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29-Jul-93 Daily File Collection
These files were added or updated between 28-Jul-93 at 21:00:00 {Central}
and 29-Jul-93 at 21:00:30.
=--=--=START=--=--= NASA Spacelink File Name:930729.SHU
KSC SHUTTLE STATUS REPORT 7/29/93
KENNEDY SPACE CENTER SPACE SHUTTLE STATUS REPORT
Thursday, July 29, 1993
KSC Contact: Bruce Buckingham
MISSION: STS-51 ACTS-TOS/ORFEUS-SPAS
VEHICLE: Discovery/OV-103 ORBITAL ALTITUDE: 184 miles
LOCATION: Pad 39-B INCLINATION: 28.45 degrees
LAUNCH DATE: August 4, 1993 CREW SIZE: 5
LAUNCH WINDOW: 9:06 - 10:14 a.m. EDT
KSC LANDING DATE/TIME: August 13/14 (7:05 a.m. on the 13th)
MISSION DURATION: 8 days/22 hours + 1 day (An additional day on
orbit may be granted if orbiter cryogenics allow.)
IN WORK TODAY:
* Service newly replaced right hand solid rocket booster
auxiliary power unit with hypergolic fuels
* Hot fire SRB hydraulic power unit (8 p.m. tonight)
* Advanced Communications Technology Satellite battery charging
* Countdown preparations
WORK SCHEDULED:
* Reconnect ordnance devices
* Aft engine compartment closeouts
* Vehicle power down on Saturday
* Countdown begin 9:30 a.m. Sunday, Aug. 1
* Close payload bay doors for flight
WORK COMPLETED:
* Remove and replace right hand solid rocket booster auxiliary
power unit
* Power reactant storage and distribution system purges
MISSION: STS-58 Spacelab Life Sciences - 2
VEHICLE: Columbia/OV-102 ORBITAL ALTITUDE: 176 miles
LOCATION: OPF bay 2 INCLINATION: 39.00 degrees
MISSION DURATION: 14 days CREW SIZE: 7
TARGET LAUNCH PERIOD: Early/Mid September
LAUNCH TIME: Approximately 11:30 a.m. EDT
LAUNCH WINDOW: 2 hours, 30 minutes
IN WORK TODAY:
* Orbiter aft closeouts
* Main engine securing, electrical interface and leak checks
* Main engine carrier panel installation
* External tank and solid rocket booster electrical mates in the
Vehicle Assembly Building
* Crew equipment interface test (Saturday)
WORK COMPLETED:
* Main engine heatshield installation
* Orbiter electrical system redundancy tests
MISSION: STS-61 Hubble Space Telescope
Servicing Mission
VEHICLE: Endeavour/OV-105 ORBITAL ALTITUDE: 356 miles
LOCATION: OPF bay 1 INCLINATION: 28 degrees
MISSION DURATION: 11 days CREW SIZE: 7
TARGET LAUNCH PERIOD: Early December 1993
IN WORK TODAY:
* 5th cryogenic tank set installation preparations
* Orbital maneuvering system functional checks
* Ammonia system leak and functional checks
* Payload integration tests
WORK SCHEDULED:
* Install 5th cryogenic tank set
* Main propulsion system leak and functional checks
WORK COMPLETED:
* Lower main and nose landing gear
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_2_5_22.TXT
GALILEO STATUS REPORTS 7/2-8/93
GALILEO MISSION DIRECTOR STATUS REPORT
POST-LAUNCH
July 2 - 8, 1993
SPACECRAFT
1. On July 6, a NO-OP command was sent to reset the command loss timer to 264
hours, its planned value for this mission phase.
2. On July 7, a periodic RPM (Retro-Propulsion Module) 10-Newton thruster
flushing maintenance activity was performed; all 12 thrusters were flushed
during the activity. Thruster flushing throughout the activity was nominal.
3. On July 7, the spacecraft, under stored sequence control, performed about a
12-degree unbalanced SITURN for the purpose of attitude maintenance. The Z
thrusters were used during the activity.
4. On July 7, cruise science Memory Readouts (MROs) were performed for the
Extreme Ultraviolet Spectrometer (EUV), Magnetometer (MAG), and Dust Detector
(DDS) instruments. Preliminary analysis indicates the data was received
properly.
5. On July 8, an Ultra-Stable Oscillator (USO) test was performed to verify
the health status of the USO and to collect gravitational red shift experiment
data; long term trend analysis is continuing.
6. On July 8, real-time commands were sent to modify System Fault Protection
(SFP) parameters and to turn the bay C/D shunt heater on. Specifically, the
SFP parameters were modified to turn the bay C/D shunt heater on and the
Photometric Calibration Target (PCT) heater No. 2 off in the event of sequence
termination.
7. The AC/DC bus imbalance measurements have not exhibited significant change
(greater than 25 DN) throughout this period. The AC measurement reads 18 DN
(4.1 volts). The DC measurement reads 156 DN (18.4 volts). These measurements
are consistent with the model developed by the AC/DC special anomaly team.
8. The Spacecraft status as of July 8, 1993, is as follows:
a) System Power Margin - 58 watts
b) Spin Configuration - Dual-Spin
c) Spin Rate/Sensor - 3.15rpm/Star Scanner
d) Spacecraft Attitude is approximately 15 degrees
off-sun (lagging) and 7 degrees off-earth (leading)
e) Downlink telemetry rate/antenna- 40bps(coded)/LGA-1
f) General Thermal Control - all temperatures within
acceptable range
g) RPM Tank Pressures - all within acceptable range
h) Orbiter Science- Instruments powered on are the PWS,
EUV, UVS, EPD, MAG, HIC, and DDS
i) Probe/RRH - powered off, temperatures within
acceptable range
j) CMD Loss Timer Setting - 264 hours
Time To Initiation - 259 hours
UPLINK GENERATION/COMMAND REVIEW AND APPROVAL:
1. The EJ-3 (Earth-Jupiter #3) final profile design package was approved by
the Project on July 6, 1993. This sequence covers spacecraft activities from
August 27 to September 27, 1993 and includes the IDA closest approach on August
28 and the initial return of science data.
TRAJECTORY
As of noon Thursday, July 8, 1993, the Galileo Spacecraft trajectory
status was as follows:
Distance from Earth 393,869,200 km (2.63 AU)
Distance from Sun 384,238,100 km (2.57 AU)
Heliocentric Speed 72,700 km per hour
Distance from Jupiter 437,473,800 km
Round Trip Light Time 43 minutes, 54 seconds
SPECIAL TOPIC
1. As of July 8, 1993, a total of 71303 real-time commands have been
transmitted to Galileo since Launch. Of these, 65531 were initiated in the
sequence design process and 5772 initiated in the real-time command process.
In the past week, 9 real time commands were transmitted; 1 was initiated in the
sequence design and 8 were initiated in the real-time command process. Major
command activities included commands to reset the command loss timer and modify
system fault protection parameters.
GALILEO STATUS REPORT
July 7, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, the EJ-2 (Earth-Jupiter #2) sequence began. Tracking was
scheduled over DSS-63 (Madrid 70 meter antenna).
Today, July 7, 1993, a routine 10-Newton thruster flushing maintenance
activity and SITURN are being performed. Science memory readouts were also
scheduled. Tracking is scheduled over DSS-63.
Tomorrow, real-time commands are scheduled to modify system fault
protection parameters. A USO (Ultra Stable Oscillator) test is also scheduled.
Tracking is scheduled over DSS-63.
GALILEO STATUS REPORT
July 8, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, a routine 10-Newton thruster flushing maintenance activity and
SITURN was performed, as planned. Science memory readouts were also scheduled.
Tracking was scheduled over DSS-63 (Madrid 70 meter antenna).
Today, July 8, 1993, real-time commands are scheduled to modify system
fault protection parameters. A USO (Ultra Stable Oscillator) test is also
scheduled. Tracking is scheduled over DSS-63.
Tomorrow, the SSI (Solid State Imaging camera) is scheduled to be turned
on for the upcoming optical navigation activities. Collection of acquisition
sensor data is also scheduled. Tracking is scheduled over DSS-63.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_2_5_23.TXT
GALILEO STATUS REPORTS 7/9-15/93
GALILEO MISSION DIRECTOR STATUS REPORT
POST-LAUNCH
July 9 - 15, 1993
SPACECRAFT
1. On July 9, the Solid State Imaging (SSI) camera was powered on in
preparation for the optical navigation activities scheduled to begin the
following week. The instrument memories were readout and verified to be
nominal.
2. On July 9, Acquisition Sensor (AS) data was collected and is being analyzed
for a possible AS parameter update scheduled for July 16.
3. At the beginning of the DSS-14 (Goldstone 70 meter antenna) track on July
10, numerous telemetry channels were in alarm. Further analysis of the
telemetry channels indicated the spacecraft had entered safing and the Command
and Data Subsystem (CDS) A string was down. Real-time commands were sent to
reset the CDS telemetry indicator which confirmed the expectations that the A
string down was caused by a spurious transient bus reset signal similar to
those observed on March 26, 1991; May 2, 1991; July 19, 1991; June 11, 1993;
and June 17, 1993. Analysis of spacecraft telemetry data indicated that the
anomaly occurred at about 1316 PDT on July 10 during a non-track period.
Real-time commands were then sent to reconfigure the CDS A string for
recovery and restart. All commands were properly received and executed by the
spacecraft and the CDS A string was brought back on-line and fully redundant
CDS operation was restored at approximately 1200 PDT on July 11, 1993.
Real-time commands were also sent to turn the Heavy Ion Counter (HIC) high
voltage on to protect its detectors.
4. On July 12, at the beginning of the DSS-63 (Madrid 70 meter antenna) pass,
the DSN (Deep Space Network) locked up on the low frequency subcarrier but no
telemetry was being processed. These responses indicated the spacecraft had
again entered safing and the CDS String A was down. Real-time commands were
sent to reconfigure downlink telemetry to the CDS B string. Subsequently,
telemetry lock was achieved and the data confirmed that the spacecraft had
entered safing and the CDS A string was down. Subsequent real-time commands
were sent to reset the CDS telemetry indicator, thus confirming the A string
down was caused by another spurious transient bus reset signal. Analysis of
spacecraft telemetry data indicated that the anomaly occurred at about 1837 PDT
on July 11 during a non-track period.
Real-time commands were then sent to reconfigure the CDS A string for
recovery and restart. All commands were properly received and executed by the
spacecraft and the CDS A string was brought back on-line and fully redundant
CDS operation was restored at approximately 2000 PDT on July 12, 1993.
Real-time commands were also sent to turn the Heavy Ion Counter (HIC) high
voltage on to protect its detectors. The high rate telemetry was switched to
the CDS B string and the low rate telemetry to the CDS A string. This change
will prevent the disruption of spacecraft telemetry in the event of another
spurious transient CDS Bus A reset. Real-time commands were sent to turn the
Two-Way Non-Coherent (TWNC) off and Delayed Action Commands (DACs) were sent to
turn S-band ranging on and off on July 15.
5. On July 15, a navigation cycle began and will complete on July 16 providing
near-continuous acquisition of two-way doppler and ranging during four
consecutive passes of the spacecraft over DSS-63, DSS-14, DSS-43 (Canberra 70
meter antenna), and then back to DSS-63.
6. The AC/DC bus imbalance measurements have not exhibited significant change
(greater than 25 DN) throughout this period. The AC measurement reads 18 DN
(4.1 volts). The DC measurement reads 159 DN (18.8 volts). These measurements
are consistent with the model developed by the AC/DC special anomaly team.
7. The Spacecraft status as of July 15, 1993, is as follows:
a) System Power Margin - 59 watts
b) Spin Configuration - Dual-Spin
c) Spin Rate/Sensor - 3.15rpm/Star Scanner
d) Spacecraft Attitude is approximately 17 degrees
off-sun (lagging) and 5 degrees off-earth (leading)
e) Downlink telemetry rate/antenna- 40bps(coded)/LGA-1
f) General Thermal Control - all temperatures within acceptable range
g) RPM Tank Pressures - all within acceptable range
h) Orbiter Science- Instruments powered on are the PWS, EPD, SSI, HIC
and DDS
i) Probe/RRH - powered off, temperatures within acceptable range
j) CMD Loss Timer Setting - 264 hours
Time To Initiation - 195 hours
GDS (Ground Data Systems):
1. Galileo Ground Data System (GDS) tests of MGDS V18.1 Command (CMD) were
conducted on July 8 and July 14 with DSS-45 and DSS-42 (Canberra 34 meter
antennas), respectively. The tests went well with V18.1 CMD being exercised
thoroughly. During the test with DSS-45 a problem with the CPA (Command
Processor Assembly) was observed. The CPA was reloaded and the rest of the
test proceeded without incident. These tests also validated the flow of
monitor 5-15 data through the MGDS. Even though all functional test objectives
were achieved, the tests were not conducted using the actual Galileo
operational PBD and CMD central hardware (H/W) configuration. The July 14 test
was the last scheduled GDS test prior to the August 1 start of MCCC/MGDS
Command parallel operations, but due to the lack of a complete flight
configuration additional GDS tests are being scheduled. The first of these
additional GDS tests are scheduled for July 19 with DSS-42.
TRAJECTORY
As of noon Thursday, July 15, 1993, the Galileo Spacecraft trajectory
status was as follows:
Distance from Earth 415,018,900 km (2.78 AU)
Distance from Sun 392,397,500 km (2.62 AU)
Heliocentric Speed 71,400 km per hour
Distance from Jupiter 430,808,300 km
Round Trip Light Time 46 minutes, 14 seconds
SPECIAL TOPIC
1. As of July 15, 1993, a total of 71892 real-time commands have been
transmitted to Galileo since Launch. Of these, 65531 were initiated in the
sequence design process and 6361 initiated in the real-time command process.
In the past week, 589 real time commands were transmitted of which all were
initiated in the real-time command process. Major command activities included
commands to bring the CDS A string up after spurious bus reset signals, turn
the HIC high voltage on, switch the high rate telemetry to the CDS B string and
the low rate telemetry to the CDS A string, and turn the TWNC off and the
S-band ranging on and off.
GALILEO STATUS REPORT
July 12, 1993
On July 10, 1993 after DSS-14 (Goldstone 70 meter antenna) had acquired
the signal from the Galileo spacecraft at 2105Z, it was discovered that the
spacecraft had entered safemode. It was determined that the CDS-A (Command and
Data Subsystem A) had failed and the spacecraft had swapped to CDS-B. The cause
of this event was a transient signal as in the previous safing events. The
spaceraft is being reconfigured to the state required to perform the EJ-2
(Earth-Jupiter #2) sequence. The current spacecraft configuration as of July
12, 1993 1400Z: LGA-1 (Low Gain Antenna), 22.5 KHZ telemetry subcarrier, TWNC
(Traveling Wave Non Coherent) on, and ranging channel off.
GALILEO STATUS REPORT #2
July 12, 1993
The Galileo Spacecraft appears to have entered safing with the CDS-A
(Command and Data Subsystem A) string down.
Over the weekend, at the beginning of the DSS-14 (Goldstone 70 meter
antenna) track on Saturday, telemetry had indicated that the spacecraft had
entered safing and the CDS-A string had gone down. Commands were sent to
reconfigure the CDS-A string for recovery and restart. Full redundant CDS
operations were restored by Sunday afternoon. Tracking was scheduled on DSS-14
on Saturday and DSS-63 (Madrid 70 meter antenna) on Sunday.
Today, July 12, 1993, at the beginning of the DSS-63 track, data appears
to indicate that the spacecraft has again has entered safing and the CDS-A
string has gone down. In this particular configuration, telemetry data cannot
be processed. Commands are currently being planned to reconfigure the CDS-A
string for recovery and restart. Tracking is scheduled over DSS-63 and DSS-14.
GALILEO STATUS REPORT
July 13, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, at the beginning of the DSS-63 (Madrid 70 meter antenna) track,
data indicated that the spacecraft had again entered safing and the CDS-A
(Command and Data Subsystem A) string had gone down. Commands were sent to
reconfigure the CDS-A string for recovery and restart. Full redundant CDS
operation was restored Monday evening. Tracking was scheduled over DSS-63 and
DSS-14 (Goldstone 70 meter antenna).
Today, July 13, 1993, no spacecraft activity is scheduled. Tracking is
scheduled over DSS-14.
Tomorrow, no spacecraft activity or tracking is scheduled.
GALILEO STATUS REPORT
July 15, 1993
The Galileo Spacecraft is operating in the dual-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, no spacecraft activity or tracking was scheduled.
Today, July 15, 1993, a navigation cycle is scheduled to begin. Tracking
is scheduled over DSS-63 (Madrid 70 meter antenna), DSS-14 (Goldstone 70 meter
antenna) and DSS-43 (Canberra 70 meter antenna).
Tomorrow, real-time commands are scheduled to update AACS (Attitude and
Articulation Control Subsystem) parameters and to perform memory readouts for
the SSI (Solid State Imaging camera). Tracking is scheduled over DSS-63 and
DSS-43.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_2_5_24.TXT
GALILEO MISSION STATUS REPORTS 7/16-22/93
GALILEO MISSION DIRECTOR STATUS REPORT
POST-LAUNCH
July 16 - 22, 1993
SPACECRAFT
1. On July 16, real-time commands were sent to update the attitude control
subsystem flight software parameters for the acquisition sensor. These
parameters were updated using the acquisition sensor data gathered on July 9.
Additionally, the spin rate and pointing deadbands were returned to their EJ-2
(Earth-Jupiter) sequence values. The Spacecraft safing changes the spin rate
and pointing deadbands. Before sequence controlled operations can be resumed
the values must be consistent.
2. On July 16, real-time commands were sent to change the spacecraft spin
configuration from the dual-spin to the all-spin mode. This action was taken
to reduce the likelihood of another transient bus reset signal since all
related information to date suggests that the spacecraft in the dual-spin mode
is more susceptible to this anomaly.
3. On July 19, in preparation for the EJ-2 prime sequence memory load, a
science instrument mini-sequence was uplinked to reconfigure the spacecraft to
its appropriate state which had changed as a result of the Command and Data
Subsystem (CDS) bus reset anomalies on July 10 and 11. The mini-sequence was
uplinked and executed on the spacecraft without incident.
4. On July 19, Delayed Action Commands (DACs) were sent to turn the
Photometric Calibration Target (PCT) heater No. 1 off and PCT heater No. 2 on.
This heater configuration is required to preclude PCT contamination when
thrusters are fired in the EJ-2 prime sequence and to maintain the planned
power margin for Retro-Propulsion Module (RPM) tank temperature and pressure
control.
5. On July 19, real-time commands were sent to turn on a calibration tone for
the Plasma Wave Subsystem (PWS) B-antenna. This will provide B-antenna
performance information which will be used in the upcoming Jupiter sequence
planning.
6. On July 19, real-time commands were sent to select Track 2 for the DMS
(tape recorder). This configured the tape recorder for the start of the EJ-2
prime sequence and the upcoming optical navigation No. 2 activities.
7. On July 21, Delayed Action Commands (DACs) were sent to reconfigure the
spacecraft from the all-spin to the dual-spin mode on July 22 just prior to the
optical navigation No. 2 activities and then back to all-spin after the
shuttering activity had completed. The time in the dual-spin mode was
minimized to reduce the likelihood of another CDS bus reset anomaly.
8. On July 21, the EJ-2 prime sequence memory load was uplinked to the
spacecraft without incident. This sequence covers spacecraft activities from
July 22, 1993 to August 27, 1993 and includes IDA optical navigation images No.
2 through 5 and the IDA approach Trajectory Correction Maneuvers (TCMs).
Additionally, Memory Readouts (MROs) were performed for the Solid State Imaging
(SSI) camera to verify its status prior to the start of optical navigation
activities. The MROs indicated the SSI was operating nominally.
9. On July 22, the EJ-2 prime sequence memory load went active and optical
navigation No. 2 activities are in progress at the writing of this report.
Memory Readouts (MROs) of optical navigation No. 2 data are scheduled through
July 26, 1993.
10. The AC/DC bus imbalance measurements have not exhibited significant change
(greater than 25 DN) throughout this period. The AC measurement reads 18 DN
(4.1 volts). The DC measurement reads 153 DN (18.0 volts). These measurements
are consistent with the model developed by the AC/DC special anomaly team.
11. The Spacecraft status as of July 22, 1993, is as follows:
a) System Power Margin - 56 watts
b) Spin Configuration - All-Spin
c) Spin Rate/Sensor - 2.89rpm/Star Scanner
d) Spacecraft Attitude is approximately 18 degrees
off-sun (lagging) and 3 degrees off-earth (leading)
e) Downlink telemetry rate/antenna- 40bps(coded)/LGA-1
f) General Thermal Control - all temperatures within acceptable range
g) RPM Tank Pressures - all within acceptable range
h) Orbiter Science- Instruments powered on are the PWS,
EUV, UVS, EPD, MAG, SSI, HIC, and DDS
i) Probe/RRH - powered off, temperatures within acceptable range
j) CMD Loss Timer Setting - 264 hours
Time To Initiation - 235 hours
UPLINK GENERATION/COMMAND REVIEW AND APPROVAL:
1. The EJ-2 prime sequence memory load was approved by the Project on July 20,
1993. The use of prime is a naming convention which distinguishes the original
EJ-2 sequence from the EJ-2 prime sequence. Changes to the EJ-2 sequence only
eliminated events which had been previously accomplished or which had been lost
because of safing. This sequence covers spacecraft activities from July 22,
1993 to August 27, 1993.
GDS (Ground Data Systems):
1. Galileo Ground Data System (GDS) tests of MGDS V18.1 Command (CMD) were
conducted on July 19 and July 21 with DSS-42 (Canberra 34 meter antenna). The
first test failed due to a MGDS System Monitor and Control (SMC) disk
fragmentation error. The test on July 21 went well with V18.1 CMD being
exercised thoroughly. This test also validated the flow of MON 5-9 and MON
5-15 data through the MGDS. The test outcome was only partially successful due
to a LAN problem at the end of the test period. Analysis of the LAN problem is
underway and a Failure Report will be generated. All functional test
objectives were achieved and the test was conducted using the actual Galileo
operational software and hardware configuration. The next GDS test is
scheduled for Saturday, July 24 with DSS-15 (Goldstone 34 meter antenna).
TRAJECTORY
As of noon Thursday, July 22, 1993, the Galileo Spacecraft trajectory
status is as follows:
Distance from Earth 435,892,200 km (2.92 AU)
Distance from Sun 400,440,900 km (2.68 AU)
Heliocentric Speed 70,100 km per hour
Distance from Jupiter 424,397,300 km
Round Trip Light Time 48 minutes, 34 seconds
SPECIAL TOPIC
1. As of July 22, 1993, a total of 71927 real-time commands have been
transmitted to Galileo since Launch. Of these, 65546 were initiated in the
sequence design process and 6381 initiated in the real-time command process.
In the past week, 35 real time commands were transmitted; 15 were initiated in
the sequence design process and 20 initiated in the real-time command process.
Major command activities included commands to update the attitude control
subsystem flight software parameters, reset the spin rate and pointing
deadbands, switch from dual-spin to all-spin, uplink a science instrument
mini-sequence, turn the PCT No. 1 heater off and PCT No. 2 heater on, turn the
PWS calibration tone on, select the tape recorder Track 2, reconfigure from
all-spin to dual-spin and back to all-spin, uplink the EJ-2 prime sequence
memory load, and perform an SSI MRO.
GALILEO STATUS REPORT
July 19, 1993
The Galileo Spacecraft is operating normally in the all-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Over the weekend, no spacecraft activity was scheduled. Tracking was
scheduled over DSS-43 (Canberra 70 meter antenna), DSS-63 (Madrid 70 meter
antenna) and DSS-14 (Goldstone 70 meter antenna) on Saturday, and over DSS-14
on Sunday.
Today, July 19, 1993, a science reconfiguration mini-sequence is scheduled
to be uplinked. Real-time commands are scheduled to turn on the PWS (Plasma
Wave) calibration tones, and switch the tape recorder back to track 2. DAC's
(Delayed Action Commands) are also scheduled to turn on the PCT (Photometric
Calibration Target) heater #1 to off and heater #2 to on. Tracking is
scheduled over DSS-14.
Tomorrow, the science reconfiguration mini-sequence is scheduled to
execute. Tracking is scheduled over DSS-14.
GALILEO STATUS REPORT
July 20, 1993
The Galileo Spacecraft is operating in the all-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, a science reconfiguration mini-sequence was uplinked, as
planned. Real-time commands were sent to turn on the PWS (Plasma Wave)
calibration tone on, and switch the tape recorder to track 2. DAC's (Delayed
Action Commands) were sent to turn on the PCT (Photometric Calibration Target)
heater #1 off and heater #2 on. Tracking was scheduled over DSS-14 (Goldstone
70 meter antenna).
Today, July 20, 1993, the science reconfiguration mini-sequence is
scheduled to execute. Tracking is again scheduled over DSS-14.
Tomorrow, the EJ-2 (Earth-Jupiter #2) sequence memory load is scheduled to
be uplinked. Tracking is scheduled over DSS-63 (Madrid 70 meter antenna) and
DSS-14.
GALILEO STATUS REPORT
July 21, 1993
IDA -38 Days (IDA is an asteroid that Galileo will flyby and photograph
enroute to Jupiter)
The Galileo Spacecraft is operating in the all-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, the science reconfiguration mini-sequence was executed, as
planned. Tracking was scheduled over DSS-14 (Goldstone 70 meter antenna).
Today, July 21, 1993, the EJ-2 (Earth-Jupiter #2) sequence memory load is
scheduled to be uplinked. DAC's (Delayed Action Commands) are scheduled to
return to the dual-spin mode for the optical navigation #2 shuttering
activities. Real-time commands are scheduled to perform a memory readout for
the SSI (Solid State Imaging) camera. Tracking is scheduled over DSS-63
(Madrid 70 meter antenna) and DSS-14.
Tomorrow, optical navigation #2 is scheduled to be shuttered. Tracking is
scheduled over DSS-14.
GALILEO STATUS REPORT
July 22, 1993
IDA -37 Days (IDA is an asteroid that Galileo will flyby and photograph
enroute to Jupiter)
The Galileo Spacecraft is operating in the all-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, the EJ-2 (Earth-Jupiter #2) sequence memory load was uplinked,
as planned. DAC's (Delayed Action Commands) were sent to reconfigure the
spacecraft to the dual-spin mode just prior to the optical navigation #2
activities, and back to all-spin after the shutter activity completes.
Real-time commands were sent to perform a memory readout for the SSI (Solid
State Imaging) camera. Tracking was scheduled over DSS-63 (Madrid 70 meter
antenna) and DSS-14 (Goldstone 70 meter antenna).
Today, July 22, 1993, optical navigation #2 is scheduled to be shuttered,
and memory readouts of the data will begin. Tracking is scheduled over DSS-14.
Tomorrow, memory readouts of optical navigation #2 data is scheduled to
continue. Tracking is scheduled over DSS-63 and DSS-14.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_2_5_25.TXT
GALILEO STATUS REPORT 7/23/93
The Galileo Spacecraft is operating normally in the all-spin mode and is
transmitting coded telemetry at 40 bps (bits/second).
Yesterday, optical navigation #2 was shuttered and memory readouts of the
data began, as planned. Tracking was scheduled over DSS-14 (Goldstone 70 meter
antenna).
Today, July 23, 1993, memory readouts of optical navigation #2 data is
continuing. Tracking is scheduled over DSS-63 (Madrid 70 meter antenna) and
DSS-14.
Over the weekend, memory readouts of optical navigation #2 data is
scheduled to continue. Tracking is scheduled over DSS-63 and DSS-14 on
Saturday, and over DSS-14 on Sunday.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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MARS OBSERVER STATUS REPORTS 6/25-30/93
MARS OBSERVER STATUS REPORT
June 25, 1993
3:30 PM PDT
The spacecraft is stable in Array Normal Spin, with communication via the High
Gain Antenna in Mission Mode; uplink at 125 bps, downlink at the 4 kbps data
rate. One Way Light Time is 15 minutes and 49 seconds. The Payload Data
System, Gamma Ray Spectrometer, Magnetometer/Electron Reflectometer,and Mars
Observer Camera are powered on. Indications are that all spacecraft subsystems
and the instrument payload are performing well. Flight Sequence C11 is
currently active.
The C11 Sequence powered off the Mars Observer Camera Star today at 1:00 PM.
Interactive commands were used to power the MOC back on at the request of the
PI in order that MOC Imaging continues through 7/1.
The Flight Team is participating in a Mapping Operations Readiness Test, which
began Wednesday, 6/16 at 8:00 AM. The ORT, which runs through 6/30, will
exercise Team preparedness for normal Mapping activities.
The Mars Orbit Insertion strategy Final Design Review took place Tuesday, 6/22.
At that meeting, the MO Navigation Team Chief presented his view that a 4th TCM
(Trajectory Correction Maneuver) does not appear to be required at this time.
He advised that his recommendation will not be final until 7/20.
The Flight Team participated in the Radio Science Operations Readiness Test on
Thursday, 6/24. The ORT simulated signal loss and re-acquisition due to
occultation during mapping operations.
DTR (Digital Tape Recorder) repack activities took place today, 6/25.
The Verification Test Laboratory completed C12 Update testing. C12 contains
the MAG (Magnetometer) Calibration mini sequence. VTL is presently testing FSW
Build 8.1, which contains the STAREX covariance propagation "bug" fix.
MARS OBSERVER MISSION STATUS
June 29, 1993
MARS OBSERVER: Spacecraft health and performance are normal.
Mars Observer is scheduled to enter Mars orbit August 24, 1993;
it will be maneuvered into a mapping orbit by November 8 and
science operations are planned to start November 24. Mars
Observer was launched September 25, 1992.
MARS OBSERVER STATUS REPORT
June 30, 1993
4:00 PM PDT
The spacecraft is stable in Array Normal Spin, with communication via the High
Gain Antenna in Mission Mode; uplink at 125 bps, downlink at the 4 kbps data
rate. One Way Light Time is 16 minutes and 9 seconds. The Payload DataSystem,
Gamma Ray Spectrometer, Magnetometer/Electron Reflectometer,and Mars Observer
Camera are powered on. Indications are that all spacecraft subsystems and the
instrument payload are performing well. Flight Sequence C11 is currently
active.
MOC (Mars Observer Camera) Imaging, planned to continue through 7/1, has been
extended 1 day. The PI (Principal Investigator) extension request will be
accommodated using non-stored commands.
The Flight Team Mapping Operations Readiness Test, which began Wednesday, 6/16
at 8:00 AM completed today. The ORT exercised Team preparedness for normal
Mapping activities.
Payload Data System Random Access Memory was reloaded on Wednesday, 6/30. The
uplink took approximately 6 hours and was successful.
ACTIVITIES NEXT WEEK
Flight Sequence C12 uplink will take place in a window opening at 7:00 AM on
Saturday, 7/3 and closing at 8:00 AM on Sunday, 7/4. C12 activation is at 9:00
AM on Sunday, 7/4.
Magnetometer Calibrations take place beginning at 2:50 AM Tuesday 7/6 and are
scheduled to end at 2:50 AM on Thursday, 7/8. Calibrations will be
accomplished by stored sequence (C12).
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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MARS OBSERVER STATUS REPORTS 7/8-20/93
MARS OBSERVER STATUS REPORT
July 8, 1993
3:30 PM PDT
The spacecraft is stable in Array Normal Spin, with communication via the High
Gain Antenna in Mission Mode; uplink at 125 bps, downlink at the 4 kbps data
rate, alternating to 8 kbps for DTR (Digital Tape Recorder) playbacks. One Way
Light Time is 16 minutes and 41 seconds. The Payload Data System, Gamma Ray
Spectrometer, Magnetometer/Electron Reflectometer,and Mars Observer Camera are
powered on. Indications are that all spacecraft subsystems and the instrument
payload are performing well. Flight Sequence C12A is currently active.
The stored sequence completed Magnetometer Calibrations as scheduled on
Wednesday, 7/7. Calibration activities had begun at 1:02 AM on Monday. Those
activities required the Spacecraft to be commanded out of Inertial Reference
and slewed to 5 different MAG data gathering positions. Upon completion of
calibrations, the Spacecraft was returned to Earth pointing for restoration of
Inertial Reference and Array Normal Spin.
Magnetometer Data recorded on DTR 2 was replayed today beginning at 11:47 AM.
DTR2 will be replayed a second time tomorrow to insure complete data.
MARS OBSERVER STATUS REPORT
July 9, 1993
The spacecraft is stable in Array Normal Spin, with communication via the High
Gain Antenna in Mission Mode; uplink at 125 bps, downlink at the 4 kbps data
rate, alternating to 8 kbps for DTR (Digital Tape Recorder) playbacks. One Way
Light Time is 16 minutes and 45 seconds. The Payload Data System, Gamma Ray
Spectrometer, and Magnetometer/Electron Reflectometer are powered on.
Indications are that all spacecraft subsystems and the instrument payload are
performing well. Flight Sequence C12A is currently active.
The first playbacks (1A-1C) of Magnetometer Data recorded on DTR 2 will
complete tonight (Friday 7/9). The second set of playbacks (2A-2D) will occur
Sunday and Monday (7/11-12). Full playback of all MAG Cal data recorded on
onboard DTRs would exceed the length of time available in one DSN (Deep Space
Network) tracking pass, necessitating incremental playback. The second
playback is to insure that all data is received.
The Mars Observer Camera PI (Principal Investigator) updated yesterday's status
report which stated that the MOC remained powered on. The MOC was powered off
on Friday, July 2.
MARS OBSERVER STATUS REPORT
July 14, 1993
10:00 AM PDT
The spacecraft is stable in Array Normal Spin, with communication via the High
Gain Antenna in Mission Mode; uplink at 125 bps, downlink at the 4 kbps data
rate. One Way Light Time is 17 minutes and 4 seconds. The Payload Data
System, Gamma Ray Spectrometer, and Magnetometer/Electron Reflectometer are
powered on. Indications are that all spacecraft subsystems and the instrument
payload are performing well. Flight Sequence C12A is active .
Playbacks of Magnetometer Calibration data recorded on DTR 2 (Digital Tape
Recorder) were completed at 6:30 PM on Monday, 7/12.
The Flight Team is preparing for the uplink of Flight Software Version 8.1 to
occur in a window opening at 8:33 AM on Tuesday, 7/20, with task completion by
11:18 AM on Friday, 7/23. Attitude Control subsystem software tasks are being
updated to correct code which had contributed to the Spacecraft entering fault
protection Contingency Mode in January and April of this year. This will be
the last fix planned prior to commencement of Mars approach and capture
activities.
Today the Spacecraft is 8,621,667 km (5,357,255 miles) from Mars, travelling at
a speed of 2.32 kps (5192 mph) with respect to Mars.
MARS OBSERVER STATUS REPORT
July 20, 1993
MOI -35 Days (Mars Orbit Insertion)
The spacecraft is stable in Array Normal Spin, with communication via the High
Gain Antenna; uplink at 125 bps, downlink at the 2 kbps Engineering data rate.
One Way Light Time is 17 minutes and 25 seconds. The Payload Data System,
Gamma Ray Spectrometer, and Magnetometer/Electron Reflectometer are powered on.
Indications are that all spacecraft subsystems and the instrument payload are
performing well. Flight Sequence C12A is active .
Uplink of Flight Software Version 8.1 is underway. Activities began at 8:33 AM
this morning, with planned task completion by 11:18 AM on Friday, 7/23. On-
board Attitude Control Subsystem software tasks are being modified in a series
of uplinks over the next 3 days. This will be the last planned fix prior to
commencement of Mars approach and capture activities. The first of these is
Mars Observer Camera imaging of Mars starting with a photo pass beginning
Monday, July 26, at 9:18 AM and completing the following morning at 12:48 AM.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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STS-51 PRE-LAUNCH ELEMENTS (7/29/93) for 8/4/93 Launch
STS-51 elements (Aug 4 launch)
STS-51
1 00051U 93216.59635868 .00044522 00000-0 13742-3 0 30
2 00051 28.4660 341.1721 0004874 284.3542 75.6549 15.91341110 28
Satellite: STS-51
Catalog number: 00051
Epoch time: 93216.59635868 = (04 AUG 93 14:18:45.38 UTC)
Element set: 003
Inclination: 28.4660 deg
RA of node: 341.1721 deg Space Shuttle Flight STS-51
Eccentricity: .0004874 Prelaunch Element set JSC-003
Arg of perigee: 284.3542 deg Launch: 04 AUG 93 13:06 UTC
Mean anomaly: 75.6549 deg
Mean motion: 15.91341110 rev/day G. L. Carman
Decay rate: 4.4522e-04 rev/day~2 NASA Johnson Space Center
Epoch rev: 2
Checksum: 271
G.L.CARMAN
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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