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WHATS-UP.DOC Release 1.00 Page 1
_______
____|__ | (tm)
--| | |-------------------
| ____|__ | Association of
| | |_| Shareware
|__| o | Professionals
-----| | |---------------------
|___|___| MEMBER
WHATS-UP (c) Joe Kasser, G3ZCZ, 1990-1991
Joe Kasser G3ZCZ/W3
POB 3419
Silver Spring, Md. 20918
Voice (301) 593 6136
Data BBS (301) 593 9067
Compuserve (CIS) 70531,1405
WHATS-UP is a tool which allows you to capture, decode, display
and extract for analysis telemetry from the following Orbiting
Satellites Carrying Amateur Radio (OSCAR).
UoSAT-OSCAR 11 1200 baud ASCII Telemetry,
AMSAT-OSCAR 13 50 baud RTTY Z blocks Telemetry,
AMSAT-OSCAR 16, WEBER-OSCAR 18 and LUSAT-OSCAR 19 Binary Tele-
metry,
DOVE-OSCAR 17 ASCII TLM packet Telemetry,
Fuji-OSCAR 20 Status and Telemetry.
WHATS-UP will also allow you to process any telemetry data you
have from the now reentered UoSAT-OSCAR 9 and Fuji-OSCAR 12
spacecraft.
WHATS-UP is a table driven program which uses configuration files
to allow maximum flexibility. If you have a Kenwood Radio,
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.
This version of the program is configured for a PK-232. It will
intercept the Microsat Binary telemetry from AMSAT-OSCAR 16
(PACSAT), WEBER-OSCAR 18 (WEBERSAT) and LUSAT-OSCAR 19 (LUSAT)
and display and process them as if they were DOVE-OSCAR 17 ASCII
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 2
telemetry. NOTE: AMSAT have STILL NOT FINALIZED or PUBLISHED the
Binary Telemetry Format for the Microsats.
The program is distributed as a Shareware product. You may freely
copy and share the product for noncommercial 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.
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 imple-
mented, you will be sent a complimentary copy of the disk with
the change incorporated.
European Radio Amateur users may register (24.00 Pounds Sterling,
includes 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 44 (0)634-
687178, 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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 3
Table of Contents
1.0 Introduction
1.1 Capabilities of WHATS-UP
1.2 Program Requirements
1.3 Packet Link Quality Measurements
1.4 Copying Non-packet Telemetry
1.5 Obtaining Updates
1.6 Limit Checking
2.0 Customization
2.1 Bringing WHATS-UP up for the First Time.
2.2 Editing the Configuration File.
2.3 Starting the program.
2.4 Screen Areas
2.5 Setting Up Customized Display Pages
3.0 Modes
3.1 Standby Mode
3.2 Interactive Mode
3.3 Real Time Mode
3.4 Orbital Dynamics Mode
3.5 Playback Mode
3.6 (Data) Extraction Mode
3.7 Audio Warnings and Orbit Data Displays
4.0 Menus
4.1 Function Keys
4.2 Modes menu
4.2.1 Extract From Playback File
4.2.2 Interactive Mode
4.2.3 Orbital Parameters
4.2.4 Playback Mode
4.2.5 Real Time Mode
4.2.6 Selections Menu
4.2.7 Exit to Dos
4.3 Selections Menu
4.3.1 Change Display Page
4.3.2 Edit Menu
4.3.3 Files Menu
4.3.4 Help Menu
4.3.5 Jump to DOS
4.3.6 Modes Menu
4.3.7 Orbits Menu
4.3.8 Radio Menu
4.3.9 Spacecraft Menu
4.3.10 PK232 Menu
4.3.11 Utilities Menu
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 4
4.3.12 Exit to DOS
4.4 Edit menu
4.4.1 Edit Spacecraft Doppler File
4.4.2 Edit Any File
4.4.3 Edit Orbital Data File
4.4.4 Edit Spacecraft Configuration File
4.4.5 Pick Capture-to-disk File
4.4.6 Edit Capture-to-disk File
4.4.7 Edit WHATS-UP.SYS
4.4.8 Edit Two Files
4.4.9 Edit Doppler Channel File
4.4.10 Edit Doppler Data File
4.4.11 Pick Spacecraft Configuration .SYS File
4.5 Files Menu
4.5.1 Change Directory Path
4.5.2 Change Playback File
4.5.3 View Playback File
4.5.4 Show Capture-to-disk Files
4.6 Orbits Menu
4.6.1 Pick AMSAT Format Element Set
4.6.2 Edit WHATS-UP.2LN
4.6.3 Load Element File
4.6.4 Pick NASA 2 Line Element Set
4.6.5 View Spacecraft Orbit Elements
4.7 Radio Menu
4.7.1 Turn Doppler Tracking On/Off
4.7.2 Change Doppler Interval
4.8 Spacecraft Menu
4.8.1 picK Spacecraft
4.8.2 Change Spacecraft
4.8.3 Pick Ops. Schedule
4.8.4 Show Ops. Schedule
4.9 TNC Menu
4.9.1 UoSAT ASCII Beacon
4.9.2 Phase 3 RTTY Beacon
4.9.3 Set Morse Code (CW)
4.9.4 Fuji/MicroSat ASCII Packet
4.9.5 Configure PK232
4.10 Utilities menu
4.10.1 Change Directory Path
4.10.2 Change Beacon Frequency
4.10.3 Show Space on Disk
4.10.4 Reset Header Counters
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 5
4.10.5 Show Defaults
4.10.6 Set PC Clock
4.10.7 Show Files
4.10.8 Show Color Chart
4.10.9 Reconfigure WHATS-UP
4.10.10 Sound CW String
5.0 Orbital Elements
5.1 Basics
5.2 Orbital Trajectories
5.3 Types of orbits
5.4 Orbital Elements
5.5 Angle of Inclination.
5.6 Right Ascension of Ascending Node (RAAN).
5.7 Eccentricity and Semimajor Axis
5.8 Decay Rate
5.9 Argument of Perigee.
5.10 Epoch Time (of Ascending Node) and Revolution Number.
5.11 The Mean Motion.
5.12 The Catalog Number
5.13 Mean Anomaly
5.14 Anticipated Spacecraft Lifetimes
6.0 The Spacecraft
6.1 Receiving system components
6.1.1 Antennas
6.1.2 Receivers
6.1.3 Terminal Units or Modems
6.2 Receiving Signals from DOVE
6.3 Receiving Signals from UoSAT-OSCAR 11
6.4 Receiving Signals from AMSAT-OSCAR 13
6.5 Receiving PSK Modulated Signals in the 70 cm Band
7.0 Decoding Active Spacecraft Telemetry
7.1 DOVE-OSCAR 17
7.2 UoSAT-OSCAR 11
7.3 AMSAT-OSCAR 13
7.4 AMSAT-OSCAR 16, WEBER-OSCAR 18 and LUSAT-OSCAR 19
7.5 Fuji-OSCAR 20
7.6 AMSAT-OSCAR 21
8.0 Spacecraft No Longer Active
8.1 Fuji-OSCAR 12
9.0 File formats
9.1 Configuration File
9.1.1 Your callsign
9.1.2 Default spacecraft Name
9.1.3 Station Latitude
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 6
9.1.4 Station longitude
9.1.5 Station Altitude
9.1.6 Station minimum antenna elevation for acquisition
9.1.7 Station minimum usable pass time
9.1.8 Early warning time
9.1.9 Default Kepler file
9.1.10 UTC offset
9.1.11 Default directory path
9.1.12 Default extracted data file
9.1.13 Default file name with list of telemetry
parameters to extract file
9.1.14 TNC Type
9.1.15 Serial port to TNC
9.1.16 PC serial port to Radio
9.1.17 PC serial baud rate
9.1.18 PC port data bits
9.1.19 PC port Stop bits
9.1.20 PC Port parity bits
9.1.21 status (top) window color
9.1.22 Telemetry Page color
9.1.23 outgoing window color
9.1.24 incoming window color
9.1.25 prompt window color
9.1.26 Alarm window color
9.1.27 Bottom window color
9.1.28 Emphasis color
9.1.29 Prompt color
9.1.30 Option color
9.1.31 Parameter changed color
9.1.32 Parameter limit exceeded color
9.1.33 Orbit element window color
9.1.34 Orbit element window Orbit element window In
range color
9.1.35 Orbit element window early warning color
9.1.36 Orbit element window next one up color
9.1.37 Orbit alert dit time
9.1.38 Orbit alert note
9.1.39 Flag Sound
9.1.40 Doppler display Flag
9.1.41 Spacecraft Configuration File Linkages
9.1.42 * Comment line
9.1.43 The remaining lines
9.2 Spacecraft Parameter Files
9.2.1 Spacecraft ID.
9.2.2 Spacecraft Suffix
9.2.3 Beacon Frequency
9.2.4 Doppler Measurement File
9.2.5 Spacecraft Identification in Keplerian Element
File
9.2.6 Doppler Measurement Sample Interval
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 7
9.2.7 Initial Frequency Offset
9.2.8 TNC configuration Code
9.2.9 Modulation
9.2.10 Data Type
9.2.10 Receiver Type
9.2.11 Selected or default display page number
9.2.12 Page Definitions
9.2.13 Telemetry Parameter Configuration
9.2.13.1 TLM_Channel
9.2.13.2 TLM_Segment_ID
9.2.13.3 TLM_Description
9.2.13.4 TLM_Eqn_Type
9.2.13.5 TLM_Ceof_C
9.2.13.6 TLM_Ceof_B
9.2.13.7 TLM_Ceof_A
9.2.13.8 TLM_Units
9.2.13.9 TLM_Page
9.2.13.10 TLM_Row
9.2.13.11 TLM_Col
9.2.13.12 TLM_Width
9.2.13.13 TLM_Dec
9.2.13.14 TLM_Limit_Check
9.2.13.15 TLM_Limit_Low
9.2.13.17 TLM_Limit_High
9.2.13.18 TLM_Negative_Blank
9.2.13.99 The Telemetry Identifier Line
9.2.13.99.1 The Line Identifier
9.2.13.99.2 The Segment Identifier
9.2.13.99.3 Spare/Not Used
9.2.13.99.4 Location of Segment Identifier
in Line
9.2.13.99.5 Spare/Not Used
9.2.13.99.6 Spare/Not Used
9.2.13.99.7 Spare/Not Used
9.2.13.99.8 Segment Identifier String
9.2.13.99.8.1 Fuji
9.2.13.99.8.2 DOVE
9.2.13.99.9 Spare
9.2.13.99.10 Number of Lines
9.2.13.99.11 First Line
9.2.13.99.12 Last Line
9.2.13.99.13 Header Lines
9.2.13.99.14 Header Display Flag
9.2.14 Digital Telemetry Status Channels
9.2.14.1 Status_Channel
9.2.14.2 Status_Display_Page
9.2.14.3 Status_Text
9.2.14.4 Status_Bit_Mask
9.2.14.5 Status_Row
9.2.14.6 Status_Col
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 8
9.2.14.7 Status_ON_Text
9.2.14.8 Status_OFF_Text
9.2.14.9 Status_ON_Color
9.2.14.10 Status_OFF_Color
9.2.15 Packet/Link Parameters
9.2.15.1 Packet_title
9.2.15.2 Packet_Type
9.2.15.3 Packet_Lines
9.2.15.4 Packet_Page
9.2.15.5 Packet_Color
9.2.15.6 Packet_Row
9.2.15.7 Packet_Col
9.2.15.8 Link_Page
9.2.15.9 Link_Row
9.2.15.10 Link_Col
9.2.15.11 Binary_Byte_Count
9.3 Telemetry Channel Extraction File
9.4 Extracted Telemetry Data File
9.5 Doppler Data File
9.5.1 The Time
9.5.2 The Doppler Mark
9.5.3 The Frequency
9.5.4 The Doppler Shift
9.5.5 The Measured Shift
9.6 Kepler Element Files (*.2LN)
9.7 AMSAT Format Element File (*.AMS)
9.8 Spacecraft Operations File
10.0 Glossary
11.0 References and Further Reading
APPENDIX
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 9
1.0 Introduction
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.
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 potential for at least the last six years.
Before every satellite launch the equations and format for the
spacecraft telemetry are published by AMSAT. 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. There's a lot of computing power out there
that has the potential to process telemetry and discover
something new, but does not have the access to the data. WHATS-UP
is an attempt to provide that data to the average Radio Amateur
and Educator.
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 10
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 from 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
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-OSCAR 11 (UO-11), 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) and
Fuji-OSCAR 20 (FO-20) 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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 11
1.2 Capabilities of WHATS-UP
WHATS-UP contains the following features:
* 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.
* Audio warning of spacecraft acquisition of signal (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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 12
* 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 Packet TNC with an RS-232 interface
is only required for real time data capture. This version is
configured for the PK-232 because only the PK-232 has the
capability for receiving the telemetry from all the
spacecraft supported by the program.
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.
By putting the correct parameters in the SPACECRAFT.SYS
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 DOVE-OSCAR 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 AMSAT-OSCAR 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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 13
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.
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.
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 to use Com2
as the serial port between the PC and the Kenwood Radio.
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 14
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.
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 mneumonic 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 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 16: If you are not using Com1 as the serial port
between the PC and the TNC, enter the port number
on this line.
Line 17: If you have a compatible radio with RS-232 control
capability and are not using Com2 as the serial
port between the PC and the Radio, enter the port
number on this line.
Line 18: If you are not using 1200 baud between the PC and
the TNC enter the actual value on this line.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 15
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'
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
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following typical messages will be send during this
activity.
MIR Loaded
RS-10/11 Loaded
AO-13 Loaded
UO-14 Loaded
AO-16 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 AO-16
Computing Next Pass for DO-17
If the default Keplerian data file is not present on
the disk, the orbital mode will be disabled.
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 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
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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.SYS 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 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.
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'* 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).
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.
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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 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 information displayed in the orbital 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.
MA Mean Anomaly, or position of the spacecraft in its
orbit (see Section 5).
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.
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 the display is shown below.
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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.
An 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 are displayed in the default window
color. 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 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
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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 realtime and interactive modes.
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 switches raw data display window in and out, if
window lines are set correctly.
Alt-B send a 'Break' to the TNC
Alt-C connect to another packet station
Alt-D disconnect from another packet station
Alt-P Printer on/off toggle
Alt-S Sound on/off toggle
Alt-X Quit Mode
left arrow decreases playback speed
right arrow increases playback speed.
4.2 Modes menu
When you bring up the Modes menu you will be prompted with
the following options.
E Extract From Playback File
I Interactive Mode
O Orbital Parameters
P Playback Mode
R Real Time Mode
S Selections Menu
X Exit to Dos
Type the letter associated with the option to perform
it.
Each of the options are described below.
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4.2.1 Extract From Playback File
This option begins up the Extraction mode.
4.2.2 Interactive Mode
This option begins up the Interactive mode.
4.2.3 Orbital Parameters
This option begins up the Orbital mode. This option is
only active if Keplerian data files are in the defined
directory path.
4.2.4 Playback Mode
This option begins up the Playback mode.
4.2.5 Real Time Mode
This option begins up the Real-time mode.
4.2.6 Selections Menu
This option begins up the Selections Menu.
4.2.7 Exit to Dos
This option allows you to terminate WHATS-UP and return
to DOS.
4.3 Selections Menu
This menu presents you with the following typical options.
C Change Display Page
E Edit Menu
F Files Menu
H Help Menu
J Jump to DOS
M Modes Menu
O Orbits Menu
R Radio Menu
S Spacecraft Menu
T PK232 Menu
U Utilities Menu
X Exit to DOS
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4.3.1 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.
4.3.2 Edit Menu
This option begins up the Edit Menu.
4.3.3 Files Menu
This option begins up the Files Menu.
4.3.4 Help Menu
This option displays help information for the function
keys.
4.3.5 Jump to DOS
This option allows you to jump into a DOS Shell. You
return to WHATS-UP by typing the DOS command 'EXIT'.
4.3.6 Modes Menu
This option begins up the Modes Menu.
4.3.7 Orbits Menu
This option begins up the Orbits Menu. This option is
only available if an orbit element file (*.AMS or
*.2LN) is present.
4.3.8 Radio Menu
This option begins up the Radio Menu if a Kenwood Radio
is present and the interface is operational.
4.3.9 Spacecraft Menu
This option begins up the Spacecraft Menu.
4.3.10 TNC or PK232 Menu
This option begins up the TNC Menu.
4.3.11 Utilities Menu
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This option begins up the Utilities Menu.
4.3.12 Exit to DOS
This option allows you to terminate WHATS-UP and return
to DOS.
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)
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
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^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
^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.
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D DOVE.DOP
F Any File
K WHATS-UP.2LN
M c:dove.SYS
P Pick ***.D17 File
R c:910313.D17
S WHATS-UP.SYS
T Two Files
W Arrays
X whats-up.txt
Y Pick ***.SYS File
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.
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.
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4.4.8 Two Files
This option lets you edit any two files.
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.
4.5 Files Menu
This menu presents you with the following typical options.
A Change Directory Path
F Change Playback File
V View Playback File
Z Show *.D17 Files
4.5.1 Change Directory Path
This option allows you to temporarily change the
directory path.
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.
4.5.3 View Playback File
This option allows you to view the contents of the
playback file.
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4.5.4 Show Spacecraft data Files
This option shows you the data files for the chosen
spacecraft in the default directory path.
4.6 Orbits Menu
This menu presents you with the following typical options.
A Pick AMSAT Format Element Set
E Edit WHATS-UP.2LN
L Load Element File
N Pick NASA 2 Line Element Set
V View Spacecraft Orbit Elements
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.
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.2LN
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 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.
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4.6.5 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.
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
If the default element file is in AMSAT format (*.AMS) the
two line display is not shown.
4.7 Radio Menu
This menu is only present if you have a Kenwood Radio
defined as your Radio Receiver for the spacecraft. The menu
presents you with the following typical options.
D Turn Doppler Tracking ON
I Change Doppler Interval
4.7.1 Turn Doppler Tracking ON/OFF
This option lets you turn the Doppler tracking on and
off.
4.7.2 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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4.8 Spacecraft Menu
This menu presents you with the following typical options.
K picK Spacecraft
M Change Spacecraft
P Pick Ops. Schedule
S Show Ops. Schedule
4.8.1 picK Spacecraft
This option allows you to choose another spacecraft
from a list of those in the default directory path. To
select one, move the cursor down to the desired one and
touch the 'Enter' key. For example, amongst the default
files supplied are DOVE.SYS and FUJI.SYS. To select the
DOVE or the Fuji-20 spacecraft, move the cursor down to
the 'DOVE.SYS' or 'Fuji.SYS' line and touch the 'Enter'
key.
4.8.2 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.SYS and FUJI.SYS. To select the
DOVE or the Fuji-20 spacecraft, type 'DOVE' or 'Fuji'
4.8.3 Pick Ops. Schedule
This option allows you to pick an operations schedule.
You would use it to look at the schedule for a
spacecraft other than the one currently selected.
4.8.4 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.
A UoSAT ASCII Beacon
B Phase 3 RTTY Beacon
C Set Morse Code (CW)
M Fuji/MicroSat ASCII Packet
T Configure PK232
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4.9.1 UoSAT ASCII Beacon
This option will configure the PK-232 to copy the
UoSAT-OSCAR 11 telemetry. Note: you require a hardware
change in the PK- 232 to make sense of the received
data.
4.9.2 Phase 3 RTTY Beacon
This option will configure the PK-232 to copy the
UoSAT-OSCAR 13 Baudot Beacon.
4.9.3 Set Morse Code (CW)
This option will configure the PK-232 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 PK-232 to copy the DOVE
and 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 AMSAT-OSCAR 21 1100 baud PSK ASCII Packet
This option will configure the PK-232 for 1100 baud on
the Radio Port. The PK-232 does not have an 'HB 1100'
command yet, that is coming in a forthcoming firmware
release, hence the approach used here. You will still
need a PSK decoder to copy the data from the
spacecraft.
Note: at the time this software was released, the
display formats for RM-1 were not available, so no
configuration file is available for RM-1 in WHATS-UP
0.60.
Note: at the time this software was released, it was
unclear if the data are HDLC or some other kind of PSK
similar to AMSAT-OSCAR 13's 400 baud PSK data. If the
data are not HDLC, you will not be able to copy
anything usable on the PK-232.
Note: In view of the two caveats above, don't expect
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too much from this mode. In particular, do not go out
to purchase a PSK modem for use with this spacecraft
without verifying that the data are receivable.
4.9.5 Configure PK232
This option configures the PK-232 to copy the UI
packets transmitted by the Packet spacecraft.
4.10 Utilities menu
This menu presents you with the following typical options.
A Change Directory Path
B Change Beacon Frequency
D Show Space on Disk
R Reset Header Counters
S Show Defaults
U Set PC Clock
Z Show Files
* Show Color Chart
! Reconfigure WHATS-UP
@ Sound CW String
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 Change Beacon Frequency
This option allows you to temporarily change the beacon
frequency displayed in the status window.
4.10.3 Show Space on Disk
This option allows you to see how much space is left on
a disk with exiting from the program.
4.10.4 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.
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4.10.5 Show Defaults
This option allows you to display the default settings.
4.10.6 Set PC Clock
This option lets you change the time in the PC. When
you do so, WHATS-UP will recalculate the positions of
the spacecraft.
4.10.7 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.
4.10.8 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.
4.10.9 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.
4.10.10 Sound CW String
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 signals.
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
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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.
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.
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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
(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.
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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.
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 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.
5.5 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.
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The maximum northern and southern latitudes reached by a
satellite are equal to the angle of inclination of its
orbit.
5.6 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.
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
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the earth's equator is defined as the Right Ascension of the
Ascending Node (RAAN).
5.7 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.
5.8 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
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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.
5.9 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.
5.10 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) for which the element set is
valid.
5.11 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).
5.12 The Catalog Number
The catalog number is the number given to the object.
5.13 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
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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.
5.14 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.
5.14.1 Orbital Decay
The last OSCAR to plunge back into the earth's atmosphere
while still active was UoSAT-OSCAR 9. 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 some-
where around 120 years; so orbital decay is not our main
worry. There has been some concern about AMSAT-OSCAR 13's
orbit, which is expected to decay somewhere between 1992 and
1995. AMSAT however are currently planning a replacement
spacecraft so the investment in receiving equipment will not
be in vain.
5.14.2 Battery lifetime.
Battery breakdown has caused the demise of all amateur
spacecraft except UoSAT-OSCAR 9. OSCARs 1, 2 and 3 were
limited to whatever charge was in the batteries when launch-
ed. 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 9 was still looking
good when it recentered the earth's atmosphere after 8
years. UoSAT-OSCAR 11, 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
UoSAT-OSCAR 11. The batteries on UoSAT-OSCAR 11 have shown
no signs of weakening after almost six years in orbit, so
the prognosis for UoSAT-OSCAR 11 and the Microsats looks
good.
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5.14.3 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. UoSAT-OSCAR 11, 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 longer switch. This situation has occurred
in AMSAT-OSCAR 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 AMSAT-
OSCAR 10 which with its 4000 km perigee, spends more time in
the Van Allen radiation belts than was planned. AMSAT-OSCAR
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.
AMSAT-OSCAR 13 is in a better orbit with a lower perigee,
and should not suffer radiation degradation before other
effects shorted its lifespan.
6.0 The Spacecraft
OSCAR spacecraft downlink signals in the amateur 145 MHz and 430
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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. UoSAT-OSCAR 11 and AMSAT-
OSCAR 13 send back BAUDOT or ASCII data while AMSAT-OSCAR 16,
DOVE-OSCAR-17, WEBER-OSCAR 18, LUSAT-OSCAR 19 and Fuji-OSCAR 20
downlink packetized telemetry.
Table 6-1 Some of the Characteristics of OSCAR Downlinks.
Spacecraft Beacon Modulation Data Note
Frequency Type Rate
(MHz)
UO-11 145.825 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
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.
Before discussing the equipment needed to receive signals from
the spacecraft, a brief word about the spacecraft themselves is
in 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 AMSAT-OSCAR 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, AMSAT-OSCAR 13 in an elliptical orbit is in range for many
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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-OSCAR 11 699 670 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
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 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
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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.
UoSAT-OSCAR 11 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
Receivers fall into two kinds, FM and linear. FM receivers
are used for reception of the FM signals from DOVE and
UoSAT-OSCAR 11, 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 (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.
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6.1.3 Terminal Units or 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
AMSAT-OSCAR 16, WEBER-OSCAR 18, LUSAT-OSCAR 19 and Fuji-
OSCAR 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 AMSAT-
OSCAR 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 AMSAT-OSCAR 13 as well as DOVE
and the other spacecraft. AMSAT-OSCAR 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 UoSAT-OSCAR 11 is a little more difficult, as
its ASCII encoding is the reverse of the standard used in
the USA. 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). 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.
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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
THE
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 is
the easiest spacecraft to receive usable signals from. This
frequency 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 is shown in Figure 6.1. DOVE's 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 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).
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Figure 6.1 Basic Receiving System for DOVE-OSCAR 17.
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 UoSAT-OSCAR 11
The same basic radio receiving system used to receive
signals from DOVE can be used to copy the telemetry from
UoSAT-OSCAR 11. 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 UoSAT-OSCAR 11 is different to that used for
DOVE due to the different data encoding (ASCII instead of
AX.25).
6.4 Receiving Signals from AMSAT-OSCAR 13
So far all the spacecraft considered have been low earth
orbits. AMSAT-OSCAR 13 however is in an elliptical orbit
with a high apogee. It also downlinks telemetry as BAUDOT
and ASCII data. While signals from 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 AMSAT-OSCAR 16, WEBER-OSCAR 18 and
LUSAT-OSCAR 19 as well as from Fuji-OSCAR 20 requires
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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
Figure 6-3 Alternate Basic Receiving System for PSK
Modulation.
OMNIDIRECTIONAL
ANTENNA
|
|
DOWNCONVERTER
|
|
SHORT WAVE PSK MODEM
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.
7.0 Decoding Spacecraft Telemetry
Apart from UoSAT-OSCAR 11 and WEBER-OSCAR 18 none of the OSCAR
spacecraft are designed for "Science" purposes. Their telemetry
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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. DOVE and
Fuji-OSCAR 20 transmit use ASCII Packet format, yet while DOVE
transmits the data in Hexadecimal format, Fuji-OSCAR 20 uses
Decimal Format. AMSAT-OSCAR 16, WEBER-OSCAR 18 and LUSAT-OSCAR 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.
AMSAT-OSCAR 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. UoSAT-OSCAR 11 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.
7.1 DOVE (DOVE-OSCAR 17)
DOVE-OSCAR 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. DOVE-OSCAR 17 is
licensed in Brazil with the callsign PT2PAZ. DOVE-OSCAR 17 was
built by AMSAT, occupies less than a cubic foot of space, masses
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8.5 kg and contains a V40 microprocessor and 8 Megabytes of RAM.
Essentially it is a loaded PC Clone in orbit. AMSAT-OSCAR 16,
DOVE-OSCAR 17, WEBER-OSCAR 18 and LUSAT-OSCAR 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. DOVE-OSCAR 17
transmits telemetry in several different packets as shown in
Figure 7-1.
Figure 7-1 A typical example of a DOVE-OSCAR 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
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
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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. Bisd 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
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
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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
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
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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-OSCAR 11
UoSAT-OSCAR 11 which was launched March 1, 1984, is similar to
and is a follow on to the now reentered UoSAT-OSCAR 9. 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 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,
UoSAT-OSCAR 11 seems to have been ignored by the majority of
radio amateurs and educational institutions.
UoSAT-OSCAR 11 carries four on-board experiments:- a Digital Com-
munications 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.
UoSAT-OSCAR 11 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 UoSAT-OSCAR 11, 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
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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 UoSAT-OSCAR 11. 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
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
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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 UoSAT-OSCAR 11 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.
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 UoSAT-
OSCAR 11 data showing some of the errors due to noise on the
downlink.
Figure 7.2-1 Example of a Received Raw UoSAT-OSCAR 11 Telemetry
Data Frame
00519D0141370267650361400404660503;4 6019E07045608040C08036C
10519C11298312000313056114069A15529A!6188;175452185905195058
20519F21220322662223000124001725000726093E27541528564D294681
30519E31041732287C33568B34007035217236276637393D38426B39455E
40649F41117242647343061044162545000146000247444748454949422x
50456251108D52634653284p54663215000056p00357451258447A59460E
60826A615FC1625F4A63334164440265160466174267700668000E69000F
UOSAT-2 9101281004625
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7.3 AMSAT-OSCAR 13
AMSAT-OSCAR 13 which was launched June 15, 1988 was built as a
joint venture between radio amateurs in the USA and in Germany
organized as the Radio Amateur Satellite Corporation (AMSAT).
AMSAT-OSCAR 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. AMSAT-OSCAR
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.
AMSAT-OSCAR 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 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.
Table 7.3-1 AMSAT-OSCAR 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
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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
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 7.3-2 AMSAT-OSCAR 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
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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
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
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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.
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 60
1 " NMI/
2 " Byte Clock
3 " Byte count reset
4 ---
5 Mode-S Beacon ON
6 " Squelch defeated
7 MSB " Squelch Hi Sensitivity
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, motore 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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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4E " O# (Orbit number and MA value)
4F Last ES-M Z last ES-pulse Motor side.
50 " O# (Orbit number and MA value)
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)
62 M-Out bit significance (OUT3, also L,S,J control)
0 LSB polarity Arm 1
1 polarity Arm 2
2 polarity Arm 3
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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 1st 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.
7.4 AMSAT-OSCAR 16, WEBER-OSCAR 18 and LUSAT-OSCAR 19
AMSAT-OSCAR 16, WEBER-OSCAR 18 and LUSAT-OSCAR 19 were launched
January 22, 1990 together with DOVE-OSCAR 17. AMSAT-OSCAR 16 and
LUSAT-OSCAR 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 UoSAT-OSCAR
11. LUSAT-OSCAR 19 is sponsored by AMSAT in Argentina. WEBER-
OSCAR 18 is an engineering project of the Center for Aerospace
Studies at Weber State University in Utah. It has the capability
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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. WEBER-
OSCAR 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 UoSAT-OSCAR 11, 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 17:04:18 LUSAT-1*>TIME-1:
PHT: uptime is 005/14:46:21. Time is Sun Jan 27 17:03:13 1991
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
27-Jan-91 16:41:11 N8ITP>PACSAT-1*>N8ITP [D]
27-Jan-91 16:41:12 N8ITP>PACSAT-1*>N8ITP (UA)
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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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 16:44:47 KC4EBR>PACSAT-1*>KC4SA:
What's shaking?>
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
27-Jan-91 17:09:22 LUSAT-1*>BCRXMT:
vmax=762523 battop=766771 temp=198465
14-Feb-91 03:02:29 N4HY>LUSAT-1*>N4HY (UA)
14-Feb-91 03:02:38 N4HY>LUSAT-1*>N4HY:
sdfjal;jfal;sdfjal;sfjalfj;aldfjl;asdfjl;asdfj;alfjal;sd
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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Table 7.4.2 AMSAT-OSCAR 16 Telemetry Decoding Equations
Spacecraft: PACSAT-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: +9.202 -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: +2.035 +0.0312 0.000 Volts
20 +8.5V Bus: +5.464 +0.0184 0.000 Volts
21 +10V Bus: +7.650 +0.0250 0.000 Volts
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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: -0.02345 +0.00355 0.000 Amps
2E BCR Output Cur:+0.00869 +0.00303 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 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 TX Out: -0.0088 +0.00435 0.000 Watts
3A S band HPA Temp 0.000 +1.000 0.000 Counts
Table 7.4.3 WEBER-OSCAR 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)
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
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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
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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38 +Z Array Temp: +0.0000 +1.0000 0.000 Counts
Table 7.4.5 LUSAT-OSCAR 19 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
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
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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
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.
7.5 Fuji-OSCAR 20
Fuji-OSCAR 20 which was launched on February 7, 1990 is a
communications satellite in low earth orbit providing
simultaneous analog and digital communications capability. Fuji-
OSCAR 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,
Fuji-OSCAR 20 and the Deployable Boom and Umbrella Test (DEBUT)
spacecraft which is similar in shape and weight to Fuji-OSCAR 20.
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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.
Fuji-OSCAR 20 is similar in construction to Fuji-OSCAR 12. In
fact, much of it was originally constructed as a backup to Fuji-
OSCAR 12 and designated as JAS-1B. It has since been modified and
improved as a result of the lessons learned during the flight of
Fuji-OSCAR 12. Fuji-OSCAR 12 was known as Fuji-1 in Japan, so
this spacecraft is known by the Japanese as Fuji-2 and as Fuji-
OSCAR 20 by the rest of the world.
Fuji-OSCAR 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.
Fuji-OSCAR 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.
Fuji-OSCAR 12 was the same shape but only carried about 600
cells. This larger number of cells means that Fuji-OSCAR 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.
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Fuji-OSCAR 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
similar to those of Fuji-OSCAR 12. It consists of an inverted
hetrodyne 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. Fuji-OSCAR 20 is using the
callsign 8J1JBS and the beacons transmit telemetry in the same
manner as Fuji-OSCAR 12.
The digital transponder provides store-and-forward packet
communication using AX.25 link level protocol, version 2.
Stations who used Fuji-OSCAR 12 are able to use Fuji-OSCAR 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 Fuji-OSCAR
12 or the Microsats is needed to copy Fuji-OSCAR 20. The
downlink channel also carries packet telemetry.
The 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 Fuji-
OSCAR 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 Fuji-OSCAR 20 you don't need to use a
digipeater call. With the present version of the software, all
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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 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 Fuji-OSCAR 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
Fuji-OSCAR 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.
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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 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.
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Using the decoding data 423 can be 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
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 --- ---
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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
...........
M9: Message #9
YY/MM/DD is year/month/day, and HH:MM:SS is hour/minute/second,
all in UTC.
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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)
#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
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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 ------
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
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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
7.6 AMSAT-OSCAR 21 (RM-1)
AMSAT-OSCAR 21 (AO-21) was launched in February January 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.
AMSAT-OSCAR 21 is 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 AMSAT-OSCAR 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.
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According to the mutual agreement, Amsat-U-Orbita developed and
made the linear transponder, command radio link, telemetry
system, 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 will be situated in Molodechno at UC1CWA and in Moscow
at RK3KP. The ground command stations for Rudak-2 only will be
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.
AMSAT-OSCAR 21 is 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 AMSAT-OSCAR 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.
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Two sets of the equipment are installed aboard the satellite:
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 AMSAT-OSCAR 7 Mode B will testify.
The Transponder RF Frequency Assignments and Beacon Data for the
Primary Payloads are shown in Table 7-6.1, and those for the
Backup payload in Table 7.6-2. 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 UoSAT-OSCAR 11 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 AMSAT-OSCAR 13 downlink. As such you may
not be able to copy this telemetry.
Table 7.6-1 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 FO-20)
Transponders #1
Linear transponder: inversely hetrodined 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.
Uplink frequencies:
RX-1 435.016 MHz 1200bps,FSK,NRZIC/Biphase-M
RX-2 435.155 MHz (AFC) 2400 bps,BPSK, Biphase-S
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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 7.6-2 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 heterodined 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 to +3 db gain using Right Hand circular Polarization. The 145
MHz transmitting antenna is a Half wave dipole. AMSAT-OSCAR 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
AMSAT-OSCAR 21 payload including the RUDAK weighs approximately
28 kg, the secondary payload weighs approximately 22 kg. Both
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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 7.6-3.
Table 7.6-3 AMSAT-OSCAR 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.
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
Examples of other frames copied and edited by G3ZCZ/W3 are
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 83
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 AMSAT-OSCAR 21 Digital 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
7.6-4. The raw digital telemetry is expected to show up on your
screen in the format shown in Table 7.6-5.
Table 7.6-4 Decoding Equations for AMSAT-OSCAR 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
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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 7.6-5 Expected Format of Raw AMSAT-OSCAR 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 7.6-6.
Table 7.6-6 Example of AMSAT-OSCAR 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:
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 85
--------------------------------------------+
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:
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)
26-Feb-91 02:37:36 RUDAK*>BEACON:
* RUDAK-II / AMSAT OSCAR 21/RM1
* Up: 435.016MHz (1200)
* 435.155MHz (2400)
* Mailbox=RUDAK Mheard=RUDAK-1
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 Fuji-OSCAR 12 PSK Telemetry Data Format. It is practically
identical to the Fuji-OSCAR 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
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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 86
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 thru row 2 column 7
(denoted #00 - #27 below)
y = 0 - F one byte Hex (System Status Data)
9 samples in row 2 column 8 thru row 2 column 9
(denoted #28a - #29c below)
s = 0 or 1 Binary Status Data
30 samples in row 3 thru 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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 87
#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
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)
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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#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 ---- ----
9.0 File formats
This section contains details of the contents of the different
files used by WHATS-UP.
9.1 Configuration File
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 station minimum usable pass time (e.g. 5)
8 early warning time (e.g. 5)
9 default Kepler file (e.g. whats-up.2ln)
10 UTC offset (e.g. EST = 5)
11 default directory path (e.g C:)
12 default extracted data file (e.g. whats-up.txt)
13 default file name with list of telemetry parameters to
extract file (e.g. ARRAYS)
14 TNC Type (e.g. PK-232)
15 PC serial port to TNC (e.g. 1)
16 PC serial port to Radio (e.g. 2)
17 PC serial port baud rate (e.g. 1200)
18 PC Serial port data bits (e.g. 8)
19 PC Serial port Stop bits (e.g. 1)
20 PC Serial port parity (e.g. 0)
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21 status (top) window color (e.g. 79)
22 Telemetry Page color (e.g. 14)
23 outgoing window color (e.g. 14)
24 incoming window color (e.g. 30)
25 prompt window color (e.g. 15)
26 alarm window color (e.g. 15)
27 bottom window color (e.g. 79)
28 Emphasis color (e.g. 14)
29 prompt color (e.g. 14)
30 option color (e.g. 78)
31 parameter changed color (e.g. 95)
32 parameter limit exceeded color (e.g. 14)
33 Orbit element window color
34 Orbit element window Orbit element window In range
color
35 Orbit element window early warning color
36 Orbit element window next one up color
37 Orbit alert dit time
38 Orbit alert note
39 Flag Sound
40 Doppler display Flag
41 The next few lines link the spacecraft configuration
files and contain:- SC ID, Spacecraft configuration
file name, autotune parameter.
The * that follows denotes the last line of SC ID data.
You must configure WHATS-UP before you try any Real Time
activity.
The items in 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.SYS)
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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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 Station minimum usable pass time
This item is the minimum time in minutes for a usable pass
for collecting data (e.g. 5).
9.1.8 Early warning time
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).
9.1.9 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.2ln).
9.1.10 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)
9.1.11 Default directory path (e.g C:)
This item is the directory path for the spacecraft capture-
to-disk (YYMMDD.S/C), spacecraft configuration (*.SYS) and
spacecraft operations schedule files (*.OPS).
9.1.12 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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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delimited format so that the data can be imported into a
spreadsheet package for further analysis (e.g. whats-
up.txt).
9.1.13 Default file name with list of telemetry parameters
to extract file
This item is the name of the file containing the channel
numbers to extract from a playback file for further analysis
(e.g. ARRAYS)
9.1.14 TNC Type
This item is the type of TNC or Multi-mode controller you
are using. WHATS-UP currently supports the PK-232.
9.1.15 Serial port to TNC
This item is the Communications port number between the TNC
and the PC (e.g. 2).
9.1.16 PC serial port to Radio
This item is the Communications port number between the TNC
and the Radio (e.g. 1). The parameters used are 4800
baud, 8 data bits, No parity. This item is hard coded to
meet the Kenwood standard.
9.1.17 PC serial baud rate
This item is the baud rate used between the TNC and the PC
(e.g. 1200).
9.1.18 PC port data bits
This item is the number of data bits used between the TNC
and the PC (e.g. 8).
9.1.19 PC port Stop bits
This item is the number of stop bits used between the TNC
and the PC (e.g. 1 or 2).
9.1.20 PC Port parity bits
This item is the parity setting used between the TNC and the
PC Values are defined as
0 No parity,
1 Odd,
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2 Even,
3 Mark,
4 Space.
The following items are the color values used for different
windows or messages.
9.1.21 status (top) window color (e.g. 79)
9.1.22 Telemetry Page color (e.g. 14)
9.1.23 outgoing window color (e.g. 14)
9.1.24 incoming window color (e.g. 30)
9.1.25 prompt window color (e.g. 15)
9.1.26 Alarm window color (e.g. 15)
9.1.27 Bottom window color (e.g. 79)
9.1.28 Emphasis color (e.g. 14)
9.1.29 Prompt color (e.g. 14)
9.1.30 Option color (e.g. 78)
9.1.31 Parameter changed color (e.g. 95)
9.1.32 Parameter limit exceeded color (e.g. 14)
9.1.33 Orbit element window color
9.1.34 Orbit element window Orbit element window In range
color
9.1.35 Orbit element window early warning color
9.1.36 Orbit element window next one up color
9.1.37 Orbit alert dit time
This item is the speed of the morse code annunciator used to
alert you of satellite AOS, EWT and LOS.
9.1.38 Orbit alert note
This item is the tone of the morse code annunciator used to
alert you of satellite AOS, EWT and LOS.
9.1.39 Flag Sound
This item controls the sounds coming from the PC. A 1 is
on, 0 is off.
9.1.40 Doppler display Flag
This item determines the type of Doppler display as
follows:-
0 display beacon frequency,
1 display Doppler shift.
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9.1.41 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. The lines contain data
as shown below.
UO-11,UOSAT11.SYS, 0
AO-13,OSCAR13Z.SYS,0
AO-16,PACSAT.SYS, 0
DO-17,DOVE.SYS, 1
WO-18,WEBER.SYS, 0
LO-19,LUSAT.SYS, 2
FO-20,FUJI.SYS, 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.
9.1.42 * Comment line
This line must be present and signals WHATS-UP that the
default parameters have been read and that the following
lines contain commands to be sent to the TNC on starting up
the program.
9.1.43 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
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 94
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 '.SYS'. Examples are
'DOVE.SYS' and 'Fuji20.SYS'. 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 contents of the SPACECRAFT.SYS file are as described
below.
9.2.1 Spacecraft ID.
This is the call sign of the spacecraft. For example,
Spacecraft ID
DOVE-OSCAR 17 DOVE-1
Fuji-OSCAR 12 8J1JAS
Fuji-OSCAR 20 8J1JBS
In the case of the Microsats and Fuji-OSCAR 12/20, and any
other using packet telemetry, WHATS-UP searches the packet
headers to detect the spacecraft by this callsign.
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-OSCAR 11 U11
Fuji-OSCAR 12 F12
AMSAT-OSCAR 13 O13
AMSAT-OSCAR 16 O16
DOVE-OSCAR 17 D17
WEBER-OSCAR 18 W18
LUSAT-OSCAR 19 L19
Fuji-OSCAR 20 F20
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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
FO-20
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 TNC configuration Code
This item tells WHATS-UP how to configure the PK-232 for the
spacecraft as follows:-
0 N/A - illegal value
1 FM Packet 1200 baud
2 RTTY BAUDOT 50 baud
3 ASCII 1200 baud
4 PSK Packet 1200 baud
5 FM Packet 1100 baud
6 CW 20 words per minute
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9.2.9 Modulation
This is the type of modulation used by the spacecraft.
Current options are :-
F FM
P PSK.
9.2.10 Data Type
This is the type of data downlinked by the spacecraft.
A ASCII as used by UoSAT-OSCAR 11 and AMSAT-OSCAR 13.
P Packet as used by DOVE-OSCAR 17, Fuji-OSCAR 20 and the
Microsats.
9.2.10 Receiver Type
This is the manufacturer of the radio receiver you are
using. This version of WHATS-UP only supports the Kenwood
series.
9.2.11 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.
9.2.12 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
9.2.13 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, TLM_Dec, TLM_Limit_Check,
TLM_Limit_Low, TLM_Limit_High, TLM_Negative_Blank.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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Each item is described in the following sections.
9.2.13.1 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.
9.2.13.2 TLM_Segment_ID
This is the segment identifier as described in Section
9.2.13.99 below.
9.2.13.3 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.')
9.2.13.4 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 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 form Y=(N+a)/b.
AMSAT-OSCAR 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
Y = A*N^2 + B*N + C,
where: N = raw telemetry data value
A, B, C = Equation Coefficients; Y, N are decimal
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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 AMSAT-OSCAR 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.
9.2.13.5 TLM_Ceof_C
This item is the equation Coefficient C.
9.2.13.6 TLM_Ceof_B
This item is the equation Coefficient B.
9.2.13.7 TLM_Ceof_A
This item is the equation Coefficient A.
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9.2.13.8 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.
9.2.13.9 TLM_Page
This item is the Display page number. A 0 is a 'wild
card' which will be displayed on every page.
9.2.13.10 TLM_Row
This item is the Display page row. It identifies which
row in the screen the data element will be displayed.
9.2.13.11 TLM_Col
This item is the Display page column. It identifies
which column in the screen the data item will be
displayed.
9.2.13.12 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.
9.2.13.13 TLM_Dec
This item defines the number of digits after the
decimal point in the display.
9.2.13.14 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]).
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9.2.13.15 TLM_Limit_Low
This item is the Low limit value (e.g. -4.00).
9.2.13.17 TLM_Limit_High
This item is the High limit value (e.g. +10.6).
9.2.13.18 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.
9.2.13.99 The Telemetry Identifier Line
The Telemetry identifier line has the same format as a
regular line, but contains different parameters as follows:
9.2.13.99.1 The Line Identifier
This item has to be '99' to identify the telemetry
identifier line.
9.2.13.99.2 The Segment Identifier
This is used when the spacecraft transmits telemetry
in more than one segment. It contains the segment
identifier showing which segment the channel is down
linked in.
9.2.13.99.3 Spare/Not Used
9.2.13.99.4 Location of Segment Identifier in Line
This item contains the location of the segment
identifier in the first line of the telemetry data.
9.2.13.99.5 Spare/Not Used
9.2.13.99.6 Spare/Not Used
9.2.13.99.7 Spare/Not Used
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9.2.13.99.8 Segment Identifier String
This item is the segment identifier string as follows.
9.2.13.99.82.1 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.
9.2.13.99.8.2 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.
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
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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.
AMSAT-OSCAR 13 RTTY Telemetry is transmitted
in the form of Z blocks shown below.
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
Note the spacing between the lines and the non
telemetry information at the end of the block.
UoSAT-OSCAR 11's ASCII telemetry looks
different, so WHATS-UP is told where to look
for the telemetry by the following items.
9.2.13.99.9 Spare
9.2.13.99.10 Number of Lines
This item is used in non packet telemetry to
tell WHATS-UP how many lines of data are in a
frame.
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9.2.13.99.11 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.
9.2.13.99.12 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.
9.2.13.99.13 Header Lines
This item is used in non packet telemetry to
tell WHATS-UP how many lines there are in the
header.
9.2.13.99.14 Header Display Flag
This item tells WHATS-UP to display the non
packet telemetry header . A '1' means display
it, a '0' means do not display it.
9.2.14 Digital Telemetry Status Channels
The next set of lines instruct WHATS-UP how to display
digital telemetry status in the Fuji-OSCAR 20 frame. Digital
status channels contain a number of status points. Fuji-
OSCAR 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,
Status_OFF_Text, Status_ON_Color, Status_OFF_Color.
Each item is described in the following sections.
9.2.14.1 Status_Channel
This is the channel number of the digital status
telemetry data in the frame. Each entry must be two
digits.
9.2.14.2 Status_Display_Page
This item is the Display page number. A 0 is a 'wild
card' which will be displayed on every page.
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9.2.14.3 Status_Text
This is the text that is displayed in the page.
9.2.14.4 Status_Bit_Mask
This is the bit mask to mask out the position of the
desired bit. The masks are in decimal. ie. 1, 10 and
100.
9.2.14.5 Status_Row
This item is the Display page row. It identifies which
row in the screen the data element will be displayed.
9.2.14.6 Status_Col
This item is the Display page column. It identifies
which column in the screen the data item will be
displayed.
9.2.14.7 Status_ON_Text
This item is the text that is displayed when the
spacecraft telemetry contains a 1 value.
9.2.14.8 Status_OFF_Text
This item is the text that is displayed when the
spacecraft telemetry contains a 1 value.
9.2.14.9 Status_ON_Color
This item is the color the text is displayed in when
the spacecraft telemetry contains a 1 value.
9.2.14.10 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.SYS 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
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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".
9.2.15 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.
9.2.15.1 Packet_title
This item is the name of UNP address (e.g. TLM,WASH,
BCXRT).
9.2.15.2 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 AMSAT-OSCAR 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.
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5 AMSAT Microsat Binary TLM Packet Telemetry.
6 UoSAT-OSCAR 9/11 ASCII Telemetry.
9.2.15.3 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.
9.2.15.4 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.
9.2.15.5 Packet_Color
This item is the color that the raw packet data will be
displayed in.
9.2.15.6 Packet_Row
This item is the row position that the raw packet will
be displayed in, on the selected page.
9.2.15.7 Packet_Col
This item is the column position that the raw packet
will be displayed in, on the selected page.
9.2.15.8 Link_Page
This item is the Display page for the cumulative count
of the packet type. The wild card '0' applies.
9.2.15.9 Link_Row
This item is the row position that the packet header
will be displayed in, on the selected page.
9.2.15.10 Link_Col
This item is the column position that the packet header
will be displayed in, on the selected page.
9.2.15.11 Binary_Byte_Count
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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
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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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"*** 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.
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
.
.
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"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.
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 (*.2LN)
The following outlines the "NASA Two-Line" Keplerian data format.
Data for each satellite consists of three lines in the following
format:
Example:
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:
COPYRIGHT Joe Kasser, G3ZCZ 1991.
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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)
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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 111
If you need to enter data in by hand, edit an AMSAT format file.
4116] B BID: ORBS-019.D
Date: 20 Jan 91 02:58:24 Z
From: N4QQ@N4QQ
To: ALL@AMSAT
Subject: Orbital Elements 019.MICROS
R:910120/0258z 18616@N4QQ.MD.USA [Silver Spring,Md] Z:20901
From: N4QQ@N4QQ.MD.USA
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. A Typical file is shown below.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 112
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
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
AO AMSAT-OSCAR
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
11.0 References and Further Reading
The best book is The Satellite Experimenter's Handbook, Martin
Davidoff, K2UBC, ARRL 1990, 2nd Edition. Other articles of
interest are listed below.
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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP.DOC Release 1.00 Page 113
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.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
APPENDIX 1 Obtaining Further Information Page 114
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 (081) 989 6741.
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 ...
From WHATS-UP (c) G3ZCZ
COPYRIGHT Joe Kasser, G3ZCZ 1991.
APPENDIX 2 Amateur Radio Software by Joe Kasser G3ZCZ
PC-HAM 3.52
PC-HAM contains a number of programs some of which are described
below.
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 written in dBASE3, but a compiled
LOGBOOK.EXE file is supplied together with the source code.
CONTEST
Keeps Dupes in memory, logs QSO's to disk in format which can be
processed by the LOGBOOK package.
CQSS
Sweepstakes game. 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. Program is
based on the one described in detail in 'Software for Amateur
Radio' by Joe Kasser G3ZCZ, published by TAB Books, Blue
Ridge Summit, PA. 17214.
WHATSON
Predict HF Propagation. Contest mode with printout to whole world
at hourly intervals. Needs BASIC
LAN-LINK 1.59
LAN-LINK will capture AMSAT related bulletins from packet
radio BBSs automatically. Amongst its many features are :-
Zmodem binary file transfer capability.
Function key and Menu driven.
Automatic logbook entries for Packet and Mailbox/Beacon
Mode AMTOR Connects, semiautomatic logbook entries for
other modes. Log file can be processed by the Logbook Package
of PC-HAM. Contest operation, sends standard message
and automatically increments QSO count. Automatic optimized
configuration of the TNC for each communications mode.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
APPENDIX 2 Amateur Radio Software by Joe Kasser G3ZCZ
All mode Function key 'OVER' feature (End). There are 10
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.
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 Mode in multiconnect situations. Bridge Mode
in multiconnect situations. Path determination to DX
station via :QMH:. 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. Screen indication of connect by desired station
(target call).
Automatic Beacon Mode CQ caller. Will call CQ repetitively
and either work the connect and keep going after disconnect
or signal you when a reply is received. SAREX special
features. :QRA: trigger to determine who else is on channel.
Automatic AMTOR SELCAL determination.
Function key change from monitoring AMTOR FEC CQ's to QSO's
in progress (chirpcopy). NAVY MARS RTTY file transmitting
protocols for the PK-232. Log files in dBASE 3 format. AND
MORE !!!!!
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP APPENDIX 3 SHAREWARE Page 117
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 that 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 Rd, Muskegon, MI. 49442, 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 (90 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.
* 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 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)
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP APPENDIX 3 SHAREWARE Page 118
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 1991.
WHATS-UP 1.00 Registration form
WHATS-UP 1.00 Registration Fee $35.00
LAN-LINK 1.59 Registration Fee $35.00
PC-HAM 3.52 Registration Fee $36.50
Register them all for $95.00.
Evaluation Copies free, you pay only for the disk/postage. For an
evaluation copy (unregistered full blown version) of each
software send a formatted disk and SASE to Joe Kasser. Overseas
users, send $5.00 ($10.00 covers all three) instead. Try the
software first, and only register your copy if you make use of
it.
To: Joe Kasser G3ZCZ, P O BOX 3419, SILVER SPRING, MD 20918.
CALL ________________ TODAY'S DATE _____________
NAME ______________________________________________
ADDRESS ___________________________________________
___________________________________________
CITY ___________________________________________
STATE _________ POSTCODE ______________________
TNC TYPE _____________________ Home BBS __________
I enclose a check for ______. Please send me the latest version
of ______________, and register me as a user.
I enclose a disk/sase or $5.00. Please send me the latest version
of ______________________ to evaluate. If I like it and use it, I
plan to become a registered user.
Disk Size 5.25 _____(360k) 5.25 _____(1.2Mb) 3.5 ______(730k)
I AM NOT/AM currently using Shareware Version _____
which I obtained from _________________________________________.
Signature _______________________
Classroom Registration 6 to 10 copies $195.00.
Radio Club Registrations 10 or more copies, 10% discount.
50 or more copies, 25% discount.
Designate one contact person to receive classroom or club
registered updates, and supply a list of names and call signs
of club members who will be using the Registered Club Copy.
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP Index Page 120
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP Index Page 121
Access, 2, 9, 14, 72, 85, 116
Acquire, 19, 90
Acquisition, 6, 11, 19, 43, 88, 90, 112
AFSK, 55, 80
Alarm, 6, 18, 89, 92
Alert, 6, 89, 92, 116
Altitude, 6, 14, 19, 35, 38, 40, 88, 90
AMSAT-OSCAR, 1, 5, 10, 12, 31, 40, 41, 42, 43, 44, 45, 47, 49, 50,
56, 57, 62, 65, 78, 79, 80, 81, 82, 83, 84, 94, 95, 96, 97, 98,
102, 105, 112
Analog, 17, 56, 69, 71, 72, 81, 82, 86
Antenna, 6, 43, 44, 46, 47, 48, 58, 59, 60, 61, 71, 81, 88, 90, 112
AOS, 11, 19, 20, 33, 43, 92, 93, 112
Apogee, 29, 35, 38, 39, 43, 47, 70, 78
Array, 12, 51, 52, 60, 65, 66, 67, 68, 69, 73, 76, 78, 86, 97
Azimuth, 19, 43
Band, 5, 44, 46, 47, 48, 49, 52, 63, 66, 112
BPSK, 80, 81
Capture-to-disk, 4, 11, 12, 14, 18, 26, 32, 89, 90, 94
Checksum, 49, 55
Clock, 5, 12, 19, 32, 33, 60, 86, 108
Coefficients, 51, 65, 66, 68, 97, 98
Color, 5, 6, 8, 11, 16, 17, 18, 20, 32, 33, 89, 92, 94, 96, 103,
104, 105, 106
Colors, 11, 13, 16, 17, 18, 20, 33, 116
Column, 12, 20, 86, 99, 104, 106, 110
Command, 9, 10, 15, 18, 23, 31, 64, 72, 79, 82, 83, 84, 86, 116
Configuration, 1, 3, 4, 5, 6, 7, 12, 13, 16, 17, 26, 27, 31, 32,
47, 79, 88, 89, 90, 93, 95, 96, 108, 115
Display, 1, 3, 6, 7, 10, 11, 12, 13, 16, 17, 18, 19, 20, 21, 22,
23, 25, 26, 27, 28, 29, 31, 33, 53, 56, 63, 77, 78, 83, 89, 92,
96, 99, 103, 104, 106, 116
Dit, 6, 89, 92
Doppler, 1, 4, 6, 8, 19, 26, 27, 29, 89, 92, 95, 107, 108, 109
DOVE, 5, 7, 13, 15, 17, 26, 30, 31, 44, 45, 46, 47, 49, 50, 51, 52,
63, 88, 89, 93, 94, 97, 101, 107, 109, 112
DOVE-OSCAR, 1, 5, 10, 12, 42, 43, 47, 49, 50, 62, 94, 96, 112
Downlink, 10, 41, 42, 48, 49, 55, 56, 63, 71, 72, 80, 81, 84
Eccentricity, 5, 29, 36, 38, 110, 111
Edit, 3, 4, 12, 13, 14, 22, 23, 24, 25, 26, 27, 28, 33, 110, 111,
116
Elevation, 6, 19, 43, 88, 90
Epoch, 5, 29, 36, 39, 110, 111
Equations, 9, 10, 49, 50, 51, 56, 57, 63, 65, 66, 68, 73, 75, 76,
82, 83, 85, 86, 97
Event, 62, 80, 116
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP Index Page 122
EWT, 19, 20, 21, 33, 92, 93, 112
Extract, 1, 3, 6, 12, 20, 21, 22, 88, 91, 107
FSK, 42, 44, 54, 61, 80, 81, 112
Fuji-OSCAR, 1, 5, 10, 42, 43, 45, 47, 49, 69, 70, 71, 72, 73, 74,
75, 76, 77, 78, 85, 86, 87, 94, 96, 103, 112
Hex, 11, 50, 51, 65, 66, 68, 76, 84, 86
Hexadecimal, 49, 50, 51, 55, 56, 75, 97, 105
Inclination, 5, 29, 35, 36, 37, 43, 70, 78, 110, 111
Interactive, 3, 11, 16, 18, 21, 22
J-pole, 46
Kenwood, 1, 11, 13, 23, 29, 91, 96
Kepler, 6, 8, 36, 88, 90, 109
Keplerian, 6, 15, 16, 19, 22, 26, 28, 93, 95, 109
LAN-LINK, 18, 115, 116, 119
Latitude, 5, 14, 70, 88, 89
Launch, 9, 10, 34, 69, 70, 79, 82, 84, 110, 113
Limit, 3, 6, 7, 11, 13, 16, 18, 89, 92, 96, 99, 100
Longitude, 6, 14, 88, 90
LUSAT-OSCAR, 1, 5, 10, 42, 43, 45, 47, 49, 50, 62, 68, 94, 112
Microsat, 1, 4, 13, 15, 30, 31, 40, 63, 101, 105, 106, 112
Mode-B, 57, 59, 112
Modem, 32, 45, 46, 48, 54, 55, 71, 83, 95, 112
Octal, 73
Orbit, 3, 4, 6, 10, 19, 20, 21, 23, 28, 29, 34, 35, 36, 37, 38, 39,
40, 41, 42, 44, 47, 50, 53, 56, 61, 62, 69, 70, 71, 78, 79, 80,
89, 90, 92, 93, 108, 113
Packet, 1, 2, 3, 4, 8, 12, 17, 18, 21, 30, 31, 32, 45, 47, 49, 50,
53, 71, 72, 80, 94, 95, 96, 102, 103, 105, 106, 107, 110, 111,
115, 116
Parameter, 6, 7, 11, 14, 54, 82, 83, 84, 89, 92, 94, 96
Perigee, 5, 29, 35, 36, 38, 39, 41, 43, 62, 70, 110, 111
Period, 19, 29, 36, 39, 43, 70, 78, 79, 117, 118
PgDn, 24, 27, 28
PgUp, 24
Playback, 3, 4, 11, 12, 13, 16, 20, 21, 22, 23, 27, 90, 91, 96, 107
Propagation, 49, 115
PSK, 5, 31, 32, 42, 44, 45, 47, 48, 52, 56, 61, 66, 67, 69, 71, 72,
74, 75, 77, 80, 83, 84, 85, 87, 95, 96, 104, 109, 112
RAAN, 5, 29, 36, 37, 38
Real-time, 11, 18, 22, 23, 53, 54, 96
COPYRIGHT Joe Kasser, G3ZCZ 1991.
WHATS-UP Index Page 123
Row, 7, 8, 12, 75, 86, 96, 99, 103, 104, 105, 106
RTTY, 1, 4, 12, 30, 31, 45, 56, 81, 95, 97, 102, 112, 116
RUDAK, 58, 59, 79, 80, 81, 83, 84, 85
Satellite, 1, 9, 10, 35, 36, 37, 38, 39, 40, 44, 46, 56, 69, 70,
71, 72, 79, 80, 82, 92, 109, 110, 111, 112, 113, 114
Scanner, 9, 44, 46, 47
Schedule, 4, 30, 32, 42, 56, 57, 90, 102, 112
Segment, 7, 96, 97, 99, 100, 101, 102, 107
Semimajor, 5, 36, 38, 39
Semiminor, 38
Spacecraft, 1, 3, 4, 5, 6, 8, 9, 10, 11, 12, 13, 15, 16, 18, 19,
20, 21, 22, 23, 26, 27, 28, 29, 30, 31, 32, 33, 35, 37, 38, 39,
40, 41, 42, 43, 44, 45, 46, 47, 48, 49, 51, 53, 54, 56, 63, 65,
66, 68, 69, 70, 71, 72, 78, 80, 81, 82, 85, 88, 89, 90, 93, 94,
95, 96, 99, 100, 104, 107, 111, 113, 114
Status, 1, 6, 7, 8, 9, 11, 12, 14, 16, 17, 32, 50, 53, 56, 58, 61,
64, 72, 73, 74, 75, 76, 77, 82, 83, 86, 87, 89, 92, 95, 103, 104,
105, 117
Telemetry, 1, 2, 3, 5, 6, 7, 8, 9, 10, 11, 12, 13, 15, 16, 17, 18,
20, 27, 31, 32, 42, 46, 47, 48, 49, 50, 51, 52, 53, 54, 55, 56,
57, 63, 65, 66, 68, 71, 72, 73, 75, 76, 77, 79, 80, 81, 82, 83,
84, 85, 86, 87, 88, 89, 91, 92, 94, 96, 97, 99, 100, 101, 102,
103, 104, 105, 106, 107, 113
Turnstile, 43, 44, 46, 71, 112
UoSAT-OSCAR, 1, 5, 10, 31, 40, 41, 42, 43, 44, 45, 47, 48, 49, 53,
54, 55, 62, 63, 80, 94, 96, 102, 106, 112, 113
Valid, 15, 39, 72, 86, 100
WEBER-OSCAR, 1, 5, 10, 42, 43, 45, 47, 48, 49, 50, 62, 63, 66, 94,
112
Yagi, 44
COPYRIGHT Joe Kasser, G3ZCZ 1991.
