200)
         15 PC Serial TNC port data bits (e.g. 8)
         16 PC Serial TNC port Stop bits (e.g. 1)
         17 PC Serial TNC port parity (e.g. N)
         18 status (top) window color (e.g. 79)
         19 Incoming window color (e.g. 14)
         20 outgoing window color (e.g. 30)
         21 prompt window color (e.g. 15)
         22 alarm window color (e.g. 15)
         23 bottom window color (e.g. 79)
         24 Emphasis color (e.g. 14)
         25 option color (e.g. 78)
         26 parameter changed color (e.g. 95)
         27 parameter limit exceeded color (e.g. 14)
         28 Orbit element window color
         29 Orbit element window Orbit element window In range color
         30 Orbit element window early warning color
         31 Orbit element window next one up color
         32 Logbook window color
         33 SAREX call color in status window


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         34 Active color
         35 Post pass color in orbit element window
         36 Orbit alert dit time
         37 Orbit alert note
         38 Flag Sound
         39 Doppler display Flag
         40 DSP-1200 Modem CW command
         41 DSP-1200 Modem 1200 ASCII command
         42 DSP-1200 Modem 1200 PSK command
         43 DSP-1200 Modem 400 PSK command
         44 DSP-1200 Modem 9600 FM command
         45 DSP-1200 Modem 1200 FM command
         46 Logbook path and name (.DBF may be left out)
         47 QSO Logging Flag
         48 Minimum angle of the sun for darkness at your QTH
         49 TNC stream switch character, default '|'
         50 The next few lines link the spacecraft configuration files.
         51 The * that follows denotes the last line of SC ID data.
         52 CW Memory contents: - The next ten lines contain the cw memory
           data.
         54 The * marker line
         55 The remaining lines contain TNC configuration parameters.

         You must configure WHATS-UP before you try any Real Time activity.

         The contents of the configuration file are described below.

        9.1.1 Your callsign

         This item is the callsign displayed at the top of the screen and
        appended to the capture files when capture-to-disk is turned on.

        9.1.2 Default spacecraft Name

         This item is the default spacecraft name (e.g. Dove). WHATS-UP adds
        the ".SYS" to the end of the name (e.g. DOVE.CNF) and loads that
        configuration file at start up.

        9.1.3 Station Latitude

         This item is your station latitude (e.g. 35.00). In the southern
        hemisphere, enter a negative number.




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        9.1.4 Station longitude

         This item is your station longitude in degrees WEST of Greenwich.
        (e.g. 74.00)

        9.1.5 Station Altitude

         This item is the altitude of your station antenna above sea level
        in Meters. (e.g. 100)

        9.1.6 Station minimum antenna elevation for acquisition

         This item is the minimum angle of elevation of your antennas at
        which you can acquire a signal. If you are on top of a hill or tall
        building the angle my be less than 0, if you are in a valley, it may
        be greater, such as 5 degrees.

        9.1.7 Default Kepler file

         This item is the default file name that contains the orbit element
        data used when the program is first turned on (e.g. whats-up.TLE).

        9.1.8 UTC offset

         This item is the time difference (in hours) between the local time
        in your PC and GMT or Universal Coordinated Time (UTC). WHATS-UP
        always displays UTC time. (e.g. EST = 5)

        9.1.9 Default directory path (e.g. C:)

         This item is the directory path  (e.g. C:\TLM) for the spacecraft
        capture-to-disk (YYMMDD.S/C), spacecraft configuration (*.CNF) and
        spacecraft operations schedule files (*.OPS).

        9.1.10 Default extracted data file

         This item is the name of the file to which data which is extracted
        from a playback file will be written to in a comma delimited format
        so that the data can be imported into a spreadsheet package for
        further analysis (e.g. whats-up.txt).

        9.1.11 Default file name with list of telemetry parameters to
        extract file



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         This item is the name of the file containing the channel numbers to
        extract from a playback file for further analysis (e.g. ARRAYS)

        9.1.12 TNC Type

         This item is the type of TNC or Multi-mode controller you are
        using.

        9.1.13 Serial port to TNC

         This item is the Communications port number between the TNC and the
        PC (e.g. 1). If you set it to 0, WHATS-UP will never try to access
        the TNC.

        9.1.14 PC TNC Serial baud rate

         This item is the baud rate used between the TNC and the PC (e.g.
        1200).

        9.1.15 PC TNC port data bits

         This item is the number of data bits used between the TNC and the
        PC (e.g. 8).

        9.1.16 PC TNC port Stop bits

         This item is the number of stop bits used between the TNC and the
        PC (e.g. 1).

        9.1.17 PC TNC Port parity bits

         This item is the parity setting used between the TNC and the PC.
        The letters to use are defined as

         N No parity, O Odd, E Even, M Mark, S Space.

         The following items are the color values used for different windows
        or messages.

        9.1.18 Status (top) window color (e.g. 79)

        9.1.19 Incoming window color (e.g. 14)

        9.1.20 Outgoing window color (e.g. 30)


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        9.1.21 Prompt window color (e.g. 15)

        9.1.22 Alarm window color (e.g. 15)

        9.1.23 Bottom window color (e.g. 79)

        9.1.24 Emphasis color (e.g. 14)

        9.1.25 Option color (e.g. 78)

        9.1.26 Parameter changed color (e.g. 95)

        9.1.27 Parameter limit exceeded color (e.g. 14)

        9.1.28 Orbit element window color

        9.1.29 Orbit element window In range color

        9.1.30 Orbit element window early warning color

        9.1.31 Orbit element window next one up color

        9.1.32 Logbook window color

        9.1.33 SAREX call display color in Status window

        9.1.34 Active color

        9.1.35 Orbit element Post pass color

        9.1.36 Orbit alert dit time

         This item is the speed of the morse code annunciator used to alert
        you of satellite AOS, EWT and LOS.

        9.1.37 Orbit alert note

         This item is the tone of the morse code annunciator used to alert
        you of satellite AOS, EWT and LOS.

        9.1.38 Flag Sound

         This item controls the sounds coming from the PC. A


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             1 is on,
             0 is off.

        9.1.39 Doppler display Flag

         This item determines the type of Doppler display as follows:-

             0 display beacon frequency,
             1 display Doppler shift.

        9.1.40 TNC Command to select modem for CW


        9.1.41 TNC Command to select modem for UoSAT ASCII 1200 baud

        9.1.42 TNC Command to select modem for 1200 baud PSK

        9.1.43 TNC Command to select modem for 400 baud AO-13 PSK

        9.1.44 TNC Command to select modem for 9600 baud packet

        9.1.45 TNC Command to select modem for 1200 baud FM AFSK

        9.1.46 Logbook file

         This item is the default file name for the logbook (e.g. vhf.dbf).

        9.1.47 QSO Logging flag

         This item is the flag that determines if acquisition of signal is
        logged. A:

             1 means log,
             0 means don't log.

        9.1.48 Minimum angle of the sun for darkness at your QTH

         This item sets the value for viewing of satellites. To see a
        spacecraft, the spacecraft must be in sunlight and the ground viewer
        must be in darkness. This parameter lets you adjust the apparent sun
        angle for darkness at your location. Note while some spacecraft may
        be in sunlight, and you may be in darkness, the spacecraft may not
        be bright enough to be visible with the naked eye. MIR and the space
        shuttle are bright enough.


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        9.1.49 TNC stream switch character, default '|'

        9.1.50 Spacecraft Configuration File Linkages

         The next few lines contain the information which WHATS-UP uses to
        link the spacecraft configuration files to the Keplerian elements
        for orbit determination and automatic selection of spacecraft at AOS
        time. There should be NO SPACE characters before or between the
        commas, in the first two data elements. The lines contain data as
        shown below.

          UO-11,UOSAT11.CNF,     0
          AO-13,OSCAR13Z.CNF,    0
          AO-16,PACSAT.CNF,      0
          DO-17,DOVE.CNF,        1
          WO-18,WEBER.CNF,       0
          LO-19,LUSAT.CNF,       2
          FO-20,FUJI.CNF,        0

         The first item is the Keplerian element identifier for the
        spacecraft as used in the orbit element files.

         The second item is the FULL configuration file name for the
        spacecraft.

         The third item is the automatic AOS selection flag as itemized
        below.

         '0', automatic selection is inhibited.
         '1', WHATS-UP selects that spacecraft configuration file at EWT
              time (if it is not selected at that time), and tunes the radio
              to the beacon frequency + offset defined in that file.
         '2', WHATS-UP selects that spacecraft configuration file at AOS
              time (if it is not selected at that time), and tunes the radio
              to the beacon frequency + offset defined in that file.

        9.1.51 Marker and Comment line

         This line must be present and begin with an '*' character. It
        signals WHATS-UP that the spacecraft default parameters have been
        read.




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        9.1.52 CW Memory contents

        The next ten lines contain the cw memory data

        9.1.53 The marker line

         This line must be present and begin with an '*' character.

        9.1.54 TNC configuration commands

        The remaining lines are commands sent to the PK232 when you
        configure the TNC. Note to avoid lock ups FLOW and XFLOW MUST be
        OFF. Typical commands are as follows:-

          HEAD ON
          ECHO OFF
          DAYSTAMP ON
          MONITOR 6
          MSTAMP ON
          FLOW OFF
          XFLOW OFF
          MFILTER None

        9.2 Spacecraft Parameter Files

         You need a Different spacecraft parameter file for each spacecraft.
        Spacecraft parameter files are named by the spacecraft and given the
        extension '.CNF'. Examples are 'DOVE.CNF' and 'Fuji20.CNF'. These
        files determine how the individual channels are decoded, and where,
        in which screen page, and in which color the decoded data are
        displayed. Some of the items are unique to WHATS-UP and some to the
        particular spacecraft.

         The entries in the file are:

         1 Spacecraft ID
         2 Spacecraft Suffix
         3 Beacon Frequency
         4 Doppler Measurement File
         5 Spacecraft Identification in Keplerian Element File
         6 Doppler Measurement Sample Interval
         7 Initial Frequency Offset
         8 Autotrack flag
         9 Modulation


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         10 Data Type
         11 Receiver Type
         12 Receiver Address
         13 PC Serial port to Radio
         14 PC Radio port Serial baud rate
         15 PC Radio port data bits
         16 PC TNC port Stop bits
         17 PC Radio Port parity bits
         18 Post pass delay
         19 Station minimum usable pass time
         20 Early warning time
         21 SAREX/Mir Callsign
         22 SAREX/Mir Header Delay
         23 SAREX/Mir Attack Mode
         24 SAREX/Mir Beacon Text
         25 LPT parallel port radio memory parameters
         26 Selected or default display page number
         27 MET Start Time
         28 Page Definitions
         29 Telemetry Parameter Configuration
         30 Digital Telemetry Status Channels
         31 Packet/Link Parameters

         The contents of each line in the SPACECRAFT.CNF file are as
        described below.

        9.2.1 Spacecraft ID

         This is the callsign of the spacecraft. For example,

         Spacecraft    ID.
         ---------------------
         DO-17         DOVE-1
         FO-20         8J1JBS

        9.2.2 Spacecraft Suffix

         This becomes the filetype for the capture-to-disk files. The
        default suggestions are as shown below.

                                    Spacecraft          Suffix

                                    UoSAT-2             U11
                                    Fuji-OSCAR 12       F12


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                                    AMSAT-OSCAR 13      O13
                                    AMSAT-OSCAR 16      O16
                                    DOVE-OSCAR 17       D17
                                    WEBER-OSCAR 18      W18
                                    LUSAT-OSCAR 19      L19
                                    Fuji-OSCAR 20       F20
                                    AMSAT-OSCAR 21      O21

        9.2.3 Beacon Frequency

         This is the frequency of the spacecraft beacon (in MHz) that you
        are monitoring. It will be displayed in the status window.

        9.2.4 Doppler Measurement File

         This is the default name of the file used to store the Doppler
        frequency measurements.

        9.2.5 Spacecraft Identification in Keplerian Element File

         Examples are as follows.

          UO-11   AO-13     AO-16     DO-17     WO-18     LO-19

        9.2.6 Doppler Measurement Sample Interval

         This is the default sample interval (in seconds) used between
        Doppler frequency measurements.

        9.2.7 Initial Frequency Offset

         This is the default value (in kHz) added to the beacon frequency,
        and output to the Radio Receiver when a particular spacecraft is
        selected. The default value is 5 to tune the radio 5 kHz above the
        beacon. This will allow the signal to slide into lock, whereby the
        TAPR PSK Modem will lock on and follow the frequency for the rest of
        the pass.

        9.2.8 Autotrack flag

         This item tells WHATS-UP if it should allow another AOS to
        interrupt data collection from this spacecraft.

         0 Don't let another AOS to interrupt collection.


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         1 Allow another spacecraft AOS to interrupt collection, namely,
           tune to that spacecraft at its AOS.

        9.2.9 Modulation

         This is the type of modulation to set the Radio to to copy data
        from the spacecraft. Current options are :-

         C CW
         F FM L LSB
         P PSK
         U USB
         D FM Duplex. Use this mode for SAREX. If duplex is selected, then
           the uplink frequency (in MHz) must be added following the D and
           separated by a comma character (i.e. D,144.49).

        9.2.10 Data Type

         This is the type of data downlinked by the spacecraft.

         A ASCII as used by UoSAT-2.
         B BAUDOT as used by AO-13.
         C CW as used by AO-21.
         P Packet as used by DO-17, Fuji-OSCAR 20 and the Microsats.

        9.2.11 Receiver Type

         This is the manufacturer of the radio receiver you are using. This
        version of WHATS-UP supports the:

        Kenwood   series.
        Lpt       line printer parallel port.
        Icom      (not tested).

        9.2.12 Receiver Address

        The assignment is as follows:

        9.2.12.1 Kenwood

        Not used.





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        9.2.12.2 LPT parallel port

         This item defines the printer port as shown below.

          Assignment     Printer Port    PC Assignment
             Bit       Address (Hex)
              1             $0378          LPT1
              2             $0278          LPT2
              3             $03BC          Custom for my laptop

         For example, to use LPT1 as the printer port, set this value to 1.
        You may use different ports for different radios on different bands

        9.2.12.3 Icom

         Set the line to the decimal value of the radio address according to
        the Icom radio manual.

        9.2.13 PC Serial port to Radio

         This item is the Communications port number between the PC and the
        Radio (e.g. 2). If you set it to 0, WHATS-UP will never try to
        access the radio via the serial port. If you select the LPT radio
        option, set this value to 0.

        9.2.14 PC Radio port Serial baud rate

         This item is the baud rate used between the PC and the Radio (e.g.
        4800).

        9.2.15 PC Radio port data bits

         This item is the number of data bits used between the Radio and the
        PC (e.g. 8).

        9.2.16 PC TNC port Stop bits

         This item is the number of stop bits used between the Radio and the
        PC (e.g. 2).

        9.2.17 PC Radio Port parity bits

         This item is the parity setting used between the Radio and the PC.
        The letters to use are defined as


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         N No parity, O Odd, E Even, M Mark, S Space.

        9.2.18 Post pass delay

         This item is the time (in minutes) that WHATS-UP after the computed
        LOS time before returning the radio to the default frequency (e.g.
        2). This delay is to be used in the event that the elements do not
        quite predict the exact times for your system.

        9.2.19 Station minimum usable pass time

         This item is the minimum time in minutes for a usable pass for
        collecting data (e.g. 5).

        9.2.20 Early warning time (EWT)

         This item is the early warning time in minutes you want for notice
        that a spacecraft is about to come up above your local horizon (e.g.
        5).

        9.2.21 SAREX/Mir Callsign

         This item is the callsign to which the automatic beacon/connect
        attempt will be made. if you wish to beacon, then you must set the
        'UNProto' parameter in the TNC to the digipeater callsign. for
        example to beacon via MIR, when MIR is using R0MIR, then set the
        SAREX call to R0MIR, and set the TNC parameter as 'UNP CQ VIA
        R0MIR'.

        9.2.22 SAREX/Mir Header Delay

         This item is the number of packet headers to count before issuing
        the next beacon packet. Try to resist the temptation to set it at a
        low value.

        9.2.23 SAREX/Mir Attack Mode

         This item is the SAREX/MIR Attack mode. Options are to try:

         B - both connect and digipeat
         C - connect to SAREX call
         Q - call CQ via the SAREX call



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        9.2.24 SAREX/Mir Beacon Text

         This item is the text to beacon via the SAREX/MIR. Put your grid
        locator at the beginning of the line for APRS compatibility, i.e.
        [FM19LA]. If you put an * as the first character, WHATS-UP will
        ignore the value in the file.

        9.2.25 LPT parallel port radio memory parameters

         This line contains two items separated by a comma, e.g., 7,23.

         The first item is the memory channel assigned to the spacecraft.
        The second item is the number or total number of memory channels.

         When the file is loaded at EWT or AOS, WHATS-UP will step through
        the radio memories to the selected channel.

         The maximum parameter is required so that when WHATS-UP is scanning
        through the memories, it resets the count to 0 at the correct
        channel.

        9.2.26 Selected or default display page number

         This is the default display page for the Real-time and Playback
        modes, when WHATS-UP is first loaded.

        9.2.27 Page Definitions

         These are the page definitions, with two items on the line. The
        format is PAGE_TITLE, Page_Color, as in the example below.

              SPACECRAFT HOUSEKEEPING, 30

        9.2.28 Telemetry Parameter Configuration

         The next set of items are the Telemetry parameter configurations
        (maximum = 99). You must have at least one of these lines in the
        file. If you want a value to show up in more than one page (other
        than the wild card [0]) you must enter it twice (once per page).
        Typically each row contains 17 items in the format shown below.

        TLM_Channel,   TLM_Segment_ID,     TLM_Description,    TLM_Eqn_Type,
        TLM_Ceof_C,    TLM_Ceof_B,         TLM_Ceof_A,         TLM_Units,
        TLM_Page,      TLM_Row,            TLM_Col,            TLM_Width,


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        TLM_Dec,       TLM_Limit_Check,    TLM_Limit_Low,
        TLM_Limit_High,
        TLM_Negative_Blank.

         Each item is described in the following sections.

         9.2.28.1 TLM_Channel

         This is the channel number of the telemetry data in the frame. The
        DOVE channel number is hexadecimal (e.g. '0F'), Fuji is decimal.
        Each entry must be two digits.

         A special identifying TLM_Channel is defined in WHATS-UP. If the
        value is '99 then the segment identifier and position of the segment
        identifier is defined in tow positions in the line. This special
        channel identifies the type of telemetry frame.

         9.2.28.2 TLM_Segment_ID

         This is the segment identifier as described in Section 9.2.28.99
        below.

         9.2.28.3 TLM_Description

         This item is the text string or description of the telemetry
        channel that will be displayed on the screen page. (e.g. '+Z Array
        Temp.')

         9.2.28.4 TLM_Eqn_Type

         This item tells WHATS-UP the type of equation to use to decode the
        telemetry.

         Type 1 is the general purpose equation used by AMSAT-NA in the
        Microsats.

        Fuji (FO-12 and FO-20) uses two other types of equations (2 and 3).
        They are in the formats of

         Y = D*(N+E), and Y = F*(G-N).

        If you know some algebra you can convert both of Fuji's equations to
        the Format used by AMSAT, but since a computer is involved, why not
        let it do the job. You do however have to convert an equation of the


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        form Y=(N+a)/b.

         AO-13 also needs three more types (4 5 and 6) of equations to
        decode the RTTY Z blocks.

         A type 1 equation in WHATS-UP is a quadratic of the form of

                  Y = A*N^2 + B*N + C, where: N = raw telemetry data value,
                                              A, B, C = Equation
                                              Coefficients; Y, N are decimal
                                              values.

         A type 2 equation in WHATS-UP has the format in the form of

                  Y = B*(A+N) + C  where C, B, A are coefficients; Y, N are
                                              decimal values.

         A type 3 equation in WHATS-UP has the format in the form of
                  Y = B*(A-N) + C  where C, B, A are coefficients; Y, N are
                                              decimal values.

         A type 4 equation in WHATS-UP has the format in the form of
                  Y = B*(N+A)^2 +C  where C,B, A are coefficients; Y, N are
                                              decimal values.

         A type 5 equation in WHATS-UP has the format in the form of
                   Y = B*(A-N)^2 + C  where C, B, A are coefficients; Y, N
                                              are decimal values.

         A type 6 equation in WHATS-UP is a special case. It is the AO-13
                                              (Channel 1C) Spin Rate
                                              equation as specified below.

                           if N > 131 then Y := 479/(N - 109) - 2
                                      else Y := (131 - N) * 0.85 + 20;

         where N is the raw decimal number in Channel 1C and Y is the spin
        rate.

         9.2.28.5 TLM_Ceof_C

         This item is the equation Coefficient C.




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         9.2.28.6 TLM_Ceof_B

         This item is the equation Coefficient B.

         9.2.28.7 TLM_Ceof_A

         This item is the equation Coefficient A.

         9.2.28.8 TLM_Units

         This item is the Units text string (e.g. '.C') in the screen
        display. However if the Tlm_Channel is '99' then this item is the
        segment identifier string.

         9.2.28.9 TLM_Page

         This item is the Display page number. A 0 is a 'wild card' which
        will be displayed on every page.

         9.2.28.10 TLM_Row

         This item is the Display page row. It identifies which row in the
        screen the data element will be displayed.

         9.2.28.11 TLM_Col

         This item is the Display page column. It identifies which column in
        the screen the data item will be displayed.

         9.2.28.12 TLM_Width

         This item is the Display width for Engineering Units. It tells
        WHATS-UP how many characters wide the display is to be. You can set
        it to any value you want. For example, you can display a voltage as
        '1.3' or '1.28567'. Before you widen the display too much, remember
        the sampling accuracy of the analog-to-digital converter in the
        spacecraft.

         9.2.28.13 TLM_Dec

         This item defines the number of digits after the decimal point in
        the display.




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         9.2.28.14 TLM_Limit_Check

         This item tells WHATS-UP to perform limit checking on the telemetry
        channel. It may have several values as

         described below.

         0 = do nothing,
         1 = check below low limit,
         2 = check above high limit,
         3 = check for EITHER [below low limit] or [above high limit]).

         9.2.28.15 TLM_Limit_Low

         This item is the Low limit value (e.g. -4.00).

         9.2.28.16 TLM_Limit_High

         This item is the High limit value (e.g. +10.6).

         9.2.28.17 TLM_Negative_Blank

         This item is a 1 if you want computed negative values to be
        displayed as a zero. Use this for example, in Solar Cell Voltage
        computations, when negative values are produced by the equation
        supplied even though the negative values are not real. The negative
        values are produced because the equation used to convert the data is
        not valid at low or zero values of light.

         A line with an '*' as the first character terminates this section.

         9.2.28.99 The Telemetry Identifier Line

         The Telemetry identifier line has the same format as a regular
        line, but contains different parameters as follows:

         9.2.28.99.1 The Line Identifier

         This item has to be '99' to identify the telemetry identifier line.

         9.2.28.99.2 The Segment Identifier

         This is used when the spacecraft transmits telemetry in more than
        one segment. It contains the segment identifier showing which


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        segment the channel is down linked in.

         9.2.28.99.3 Spare/Not Used

         9.2.28.99.4 Location of Segment Identifier in Line

         This item contains the location of the segment identifier in the
        first line of the telemetry data.

         9.2.28.99.5 Spare/Not Used
         9.2.28.99.6 Spare/Not Used
         9.2.28.99.7 Spare/Not Used

         9.2.28.99.8 Segment Identifier String

         This item is the segment identifier string as follows.

          9.2.28.99.82.1 Fuji

          The Fuji frame contains one real time segment (Segment 1) in a
        frame addressed as 8J1JBS>BEACON. A typical frame is shown below.

              19-Apr-90 17:14:34 8J1JBS*>BEACON:
              JAS1b RA 90/04/19 17:13:58
              609 430 687 676 744 837 845 829 498 681
              617 001 505 516 526 524 526 523 654 000
              683 675 686 695 999 643 875 471 099 000
              110 111 000 000 111 100 001 111 111 000

          The segment identifier is in the seventh and eighth characters of
        the first line of the data. A segment identifier of that position
        identifies the second segment. The segment identifier is the 'RA'
        located on the first line of the data just after the JAS1b where the
        'R' in 'RA' is the seventh character in the line.

          Any telemetry frame addressed to BEACON received without that
        segment identifier is assumed by WHATS-UP to be Segment 2.

          9.2.28.99.8.2 DOVE

          DOVE transmits telemetry in two frames each addressed as DOVE-
        1>TLM. The Microsat ASCII frame thus contains two segments. Two
        typical segments of DOVE telemetry are shown below.



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         DOVE-1>TLM [01/29/90 22:08:46]:
         00:59 01:59 02:86 03:30 04:58 05:58 06:6D 07:45 08:6C 09:66 0A:A1
         0B:D9 0C:E8 0D:D8 0E:01 0F:23 10:CC 11:A8 12:00 13:01 14:A8 15:94
         16:96 17:94 18:95 19:96 1A:93 1B:90 1C:9A 1D:98 1E:23 1F:5E 20:BC

         DOVE-1>TLM [01/29/90 22:08:47]:
         21:98 22:7B 23:24 24:21 25:2E 26:00 27:00 28:00 29:00 2A:00 2B:00
         2C:00 2D:29 2E:00 2F:9B 30:C8 31:9C 32:11 33:DA 34:C0 35:95 36:A4
         37:A4 38:B2 39:96 3A:00

          The default segment identifier used by WHATS-UP is in the first
        and second characters of the first line of the data. A segment
        identifier of '00' identifies the first segment, and anything else
        in that position identifies the second segment.

          9.2.28.99.8.3 AO-13

          AO-13 RTTY Telemetry is transmitted in the form of Z blocks shown
        below (several blank lines have been deleted to same space in this
        document).

           Z  HI. THIS IS AMSAT OSCAR 13
                05.02.44  4661
           .0086   .0000   .07B9

           64  6   0   1   16  218 1

           193 170 158 143 181 144 147 140 200 7
           147 7   7   7   165 29  100 7   149 7
           10  7   145 115 34  7   153 129 122 180

           152 73  7   145 137 55  7   183 136 151
           7   154 137 169 211 142 127 100 9   140
           161 7   173 149 150 154 14  131 127 210
           HI THIS IS AMSAT OSCAR 13 08SEP90
           NEW AO13  SCHEDULE FROM 17OCT90 AFTER MOVE TO  LON
               180  LAT 0
           MODE B  MA 000 TO 095
           MODE JL MA 095 TO 125
           MODE LS MA 125 TO 130
           MODE S MA 130 TO 135
           MODE BS MA 135 TO MA 140
           MODE B  MA 140 TO 256



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          Note the non telemetry information at the end of the block. UO-2's
        ASCII telemetry looks different, so WHATS-UP is told where to look
        for the telemetry by the following items.

          9.2.28.99.9 Spare

          9.2.28.99.10 Number of Lines

          This item is used in non packet telemetry to tell WHATS-UP how
        many lines of data are in a frame.

          9.2.28.99.11 First Line

          This item is used in non packet telemetry to tell WHATS-UP which
        line in the frame contains the first line of data.

          9.2.28.99.12 Last Line

          This item is used in non packet telemetry to tell WHATS-UP which
        line in the frame contains the last line of data.

          9.2.28.99.13 Header Lines

          This item is used in non packet telemetry to tell WHATS-UP how
        many lines there are in the header.

          9.2.28.99.14 Character Count

          In non packet telemetry this item tells WHATS-UP the maximum
        number of characters on a line. Use it in BAUDOT,ASCII and CW
        telemetry to stop the display overrunning the page and to force
        recognition of the identifier and turn the automatic capture-to-disk
        on.

        9.2.29 Digital Telemetry Status Channels

         The next set of lines instruct WHATS-UP how to display digital
        telemetry status in the FO-20 frame. Digital status channels contain
        a number of status points. FO-12 and 20 have three data elements in
        each digital status channel. Typically, each line in the WHATS-
        UP.SYS file contains ten items in the following format.

        Status_Channel,     Status_Display_Page,     Status_Text,
        Status_Bit_Mask,    Status_Row, Status_Col,  Status_ON_Text,


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        Status_OFF_Text,    Status_ON_Color,         Status_OFF_Color.

         Each item is described in the following sections.

         9.2.29.1 Status_Channel

         This is the channel number of the digital status telemetry data in
        the frame. Each entry must be two digits.

         9.2.29.2 Status_Display_Page

         This item is the Display page number. A 0 is a 'wild card' which
        will be displayed on every page.

         9.2.29.3 Status_Text

         This is the text that is displayed in the page.

         9.2.29.4 Status_Bit_Mask

         This is the bit mask to mask out the position of the desired bit.
        The masks are in decimal. i.e. 1, 10 and 100.

         9.2.29.5 Status_Row

         This item is the Display page row. It identifies which row in the
        screen the data element will be displayed.

         9.2.29.6 Status_Col

         This item is the Display page column. It identifies which column in
        the screen the data item will be displayed.

         9.2.29.7 Status_ON_Text

         This item is the text that is displayed when the spacecraft
        telemetry contains a 1 value.

         9.2.29.8 Status_OFF_Text

         This item is the text that is displayed when the spacecraft
        telemetry contains a 1 value.




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         9.2.29.9 Status_ON_Color

         This item is the color the text is displayed in when the spacecraft
        telemetry contains a 1 value.

         9.2.29.10 Status_OFF_Color

         This item is the color the text is displayed in when the spacecraft
        telemetry contains a 0 value.

         These lines also terminate with an '*' character. A few typical
        lines from a Fuji.CNF file are shown below.

                     30,3,JTA Power    :,100, 4, 1, ON  , OFF ,11,10
                     30,3,JTD Power    :, 10, 4,25, ON  , OFF ,11,10
                     30,3,JTA Beacon   :,  1, 4,45, PSK , CW  ,11,10
                     38,3,Solar Panel 3:,100,12, 1, LIT , DARK,11,10
                     38,3,Solar Panel 4:, 10,12,25, LIT , DARK,11,10
                     38,3,Solar Panel 5:,  1,12,45, LIT , DARK,11,10

         Note the blanks in the Text ON and OFF positions. The blanks are
        used to ensure that a word such as "LIT" which contains three
        letters fully overwrites a word which contains four characters such
        as "DARK".

        9.2.30 Packet/Link Parameters

         The next set of items are the Packet/Link Parameters configurations
        (maximum = 16). If you want a value to show up in more than one page
        (other than the wild card [0]) you must enter it twice (once per
        page). Typically each row contains 10 items in the sequence shown
        below.

        Packet_title,  Packet_Type,   Packet_Lines,  Packet_Page,
        Packet_Color,  Packet_Row,    Packet_Col,    Link_Page,
        Link_Row,      Link_Col,      Binary_Byte_Count.

         Each item is described in the following sections.

         9.2.30.1 Packet_title

         This item is the name of UNP address (e.g. TLM,WASH, BCXRT).




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         9.2.30.2 Packet_Type

         This item is used by WHATS-UP to define the type of telemetry. The
        following assignments have been allocated but are not necessarily
        used in this release of WHATS-UP.

         0 AO-13 Non Packet Decimal telemetry.

         1  AMSAT Microsat Packet Telemetry (TLM) with the format CC:DD
            where CC is the hexadecimal channel number and DD the
            hexadecimal data.

         2  AMSAT Microsat Packet Telemetry, hexadecimal ASCII STATUS
            telemetry.

         3  Fuji Packet Telemetry format of decimal data in which the line
            and the position on the line identify the channel. WHATS-UP
            allows for up to 60 channels.

         4  AMSAT Microsat Packet Telemetry hexadecimal Binary STATUS
            telemetry.

         5  AMSAT Microsat Binary TLM Packet Telemetry.

         6  UO 1/2 ASCII Telemetry.

         9.2.30.3 Packet_Lines

         This item is the number of lines of text in the packet. For
        example, the AMSAT TLM packets contain three lines, the WASH packets
        contain only one.

         9.2.30.4 Packet_Page

         This item is the page that the raw contents of the packet will be
        displayed on. A '0' is a wild card which will make WHATS-UP display
        it on every page. By careful use of this item, you can display both
        raw and decoded packet data on the same page.

         9.2.30.5 Packet_Color

         This item is the color that the raw packet data will be displayed
        in.



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         9.2.30.6 Packet_Row

         This item is the row position that the raw packet will be displayed
        in, on the selected page.

         9.2.30.7 Packet_Col

         This item is the column position that the raw packet will be
        displayed in, on the selected page.

         9.2.30.8 Link_Page

         This item is the Display page for the cumulative count of the
        packet type. The wild card '0' applies.

         9.2.30.9 Link_Row

         This item is the row position that the packet header will be
        displayed in, on the selected page.

         9.2.30.10 Link_Col

         This item is the column position that the packet header will be
        displayed in, on the selected page.

         9.2.30.11 Binary_Byte_Count

         This item is the number of bytes in a binary packet. As no standard
        currently exists, we have to tell the computer how many bytes to
        expect.

         These lines also terminate with an '*' character.

        9.3 Telemetry Channel Extraction File

         The contents of this file are the defaults for extracting data from
        the playback file. A typical set are shown below. WHATS-UP does a
        string match, and looks for the first time that a particular string
        occurs. You may thus use the contents of a time packet, or the time
        mark in a header.

         ZCZC (default start time string) {start of file}
         NNNN (default stop time string) {end of file}
         2F


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         35
         38

         The first line contains the start string. 'ZCZC' tells WHATS-UP to
        start extracting at the beginning of the file. The second line
        contains the stop string. 'NNNN' tells WHATS-UP to stop extracting
        at the end of the file. The remaining lines are the individual
        channels (uppercase letters), one channel per line.

        9.4 Extracted Telemetry Data File

         This an ASCII string, comma delimited file which can be imported
        into your spreadsheet. The format of the file is such that each line
        starts with a date code or packet header. Then each channel and the
        datum associated with that channel follow for all channels in the
        packet segment or non packet frame for each and every channel
        displayed in the selected page on the screen. If the data from that
        channel is not displayed on the screen in the extract mode, the data
        will not be extracted.

         A typical example of three lines from this file is shown below.

         "01-Mar-91 03:39:46 DOVE-1*>TLM:","35", 6.7,"38", -9.7
         "01-Mar-91 03:39:56 DOVE-1*>TLM:","35", 6.7,"38", -10.3
         "01-Mar-91 03:40:06 DOVE-1*>TLM:","35", 6.7,"38", -10.3

        9.5 Doppler File

         Doppler data are stored in this file. If the file does not exist,
        it is created when needed. If it does exist, data are appended to
        the file. The first line of data identifies the time, place and
        spacecraft as shown below.

         "*** 22-Feb-91 02:57 Doppler Track STARTED for WEBER @ G3ZCZ"

         The next line provides the headings for the five columns as
        follows.

         "Time","Doppler Mark","Frequency","Doppler Shift","Measured Shift"

        9.5.1 The Time

         The Time is obtained from the PC clock.



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        9.5.2 The Doppler Mark

         The Doppler Mark is a sequential count incrementing at each sample.
        It can be used to provide an 'X' axis in a graph. Elapsed time will
        be the Doppler mark multiplied by the Doppler sampling interval in
        seconds.

        9.5.3 The Frequency

         The Frequency is the measured radio frequency.

        9.5.4 The Doppler Shift

         The Doppler Shift is the calculated/predicted Doppler Shift in kHz.

        9.5.5 The Measured Shift

         The Measured Shift is the difference (in kHz) between the measured
        radio frequency and the beacon frequency in the configuration file.

         These parameters should allow you to plot Doppler curves and
        determine orbit parameters using the time of closest approach
        technique.

         Typical entries in the file are shown in the following lines.

         "02:57:32", 2, 437110740, 8.1494,10.740
         "02:57:37", 3, 437110740, 8.1354,10.740
         "02:57:42", 4, 437110740, 8.1202,10.740
         "02:57:47", 5, 437109860, 8.1045,9.860
         "02:57:52", 6, 437110670, 8.0880,10.670
         "02:57:57", 7, 437110620, 8.0709,10.620
         "02:58:13", 8, 437110620, 8.0525,10.620
         "02:58:18", 9, 437109780, 7.9868,9.780
         .
         .
         "03:07:17", 115, 437092570, -7.7884,-7.430
         "03:07:22", 116, 437092570, -7.8204,-7.430
         "03:07:27", 117, 437092570, -7.8511,-7.430
         "03:07:32", 118, 437092570, -7.8802,-7.430
         "*** 22-Feb-91 03:07 Auto End"

         The lines of data end with a termination statement.



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         All text items are enclosed in double quotation marks ("). All
        elements are delimited by comma characters (,).

         If you plan to do Doppler measurements on the Microsats, then you
        may be interested in the following information.

         The following frequencies were taken after the completion and final
        tuning of the completed transmitter assemblies. The measurements
        were made at a temperature of 23 deg. C. As the frequency does
        change with temperature the current frequency will be slightly
        different.

                         PACSAT:   Normal PSK TX:        437.02625 MHz
                                   Raised Cosine TX:     437.05130 MHz
                                   S-Band TX:           2401.14280 MHz

                         DOVE:     FM TX No. 1:          145.82516 MHz
                                   FM TX No. 2:          145.82438 MHz
                                   S-Band TX:           2401.22050 MHz

                         WEBERSAT: Normal PSK TX:        437.07510 MHz
                                   Raised Cosine TX:     437.10200 MHz

                         LUSAT:    Normal PSK TX:        437.15355 MHz
                                   Raised Cosine TX:     437.12580 MHz

        9.6 Kepler Element Files (*.TLE)

         The following outlines the "NASA Two-Line" Keplerian data format.
        Data for each satellite consists of three lines in the following
        format:

        Mir
        1 16609U          91 36.87776287 0.00038608           39705-3 0  2481
        2 16609  51.6077 232.9299 0024950 205.6681 154.3223 15.64092124284608

         Line 1 contains an eleven-character name.
         Lines 2 and 3 are the standard Two-Line Orbital Element Set used by
                NASA and NORAD. The format description is:
          Line 2  Column Description
                   01-01 Line Number of Element Data
                   03-07 Satellite Number
                   10-11 International Designator (Last two digits of launch
                         year)


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                   12-14 International Designator (Launch number of the
                         year)
                   15-17 International Designator (Piece of launch)
                   19-20 Epoch Year (Last two digits of year)
                   21-32 Epoch (Julian Day and fractional portion of the
                         day)
                   34-43 First Time Derivative of the Mean Motion or
                         Ballistic Coefficient (Depending on ephemeris type)
                   45-52 Second Time Derivative of Mean Motion (decimal
                         point assumed; blank if N/A)
                   54-61 Radiation pressure coefficient. (Decimal point
                         assumed)
                   63-63 Ephemeris type
                   65-68 Element number
                   69-69 Check Sum (Modulo 10) (Letters, blanks, periods =
                         0; minus sign = 1; plus sign = 2)
          Line 3
                   Column   Description
                   01-01 Line Number of Element Data
                   03-07 Satellite Number
                   09-16 Inclination (Degrees)
                   18-25 Right Ascension of the Ascending Node (Degrees)
                   27-33 Eccentricity (decimal point assumed)
                   35-42 Argument of Perigee (Degrees)
                   44-51 Mean Anomaly (Degrees)
                   53-63 Mean Motion (Revs per day)
                   64-68 Revolution number at epoch (Revs)
                   69-69 Check Sum (Modulo 10)
                    All other columns are blank or fixed.

        9.7 AMSAT Format Element File (*.AMS)

         The AMSAT format file is the AMSAT file as received by means of
        packet radio. WHATS-UP scans the text for the word "Satellite:".
        When it finds it, it assumes that the next few lines carry the data
        in the fixed order. You thus, do not need to edit the file, just
        capture it to disk, and save with a filetype of 'AMS'. For example
        the following file could be saved as ORBS-19.AMS.

         If you need to enter data in by hand, edit an AMSAT format file,
        such as this one.

            4116] B   BID: ORBS-019.D
            Date: 20 Jan 91 02:58:24 Z


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            From: N4QQ@N4QQ
            To: ALL@AMSAT
            Subject: Orbital Elements   019.MICROS

            R:910120/0258z [e-mail] [Silver Spring,Md]  Z:20901
            From: [e-mail]
            To: ALL@AMSAT

            HR AMSAT ORBITAL ELEMENTS FOR THE MICROSATS FROM N3FKV
            HEWITT, TX      JANUARY 19, 1991
            TO ALL RADIO AMATEURS BT

            Satellite: AO-16
            Catalog number: 20439
            Epoch time:      91014.08680572
            Element set:     188
            Inclination:       98.6853 deg
            RA of node:        94.6412 deg
            Eccentricity:    0.0010690
            Arg of perigee:   259.0593 deg
            Mean anomaly:     100.9381 deg
            Mean motion:   14.28942714 rev/day
            Decay rate:       3.95e-06 rev/day^2
            Epoch rev:            5098

            Satellite: DO-17
            Catalog number: 20440
            Epoch time:      91014.07510019
            Element set:     187
            Inclination:       98.6867 deg
            RA of node:        94.6574 deg
            Eccentricity:    0.0010787
            Arg of perigee:   258.7019 deg
            Mean anomaly:     101.2949 deg
            Mean motion:   14.29004143 rev/day
            Decay rate:       4.60e-06 rev/day^2
            Epoch rev:            5098

        9.8 Spacecraft Operations File

         This is a text file which can usually be obtained from a packet
        radio bulletin. You may create one with the editor, if you can't
        find one on a packet radio BBS. A Typical file is shown below.



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               AO-13 TRANSPONDER SCHEDULE

                 Mode-B : MA 060 to MA 165 :
                 Mode-JL: MA 165 to MA 190 :
                 Mode-LS: MA 190 to MA 195 :
                 Mode-S : MA 195 to MA 200 : <= Mode B is Off - no swishing!
                 Mode-BS: MA 200 to MA 205 : <= QRP on BS please.
                 Mode-B : MA 205 to MA 256 :
                 Omnis  : MA 240 to MA 060 :

               This schedule is expected to continue through 27 March 91



































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        10.0 Glossary

        AMSAT     The Radio Amateur Satellite Corporation
        AO        AMSAT-OSCAR
        AOS       Acquisition of Signals
        ARRL      American Radio Relay League
        CCD       Charge Coupled Device
        DO        DOVE-OSCAR
        DOVE      Digital Orbiting Voice Encoder, also used interchangeably
                  with DOVE-OSCAR or DO
        EWT       Early Warning Time
        FM        Frequency Modulation
        FO        Fuji-OSCAR
        FSK       Frequency Shift Keying
        LO        LUSAT-OSCAR
        LOS       Loss of Signals
        OSCAR     Orbiting Satellite Carrying Amateur Radio
        PSK       Phase Shift Keying
        RTTY      Radio Teletypewriter
        SSB       Single Side Band
        TNC       Terminal Node Controller
        TU        Terminal Unit (Radio Modem)
        UO        UoSAT-OSCAR
        WO        WEBER-OSCAR






















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        11.0 References and Further Reading

         The best book is "The Space Radio Handbook" by John Branegan,
        GM4IHJ. It is published by the Radio Society of Great Britain. The
        book is available from the RSGB, Lambda House, Cranborne Rd, Potters
        Bar, Herts., England EN6 3JE. The price is 13.34 pounds sterling.
        John has also written several booklets on MIR, DOVE and UOSAT-2
        specifically for the educator and beginner. He can be reached at 8
        Whitehills, Saline, Fife, Scotland KY12 9UJ. (Send a SASE or IRCs
        please)

         Other books and articles of interest are listed below.

         Space Radio Handbook, John Branegan, GM4IHJ, Radio Society of Great
        Britain.

         Satellite Experimenter's Handbook, Martin Davidoff, K2UBC, ARRL
        1990, 2nd Edition.

         A Turnstile Antenna for Two Meters, Joe Kasser, G3ZCZ, 73 Magazine,
        June 1978.

         Antennas for Microsat Ground Stations, Dick Jansson, WD4FAB, The
        AMSAT Journal, Volume 13, Number 1, March 1990.

         Satellite Antennas from Recycled Junk, Howard Sodja, W6SHP,
        Proceedings of the OSCAR Seminar, September 29 & 30, 1990. Available
        from Project OSCAR Inc.

         Microcomputer Processing of UoSat-OSCAR 9 Telemetry, Robert J.
        Diersing, N5AHD, The Satellite Anthology, Pages 46-51, ARRL, 1988.

         The First Flock of Microsats, Tom Clark, W3IWI, Jan King, W3GEY,
        Bob McGwier, N4HY and the AMSAT team, The AMSAT Journal, Volume 12
        Number 1, May 1989.

         Ariane Launch Vehicle Malfunctions - Phase 3A Spacecraft Lost!, Tom
        Clark, W3IWI, Joe Kasser, G3ZCZ, Orbit Magazine, Volume 1 Number 2,
        June/July 1980.







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        12.0 Change History

         1.00 (4/01/91) Initial Release.

         1.10 (7/15/91) Converted to TP 6.0. Break procedure added on TNC
              port. Radio port parameters added to WHATS-UP.SYS. Autotrack
              added. Default radio freq/mode added. TNC and Radio Serial
              Port values 0 added to allow WHATS-UP to run in a multi-
              tasking environment without interfering with the serial ports.
              Directory path changed to apply only to capture-to-disk files.
              Debug Menu added. Radio Menu changed. CW telemetry automatic
              capture-to-disk added (for A-O 21).

         1.20 (11/08/91) SARA, TNC1, TNC2, PK-88, KAM and MFJ-1278 added.

         1.30 (07/04/94) DSP-2232, PK-900 added. SAREX/MIR Attack Mode and
              logging added. TLE and CNF nomenclature adopted.

         1.40 (01/01/96) Mutual visibility mode, sunlight and visible
              indicators, CW terminal functions, parallel port interface for
              memory up/down control, mission elapsed time (MET) window
              added. Julian dates for multi-year functions. Several
              additions in various menus.























        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 158


        13.0 Obtaining Further Information

         For further information about any of the spacecraft and the Radio
        Amateur Satellite program, photocopy and mail the following form
        together with a self addressed stamped envelope (SASE) to :-

         To: [ ] Project OSCAR Inc. POB 1136, Los Altos, CA. 94023-1136.

             [ ] AMSAT-UK, 94 Herongate Road, Wanstead Park, London E12 5EQ.
                 Telephone [phone].

         I read about the Radio Amateur Satellite program in WHATS-UP and am
        interested in it. Please send me further information about the
        program, and details of membership in your organization.

         CALL ________________ TODAY'S DATE _____________

         NAME ______________________________________________

         ADDRESS ___________________________________________

         ___________________________________________

         CITY ___________________________________________

         STATE _________ POSTCODE ______________________

         Comments and questions ...


















        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 159


        14.0 Other Products by Joe Kasser, W3/G3ZCZ

        14.1 PC-HAM 3.52

         PC-Ham contains the following suite of programs.

        14.1.1 LOGBOOK

         Full blown logging package. With automatic check of logs for awards
        such as DXCC. Allows you to recall any entry by call sign within
        seconds. Indexed displays, QSLing, Contest mode QSLing (prints the
        lot) and lots more. Although written in dBASE3 the package contains
        a compiled version (LOGBOOK.EXE), so you don't need dBASE to run it.
        The source code is ONLY given to registered users. Ideal for DX-
        peditions or for DX robot users to handle QSLing and log statistics.

        14.1.2 CONTEST

         Keeps Dupes in memory, logs QSO's to disk in format which can be
        processed by the LOGBOOK package. Now compiled in Turbo BASIC,
        source code is supplied so that you can modify the program to meet
        your requirements.

        14.1.3 CQSS

         Sweepstakes game compiled in Turbo BASIC. Work the ARRL Sweepstakes
        contest on your computer. You are located just outside Washington
        DC. A propagation model is built in to the program. This program is
        REQUIRED training for all sweepstakes operators. Earlier version of
        the program is described in detail in Software for Amateur Radio by
        Joe Kasser G3ZCZ, published by TAB Books, Blue Ridge Summit, PA.
        17214.

        14.1.4 WHATSON

         Predict HF Propagation for given days. Contest mode with printout
        to whole world at hourly intervals. Needs BASIC.

        14.2 STARTREK The Computer Program

         An ideal task for the beginner to learn a language on, is a
        simulation game which is written to run on a computer that the
        beginner has access to. For in that case, there is complete control
        of all inputs and outputs. This kind of game (in which the player


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        WHATS-UP.DOC Release 1.40 Page 160


        makes decisions based on the information available to him or her
        available at the time), can be made sufficiently sophisticated and
        complex so as to make writing it an adequate challenge for anybody.

         The techniques used in writing a good game are the same that
        programmers use in professional activities. Writing a good game
        poses a challenge that allows you to develop good habits and
        techniques for programming and also allows you to learn a language
        in an interesting manner. By taking an orderly approach to the game
        design, complex operations may be clearly understood and converted
        to computer code with the aid of a language reference manual,
        irrespective of the language being used.

         This product teaches the techniques for writing such a game using
        the STARTREK game as an example, and the BASIC language as the
        programming language in which to write the code.

         Registration fees.

         Single Copy        $15.00
         10 - 50 Copies     $12.00 per registered copy.
         50 - 100 Copies    $10.00 per registered copy.
         100 + Copies       $8.00 per registered copy.

        14.3.LAN-LINK 2.34

         LAN-LINK is a Personal Packet Terminal Program for the TNC1, TNC2,
        KPC-2 and most of all a smart multi-mode digital communications
        controller for the PK-900, DSP-2232, KAM, MFJ1278 and the PK-232.
        LAN-LINK is designed to optimize the configuration of the TNC in
        each communications mode and to provide some smart terminal
        features. LAN-LINK is a sophisticated program. In its basic state it
        allows you to use the TNC in an optimal manner. It configures the
        TNC (it types the commands) for you to maximize the communications
        efficiency in the communications mode of your choice. That means,
        for example, when working Packet on HF you need to program the TNC
        parameters to different values than you would use on VHF to make
        maximum use of the mode. One significant difference is the length of
        the packet itself, for the longer it is, the greater the probability
        of QRM destroying it. This program will adjust the packet parameters
        for you.

         PROGRAM HIGHLIGHTS: Function key and Menu driven. Expert system
        (ELMER) in packet mode for building smart servers. Automatic logbook


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        WHATS-UP.DOC Release 1.40 Page 161


        entries for Packet and Mailbox/Beacon Mode AMTOR Connects,
        semiautomatic logbook entries for other modes. Logbook file is dBASE
        compatible and can be processed by the LOGBOOK Package of PC-HAM by
        G3ZCZ for indexed listings, tracking of DXCC and other AWARDS, etc.
        Contest operation, sends standard message and automatically
        increments QSO count. Automatic optimized configuration of the TNC
        for each communications mode. All mode Function key 'OVER' feature
        (End). There are 60 files with fixed names (LAN-LINK.001 through
        LAN-LINK.010) which may be viewed and transmitted by means of
        function keys. They may also be edited from the Edit Menu. Set up of
        TNC for AMSAT-OSCAR Telemetry reception. Time display and event
        scheduler. ASCII Text Editor. Customizable Colors.

         Access to the TNC Command Mode is provided in case the user wishes
        to override any defaults. Automatic capture to disk of all packet
        radio connects. Automatic indication of the number of Packet
        connects. Local Area Network (LAN) message store and forward
        capability. Capable of automatic connect attempts to download a QTC
        from another station in the LAN. Capable of automatic connect
        attempts to a packet BBS to download your incoming messages, when
        your callsign appears on the BBS mail beacon annunciator. Capable of
        automatically requesting Bulletins on subjects that interest you
        from your local packet BBS. Digipeat monitoring and capture. Alert
        signal to let you know when a predetermined call shows up in a
        packet header on frequency. Conference and Bridge modes in
        multiconnect situations. Indicator that a specific station
        designated as the 'target' call connected in Packet Mode, or linked
        to AMTOR Beacon/Mailbox while you were away. Automatic NET/ROM and
        KA Node path set up from LAN-LINK.DIR call/path directory file.
        Selective answering machine and MAILBOX using NC/L command dialogue.
        Automatic Beacon Mode CQ caller. Automatic contest (DX-pedition)
        mode. Will call CQ repetitively and either work the connect and keep
        going after disconnect or signal you when a reply is received.
        Zmodem binary file transfer capability. RTTY SELCAL.

        14.4 ELMER 1.00

         ELMER is an Expert System Based on a Finite State Machine. There
        are two versions of ELMER supplied with LAN-LINK. One is built in
        for use in packet mode communications, when connected to someone
        else. The second version is a stand alone version for use in
        developing the text files and the logic. The stand alone version
        lets you program and debug your own personal ELMER by yourself. The
        stand alone version is a separate product and requires separate


        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 162


        registration.

        14.5 BASIC PACKET RADIO

         Basic Packet Radio explains how the computer can be used to smarten
        up your use of packet. Not only does the book explain packet radio,
        it comes with a full feature version of LAN-LINK (for the PC) on
        disk and contains the manual for the program.

         The topics covered in the book are outlined below.

         Getting Started in Packet Radio, What Packet Radio Is, The Shared
        Radio Channel, The Virtual Channel, The Equipment Needed to Hold a
        Packet QSO, The TNC, TNC Modes, The Terminal Program.

         Connecting the PC to the TNC, Command Convention, Making the PC
        Communicate with the TNC, Determining and Changing the State of a
        Parameter, Setting the Carriage Returns and Line Feed Display
        Controls, Flow Control, Connecting the TNC to the Radio, Delays in
        the Transceiver.

         The Local Area Network, How TNCs Communicate, Controlling the
        Display of Monitored Packets, Setting Your TNC to Display or Ignore
        Packets, The Wireless LAN, Use of Packet Beacons, The Alert Call,
        The Target Call, LAN Answering Machine, Mail Beacon (Annunciator),
        Remote Beacon Shutdown.

         Connecting to Someone, Connecting to Other Stations the LAN-LINK
        Way, The Point and Shoot (MH List) Way, Using the Call Menu, Loop
        Backs, Names, Handles and Paths, Connecting via NET/ROM and TheNet,
        Connecting via KA-Nodes, The SAREX Call and Working MIR.

         Extending the Range, Digipeating, Using NET/ROM and TheNet Nodes,
        Using G8BPQ Nodes, Using KA-Nodes, Using MSYS Nodes, Using ROSE
        Switches, Using LAN-LINK to Communicate via Nodes, Path
        Determination to a DX Station, Finding Packet Signals, Using
        Communication Satellites.

         The Packet Bulletin Board System, How to Connect to the PBBS,
        Connected to the PBBS, Connected, But What Next ?, Telling it Your
        Name, Getting Information about the PBBS Itself, The Command Prompt
        Line, Changing the Prompt Line, Listing the Messages and Bulletins,
        Reading Messages, Sending Messages, Sending Messages Around the
        World, Sending a Bulletin, Forwarding Bulletins, Sending NTS


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        WHATS-UP.DOC Release 1.40 Page 163


        Traffic, The Parts of the NTS Message, Killing Messages, Using LAN-
        LINK to Send NTS Traffic, Handling NTS Traffic, Files, Talk to the
        SYSOP, Connecting Elsewhere via the PBBS, Obtaining On-Line Help,
        Logging Off the PBBS, The F6FBB PBBS Features, Automating Message
        Reading, Message Headers.

         The PacketCluster, Summary of commands and features, Smartening Up
        PacketCluster Access With LAN-LINK.

         Internet wormholes and how to access them.

         Other Applications of Packet, Data Base Servers, Using a REQFIL
        Server, Using a REQDIR Server, Using a REQQTH Server, Electronic
        Newspapers, Non Real-Time QSOs, Automatic Beacons, Robots and
        Contests, Propagation Research, Transmission Control
        Protocol/Internet Protocol (TCP/IP).

         This is a book to read once, then use as a reference over and over
        again. If you decide you don't like the book, send it back within 30
        days for a swift refund.


























        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 164


        15.0 How Shareware Works

         The Association of Shareware Professionals (ASP) has established
        standards for its members and for any organization which has "ASP
        Approved" status. The ASP wants to make sure the shareware principle
        works for you. If you are unable to resolve a problem with an ASP
        member or organization (other than technical support), the ASP may
        be able to help. Please write to

         The ASP Ombudsman, 545 Grover Road, Muskegon, MI. 49442-9427, USA.

         You are encouraged to copy the floppy disk and share it freely with
        others. You have the luxury of trying out the product at your own
        pace and in the comfort of your own home or workplace.

         After you have used the material for a reasonable evaluation period
        (30 days), you should either discontinue use of the material or
        register your copy. Your support is important and greatly
        appreciated. With it, Shareware authors are encouraged to design and
        distribute new products. Without it, a great deal of high quality,
        low cost software will cease to be available.

          Why pay at all?

         You receive support from the author. You receive a CURRENT copy of
        the program. Your input and ideas help shape future products. You
        have a sense of pride and ownership in having honestly participated
        in the Shareware revolution. You help to keep software prices down
        by supporting a distribution method which doesn't depend on
        expensive advertising campaigns.

         Be aware of the following restrictions, designed to protect the
        community of Shareware users and to prevent greedy people from
        taking unfair advantage of the trust, hard work and good will of
        Shareware authors.

         1. No price or consideration may be charged for the material.
            However, a distribution cost may be charged for the cost of the
            diskettes, shipping and handling, not to exceed $6.

         2. The files and programs on the disks may not be modified or
            deleted.

         3. The material cannot be sold as part of some other more inclusive


        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 165


            package.

         4. The material cannot be "rented" or "leased" to others.

         5. The end user must be told clearly in writing on the outside of
            the package and in all advertising that the diskette(s) are
            "Shareware."

         6. The package must contain a written explanation that the disk is
            for evaluation purposes, and that an additional "registration
            fee" is expected by the author, if the material is used beyond
            an initial evaluation period.

         7. In the case of distribution via any telecommunications link, the
            following must be done:
            * An error checking protocol must be used.
            * The individual files must be combined into, and transferred in
            a library or archive format.

         8. Shareware distribution is permitted only in the United States,
            Canada, England, and Australia.

























        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 166


        Appendix 1 WHATS-UP 1.40 REGISTRATION FORM

         PLEASE COPY this form and MAIL to

        Software for Amateur Radio, P.O. BOX 3419, SILVER SPRING, MD 20918.

         CALL ________________ TODAY'S DATE ________________
         NAME ______________________________________________
         ADDRESS ___________________________________________
         ___________________________________________________
         CITY ______________________________________________
         STATE _________ POSTCODE ____________ TNC TYPE_____
         FIRMWARE REV ____ HOME BBS ______________
         DISK SIZE 5.25 _____ 3.5 ____

         Please register me as a user of WHATS-UP. I am currently using
        WHATS-UP Version ______ which I obtained from _______. Please send
        me the latest version of WHATS-UP or if a more recent one does not
        exist at this time, QSL my registration and add my name to the list
        to receive a free update when it becomes available.

        I also enclose an additional amount for evaluation copies of ELMER
        _, LAN-LINK _, PC-HAM _ and Startrek TCP _ ($5 for 1 program, $15.00
        for the set). If I like them, I plan to register them in due course.

         Basic Packet Radio Book (29.95)                       __.__
         Shipping for book $3.50 US/Canada, $10.00 overseas    __.__
         WHATS-UP Registration ($45.00)                        __.__
         LAN-LINK Registration ($45.00)                        __.__
         ELMER Registration ($45.00)                           __.__
         Evaluation software                                   __.__
         ____________________________________
         Maryland Residents please add 5% sales tax.           __.__

         Total Enclosed                                        __.__
         MasterCard/Visa Number ___________________________Expires __/__

         Many additions come into WHATS-UP as a result of user suggestions,
        so here's your chance to get some input in. Write them on this piece
        of paper.






        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 167


        Index

        µ, 50

        AFSK, 9, 75, 108, 118, 124, 130
        Alt-A, 6, 45
        Alt-B, 3, 23, 24
        Alt-C, 3, 23, 24, 46
        Alt-D, 3, 23, 24
        Alt-E, 6, 46
        Alt-F, 3, 23, 24
        Alt-H, 6, 46
        Alt-I, 3, 23, 24
        Alt-J, 3, 23, 24
        Alt-P, 3, 23, 25
        Alt-S, 3, 6, 23, 25, 46
        Alt-U, 6, 46
        Alt-X, 3, 6, 23, 25, 47
        Altitude, 8, 14, 19, 21, 53, 57, 58, 108, 125, 127
        AOS, 4, 5, 8, 18, 19, 20, 21, 43, 62, 129, 131, 134, 135, 138, 156
        Ariane, 105, 110, 157
        Arrows, 9
        ARSENE, 8, 111, 115, 116
        ASCII, 5, 9, 2, 3, 7, 8, 13, 28, 39, 40, 41, 43, 61, 64, 66, 69, 74,
          75, 98, 102, 124, 126, 130, 135, 143, 145, 148, 150, 162
        Astronomy, 105, 106
        Autotrack, 3, 9, 7, 21, 22, 23, 24, 132, 134, 158

        BAUDOT, 3, 40, 61, 64, 66, 135, 145
        Beacon, 5, 9, 10, 2, 4, 7, 19, 24, 39, 40, 41, 48, 49, 61, 70, 76, 80,
          94, 95, 97, 98, 100, 101, 104, 105, 108, 111, 115, 116, 118, 119,
          123, 124, 130, 131, 132, 133, 134, 137, 138, 143, 147, 151, 162, 163
        Branegan, 157

        Capture-to-disk, 4, 5, 6, 13, 18, 23, 31, 32, 33, 41, 126, 127, 133,
          145, 158
        CNF, 6, 7, 8, 10, 16, 30, 31, 38, 39, 40, 42, 126, 127, 131, 132, 133,
          147, 158
        Co-axial, 11
        Color, 5, 8, 9, 5, 16, 17, 18, 19, 20, 41, 43, 125, 126, 128, 129, 132,
          138, 146, 147, 148
        CW, 2, 4, 5, 6, 9, 4, 9, 11, 26, 27, 37, 39, 40, 43, 49, 50, 51, 76,
          91, 92, 94, 95, 96, 97, 98, 100, 104, 105, 118, 119, 120, 126, 130,
          132, 135, 145, 147, 158


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        WHATS-UP.DOC Release 1.40 Page 168



        Delay, 5, 10, 36, 37, 50, 109, 133, 137
        Digipeater, 73, 94, 111, 117, 118, 137
        Doppler, 3, 4, 9, 10, 2, 9, 19, 23, 24, 31, 32, 36, 126, 130, 132, 134,
          150, 151, 152
        DOVE-OSCAR, 2, 4, 62, 134, 156
        Downconverter, 64, 68
        Downlink, 7, 3, 4, 11, 61, 67, 69, 76, 84, 94, 95, 107, 108, 111, 118,
          119, 122
        Drag, 35, 52, 57

        Earth-Sun, 54
        EWT, 10, 19, 20, 21, 43, 129, 131, 137, 138, 156
        Extract, 4, 8, 5, 20, 28, 125, 127, 128, 150

        Fades, 3, 65, 66
        FO, 4, 61, 64, 69, 92, 93, 94, 95, 102, 119, 131, 133, 139, 145, 156
        Footprint, 21
        Fuji-OSCAR, 7, 4, 7, 62, 92, 95, 96, 97, 98, 99, 100, 101, 102, 103,
          104, 133, 134, 135, 156

        Greek, 50

        Hop, 21

        Icom, 135, 136
        Inclination, 7, 35, 53, 55, 62, 93, 111, 116, 153, 154
        Index, 168

        JAS, 93, 95, 98, 101, 102, 143
        JBS, 94, 95, 101, 133, 143
        Jupiter, 106, 107, 110, 111

        Kepler, 8, 10, 54, 125, 127, 152
        Keplerian, 4, 9, 15, 19, 28, 31, 33, 34, 131, 132, 134, 152
        Keyboard, 6, 4, 9, 10, 15, 43, 49, 50
        Keyer, 9, 51
        Keystroke, 49
        KPC, 161

        LAN-LINK, 11, 4, 18, 42, 44, 45, 46, 161, 162, 163, 164, 167
        Laptop, 9, 136
        Latitude, 8, 13, 21, 93, 125, 126
        Launched, 58, 59, 70, 73, 76, 84, 92, 105, 111, 116


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        WHATS-UP.DOC Release 1.40 Page 169


        Line-of-sight, 11
        Logbook, 6, 9, 10, 4, 9, 44, 45, 46, 47, 125, 126, 129, 130, 160, 161,
          162
        Longitude, 8, 13, 21, 125, 127
        LPT, 10, 133, 135, 136, 138
        LSB, 37, 80, 81, 82, 83, 96, 97, 100, 104, 135
        LUSAT, 2, 84, 85, 89, 91, 92, 131, 152
        LUSAT-OSCAR, 2, 4, 62, 134, 156

        Mheard, 123
        MicroSat, 5, 2, 6, 14, 39, 40, 58, 84, 143, 148, 157
        Milliseconds, 50, 51
        MIR, 2, 6, 10, 4, 9, 15, 20, 21, 47, 48, 49, 130, 133, 137, 138, 152,
          157, 158, 163
        Mode-B, 78, 79, 155
        Mode-BS, 155
        Mode-J, 82, 83
        Mode-JD, 94
        Mode-JL, 79, 155
        Mode-L, 79, 80, 83
        Mode-LS, 155
        Mode-S, 79, 80, 82, 83, 155
        Morse, 5, 3, 4, 21, 39, 40, 43, 50, 51, 82, 91, 95, 129
        Multi-mode, 2, 64, 128, 161
        Multi-task, 50
        Multi-tasking, 42, 158
        Multi-year, 158

        North, 19, 55, 116

        Orbits, 3, 4, 6, 11, 26, 27, 33, 53, 58, 62, 63, 66

        PACSAT, 2, 85, 131, 152

        QTH, 9, 126, 130

        RAAN, 7, 35, 55, 56
        Range, 8, 3, 11, 14, 18, 19, 20, 62, 64, 65, 67, 76, 98, 107, 113, 125,
          129, 163
        Ranging, 82, 106
        Re-entered, 59, 73
        Real-time, 5, 18, 21, 23, 26, 28, 74, 138, 164
        Receiver, 3, 9, 4, 5, 10, 12, 23, 24, 36, 64, 65, 66, 67, 68, 78, 79,
          107, 108, 121, 133, 134, 135


        COPYRIGHT Joe Kasser, G3ZCZ 1996.
        WHATS-UP.DOC Release 1.40 Page 170


        RS, 5, 13, 14, 15, 20, 41, 64, 66, 120, 121

        SARA, 5, 7, 39, 41, 69, 105, 106, 107, 108, 110, 111, 158
        SARA-OSCAR, 7, 62, 105
        SAREX, 2, 4, 6, 9, 10, 4, 9, 26, 27, 42, 47, 48, 49, 125, 129, 133,
          135, 137, 138, 158, 163
        Segment, 138, 139, 141, 142, 143, 144, 150
        Sidereal, 110
        SSB, 11, 12, 45, 63, 94, 156
        Stream, 9, 126, 131
        Sub-satellite, 21
        Sun, 4, 9, 33, 34, 35, 54, 55, 56, 59, 60, 70, 73, 81, 82, 85, 93, 106,
          107, 108, 109, 110, 126, 130

        Telemetry, 2, 7, 8, 10, 2, 3, 4, 5, 6, 15, 16, 17, 20, 23, 32, 40, 41,
          42, 61, 65, 66, 69, 70, 71, 73, 74, 75, 76, 77, 78, 84, 85, 86, 87,
          89, 91, 94, 95, 96, 98, 99, 101, 102, 103, 104, 107, 108, 111, 113,
          115, 116, 117, 118, 119, 120, 121, 122, 124, 125, 127, 133, 138, 139,
          140, 142, 143, 144, 145, 146, 147, 148, 149, 150, 157, 158, 162
        Temporary, 51
        Transceiver, 11, 12, 163
        Transients, 10
        Transverter, 12
        Transverters, 12
        TTL, 9

        UoSAT-OSCAR, 4, 40, 156, 157
        Uplink, 11, 94, 95, 108, 111, 118, 119, 123, 124, 135

        Vector, 54, 82
        Viewer, 130

        WEBER-OSCAR, 2, 4, 62, 134, 156

        Zap, 6, 48, 49











        COPYRIGHT Joe Kasser, G3ZCZ 1996.