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"930311.DFC" (34872 bytes) was created on 03-11-93
11-Mar-93 Daily File Collection
These files were added or updated between 10-Mar-93 at 21:00:00 {Central}
and 11-Mar-93 at 21:01:04.
=--=--=START=--=--= NASA Spacelink File Name:930311.REL
3/11/93: NASA TETHERED PAYLOAD TO BE LAUNCHED BY AIR FORCE
Michael Braukus
Headquarters, Washington, D.C.
M
Jerry Berg
Marshall Space Flight Center, Huntsville, Ala.
LAUNCH ADVISORY
The first flight of NASA's Small Expendable-tether Deployer System (SEDS)
is scheduled to be launched aboard a U.S. Air Force Delta 2 rocket from Cape
Canaveral Air Force Station, Fla., no earlier than March 18. The SEDS tether
system will be a secondary payload on the Delta 2 launch vehicle.
The launch window opens 10:55 p.m. and extends until 11:22 p.m. EST, if
the launch occurs on March 18, according to Air Force officials. The tether
deployment process is planned to begin about 60 minutes after the Delta 2
launch and end approximately 1 hour and 40 minutes later.
SEDS is intended to demonstrate a low-cost method for using a tether to
deploy small payloads, such as satellites, to higher orbits or downward toward
Earth's atmosphere. It also is being flown to expand the limited amount of
existing data on the dynamics of tethered bodies in space.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:930311.SHU
KSC SHUTTLE STATUS REPORT 3/11/93
SPACE SHUTTLE DAILY STATUS-STS 55
Thursday, March 11, 1993
George H. Diller
Kennedy Space Center
Vehicle: OV-102/Orbiter Columbia Mission: STS-55
Current location: Pad 39-A Orbital altitude: 184 sm
Payload: Spacelab D-2 Inclination: 28.45 degrees
Launch date: TBD Landing: KSC
Mission duration: 8 days 22 hours Crew size: 7
STS-55 IN WORK:
- Flight Readiness Test (FRT) of main engines/flight controls
- orbiter aft confidence test tonight
STS-55 WORK SCHEDULED:
- begin aft compartment closeouts Friday
- begin avionics bay closeouts Friday
- external tank purges Friday
- enhanced orbiter refrigerator/freezer (EORF)
interface verification test (IVT) pending
STS-55 WORK COMPLETED:
- reinstalled hydraulic hoses
SPECIAL TOPICS: (STS-56)
Discovery's rollout from the Vehicle Assembly Building to Launch Pad 39-B
has been rescheduled for 12 Noon on Friday, March 12. This decision was made
to avoid inclement weather which is expected in central Florida on Friday night
and Saturday morning, and also because Discovery will be ready for rollout.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:930311.SKD
DAILY NEWS/TV SKED 3/11/93
Daily News
Thursday, March 11, 1993
Two Independence Square,
Washington, D.C.
Audio service: 202/358-3014
% Space Station Press Briefing;
% Galileo Mission Status;
% Work Continues on Discovery.
Today at 3:00 p.m. EST, Administrator Goldin will lead a press briefing to
discuss the details of the redesign process of the Space Station. He will be
joined by Arnold Aldrich, Associate Administrator for Space Systems
Development, and Bryan O'Connor, Deputy Associate Administrator for Space
Flight. NASA center directors will also be in attendance.
The press briefing will be carried live on NASA Select television.
* * * * * * * * * * * * * * * *
The Galileo spacecraft, traveling in its orbit at about 66,000 miles per hour,
is 51 million miles from Earth. Galileo is headed away from the Sun, traveling
towards its flyby of the asteroid Ida on August 28, 1993 and its arrival in
Jupiter's orbit on December 7, 1995.
The spacecraft is continuing to perform excellently, except that the high-gain
antenna is still only partly deployed. Galileo is transmitting telemetry at
1200 bits per second over its low-gain antenna.
* * * * * * * * * * * * * * * *
Technicians are preparing Discovery for its rollout from the VAB to the Launch
Pad. The rollout has been rescheduled for Friday. In the mean time, workers
have reinstalled the hydraulic hoses and will do the Flight Readiness Test of
the main engines and flight controls. The orbiter aft confidence test will be
conducted tonight. Closeouts of the aft compartment and the avionic bay will
begin tomorrow.
Here's the broadcast schedule for Public Affairs events on NASA Select TV. Note
that all events and times may change without notice, and that all times listed
are Eastern. Live indicates a program is transmitted live.
Thursday, March 11, 1993
12:00 pm NASA Today
12:15 pm Aeronautics & Space Report
1:00 pm NOVA: The Fastest Planes in The Sky
2:00 pm Starfinder #14
2:30 pm Images of the Universe
3:00 pm Space Station Redesign Press Briefing
Friday, March 12, 1993
12:00 pm NASA Today
12:15 pm Aeronautics & Space Report
12:30 pm Setting the Stage for the Future
1:00 pm Time of Apollo
1:30 pm Apollo Atmospherics and Entry Phase
2:00 pm Starfinder #15
2:30 pm Life on Mars
3:00 pm TQM #55
NASA Select TV is carried on GE Satcom F2R, transponder 13, C-Band, 72 degrees
West Longitude, transponder frequency is 3960 MegaHertz, audio subcarrier is
6.8 MHz, polarization is vertical.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:930311A.REL
3/11/93: ORGANIZATIONAL CHANGES TO ENHANCE PROGRAMS, RELATIONS
Jeff Carr
Headquarters, Washington, D.C. March 11, 1993
RELEASE: 93-044
A series of organizational changes to improve the focus on programs and
enhance external relationships were announced today by NASA Administrator
Daniel S. Goldin.
In a move to strengthen the top-level management of the agency, Goldin
has named John R. Dailey as Acting Deputy Administrator. Dailey has been
serving as Associate Deputy Administrator since November 1992 after retiring
from a highly distinguished 36-year career in the Marine Corps.
The Administrator also announced that Dr. Joseph Shea, recently named
as Assistant Deputy Administrator for Space Station Analysis, will have
oversight of all Space Station related development activities.
The organizational changes particularly target NASA science and
exploration programs and the agency's relations with American industry,
academia, government and non-government laboratories, and international
partners. "Science and exploration are what NASA is all about," the
Administrator said. "These changes will reestablish that focus."
New program offices for Life and Microgravity Sciences and Applications
and for Advanced Concepts and Technology have been formally established and
will report directly to the Administrator.
The official formation of the Office of Planetary Science and
Astrophysics and the Office of Mission to Planet Earth also are being
implemented effective this date. The plan to form these offices out of the
former Office of Space Science and Applications was announced in October 1992.
Named as Associate Administrator for Life and Microgravity Sciences and
Applications is Dr. Harry C. Holloway, Deputy Dean of the Uniformed Services
University of the Health Sciences, Bethesda, Md. Dr. Holloway has performed
extensive study into the impact of extreme environments on human adaptation.
He has been Chairman of the NASA Aerospace Medicine Advisory Committee since
1988 and a member of NASA's U.S./U.S.S.R. Joint Working Group on Space Biology
and Medicine.
Assisting Dr. Holloway in setting up this new organization will be Dr.
Bonnie J. Dunbar, a NASA astronaut since 1981. Dr. Dunbar is a veteran of
three space flights which logged more than 761 hours in space. Her most recent
flight was STS-50, June 25- July 9, 1992, on which she was Payload Commander of
the first U.S. Microgravity Laboratory mission. She received her doctorate in
Biomedical Engineering from the University of Houston in 1983 and a master of
science degree in Ceramic Engineering from the University of Washington in
1975.
Dr. Arnauld E. Nicogossian will become Deputy Associate Administrator
for Space Flight Activities, Life and Microgravity Sciences and Applications.
He is presently Chief Medical Officer in NASAUs Office of Space Flight and has
been with NASA since 1972.
In announcing the new organization for Life and Microgravity Sciences
and Applications, Goldin said it is critical to the President's stated
objective for a strong and productive space program, which includes development
of a space station.
Goldin said, "The President wants the current space station redesigned
as part of a program that is more efficient and effective, and capable of
producing greater returns on our investment. The redesigned space station must
provide for significant long duration space research in materials and life
sciences during this decade."
"To assure the right emphasis in the redesign effort and also within
NASA," Mr. Goldin said, "I am elevating Life and Microgravity Sciences and
Applications to report directly to the Administrator, and I am bringing all of
the elements together into a strong organization."
The decision also was recommended in a NASA study led by Roy Estess,
Director of Stennis Space Center, Miss., which reviewed the agency's life
sciences activities. "Applications is also a key element of this new
organization," the Administrator said, "because providing benefits here on
Earth must be an important consideration."
The Administrator also pointed out that, "turning back the pages of
NASA's history, the agency's greatest scientific research in life sciences was
during the Skylab program, in which there was a similar emphasis placed on the
activity in an organizational sense."
Dr. Wesley Huntress will become Associate Administrator for Planetary
Science and Astrophysics. He was named as acting in that position in October
and previously had been Director of the Solar System Exploration Division since
1990. Prior to joining NASA in 1988, he had a distinguished 20-year career at
the Jet Propulsion Laboratory, Pasadena, Calif.
The new Mission to Planet Earth (MTPE) Office will be headed by Dr.
Shelby G. Tilford, named as the Acting Associate Administrator. The MTPE office
will consist of divisions for flight systems, for operation, data and
information systems, and for science.
The Administrator also has taken measures to strengthen NASA's space
programs and the commercialization of technology.
The Office of Advanced Concepts and Technology has been formally
established with Gregory Reck as Acting Associate Administrator. Reck served as
Director of the Space Technology Program at NASA Headquarters before his
selection to this post and has over 20 years experience in technical research,
management and oversight of various technology programs.
In the Office of Aeronautics, Dr. Kristin A. Hessenius has been named
as Deputy Associate Administrator. She has been the Director of Aeronautical
Research in the Office of Aeronautics. Prior to coming to NASA Headquarters,
Dr. Hessenius was Deputy Director of Aerophysics at NASA's Ames Research
Center, Mountain View, Calif. In 1992, she was one of 10 women honored by the
National Aviation Club for outstanding contributions to the field of aviation.
Goldin has named Deidre A. Lee as Associate Administrator for
Procurement. She has been acting in that position since early January and had
been Deputy Associate Administrator of Procurement since September 1992. She
has an extensive background in a variety of military and government procurement
positions. Procurement reform is a vital element in NASA's new management
approach.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_12_7.TXT
Mir element set 928 (10-Mar-93)
Mir
1 16609U 86 17 A 93 69.44198879 .00029536 00000-0 36741-3 0 9282
2 16609 51.6220 355.2378 0002332 106.3933 253.7596 15.59699152403734
Satellite: Mir
Catalog number: 16609
Epoch time: 93069.44198879
Element set: 928
Inclination: 51.6220 deg
RA of node: 355.2378 deg Semi-major axis: 3653.6833 n.mi.
Eccentricity: 0.0002332 Apogee altitude: 210.6012 n.mi.
Arg of perigee: 106.3933 deg Perigee altitude: 208.8971 n.mi.
Mean anomaly: 253.7596 deg Altitude decay: 0.0461 n.mi./day
Mean motion: 15.59699152 rev/day Apsidal rotation: 3.7508 deg/day
Decay rate: 2.9536E-04 rev/day~2 Nodal regression: -5.0227 deg/day
Epoch rev: 40373 Nodal period: 92.2639 min
G.L.CARMAN
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_2_5_48.TXT
GALILEO MISSION STATUS REPORTS 2/24/93 thru 3/04/93
GALILEO STATUS REPORT
February 24, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting uncoded telemetry at 40 bps (bits/second).
Yesterday, no spacecraft activity was scheduled. Tracking was scheduled over
DSS-63 (Madrid 70 meter antenna) and DSS-14 (Goldstone 70 meter antenna).
Today, February 24, 1993, real-time commands are scheduled to perform a scan
actuator subassembly friction test. Tracking is scheduled over DSS-14, DSS-42
(Canberra 34 meter antenna) and DSS-63.
Tomorrow, a wobble identification is scheduled. Tracking is scheduled over
DSS-63.
GALILEO STATUS REPORT
March 1, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting coded telemetry at 1200 bps (bits/second).
Over the weekend, no spacecraft activity or tracking was scheduled.
Today, March 1, 1993, a routine RPM (Retro-Propulsion Module) 10-Newton
thruster flushing maintanence activity, SITURN, USO (Ultra Stable Oscillator)
test and cruise science memory readouts are scheduled. Additionally, the AACS
(Attitude and Articulation Control Subsystem) cone controller update
mini-sequence is scheduled to be uplinked. Tracking is scheduled over DSS-63
(Madrid 70 meter antenna) and DSS-14 (Goldstone 70 meter antenna).
Tomorrow, the downlink telemetry rate is scheduled to change to 40 bps
uncoded. Tracking is scheduled over DSS-14.
GALILEO STATUS REPORT
March 2, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting uncoded telemetry at 40 bps (bits/second).
Yesterday, a routine RPM (Retro-Propulsion Module) 10-Newton thruster
flushing maintanence activity, SITURN, USO (Ultra Stable Oscillator) test and
cruise science memory readouts were performed, as scheduled. Additionally, the
AACS (Attitude and Articulation Control Subsystem) cone controller update
mini-sequence was uplinked. Tracking was scheduled over DSS-63 (Madrid 70
meter antenna) and DSS-14 (Goldstone 70 meter antenna).
Today, March 2, 1993, the downlink telemetry rate was changed to 40 bps
uncoded. Tracking was performed over DSS-14.
Tomorrow, the downlink telemetry rate is scheduled to change to 1200 bps
coded. Real-time commands are scheduled to update the AACS cone controller and
spin detector parameters. Tracking is scheduled over DSS-63.
GALILEO STATUS REPORT
March 3, 1993
The Galileo Spacecraft is operating normally in the dual-spin mode and is
transmitting uncoded telemetry at 40 bps (bits/second).
Yesterday, the downlink telemetry rate was changed to 40 bps uncoded.
Tracking was performed over DSS-14 (Goldstone 70 meter antenna).
Today, March 3, 1993, the downlink telemetry rate is scheduled to be
changed to 1200 bps coded. Real-time commands are scheduled to update the AACS
(Attitude and Articulation Control Subsystem) cone controller and spin detector
parameters. Tracking is scheduled over DSS-63 (Madrid 70 meter antenna).
Tomorrow, real-time commands are scheduled to turn on the RTG boom heaters
and to enable their temperature control monitors. The EPD (Energetic Particle
Detector) shade retraction and motor maintanence exercise, telecommunications
test, and cruise science memory readouts are also scheduled. Tracking is
scheduled over DSS-63.
GALILEO
MISSION DIRECTOR STATUS REPORT
POST-LAUNCH
February 25 - March 4, 1993
SPACECRAFT
1. On March 1, a periodic RPM (Retro-Propulsion Module) 10-Newton thruster
maintenance activity was performed; all 12 thrusters were flushed during the
activity. There was a small change in velocity caused by imbalances in the
firings of the S-thrusters. This effect was first noticed during the RPM
thruster flushing activity on February 8, 1993.
2. On March 1, a SITURN was scheduled in the EE-12B (Earth-Earth #12B) prime
sequence. The purpose of the SITURN was to ensure the spacecraft was at the
EE-12B prime attitude after the close of the spacecraft contingency window.
3. On March 1, the Attitude and Articulation Control Subsystem (AACS) cone
controller parameter update mini-sequence was uplinked to the spacecraft
without incident. This sequence which executed on March 3 verified the cone
controller performance with the current gains, updated the cone controller
gains, verified the cone controller performance with the updated gains, and
updated spin detector parameters.
4. On March 2, 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.
5. On March 2, cruise science Memory Readouts (MROs) were performed for the
Extreme Ultraviolet Spectrometer (EUV), Dust Detector (DDS), and Magnetometer
(MAG) instruments. Preliminary analysis indicates the data was received
properly.
6. On March 3, real-time commands were sent to update the attitude control
subsystem cone controller and spin detector parameters in support of the AACS
mini-sequence uplinked on Monday.
7. On March 4, real-time commands were sent to turn the Radioisotope
Thermoelectric Generator (RTG) boom heaters on and enable their temperature
control monitors in accordance with the Retro-Propulsion Module (RPM) pressure
profile strategy and to prepare for the 10.5 rpm spin up wobble compensation
scheduled for March 10.
8. On March 4, the Energetic Particle Detector (EPD) motor maintenance
exercise was performed which stepped the motor through its eight operating
positions and then returned to the normal position (No. 4). Later the EPD
shade was retracted nominally via the spacecraft stored sequence. Retraction
was confirmed via EPD detector temperature telemetry.
9. On March 4, a command threshold test was performed. Data analysis is in
progress at the writing of this report.
10. On March 4, cruise science Memory Readouts (MROs) were performed for the
Extreme Ultraviolet Spectrometer (EUV). Analysis indicates the data was
received properly.
11. The AC/DC bus imbalance measurements have not exhibited significant change
(greater than 25 DN) throughout this period. The AC measurement reads 19DN
(4.3 volts). The DC measurement reads 141DN (16.6 volts). These measurements
are consistent with the model developed by the AC/DC special anomaly team.
12. The Spacecraft status as of March 4, 1993, is as follows:
a) System Power Margin - 40 watts
b) Spin Configuration - All-Spin
c) Spin Rate/Sensor - 2.88 rpm/Star Scanner
d) Spacecraft Attitude is approximately 3 degrees
off-sun (leading) and 8 degrees off-earth (lagging)
e) Downlink telemetry rate/antenna- 40bps(uncoded)/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 - 240 hours
Time To Initiation - 239 hours
GDS (Ground Data Systems):
1. Galileo participated in a re-test of the DSN (Deep Space Network) Version
1.5 GCF (Ground Communications Facility) upgrade data flow test on 3 March. The
purpose of this test was to demonstrate a new Galileo data flow path through
the DSN SFOC Gateway (SG) to the Error Correction and Switching (ECS)
subsystem. The 3 March test exercised telemetry, monitor and tracking data for
Galileo only. The test failed due to blocks of data being dropped between the
SG and the ECS for 134.4 KBPS. The cause of this problem is unknown and is
under investigation. Another retest will be performed prior to March 15, 1993.
In addition, Galileo participated in a CMD data flow test on 2 March. The
purpose of this test was to verify the CMD flow through the SG and ECS
interface. This test was canceled at the beginning of the test period due to
the unavailability of the necessary communication resources. A retest of the
CMD data flow will be rescheduled prior to 15 March. The Version 1.5 GCF
upgrade is scheduled to go into operations on 15 March.
2. A MOSO System Test for GLL MGDS V18 Command was performed 2 March from
20:00 to 00:00 GMT using MGDS SIM. The purpose of this test was to exercise the
connectivity of V18 CMD with a simulated DSN station (and CPA). This test was
unsuccessful due to a configuration (setup) problem between the MGDS CMD and
the Project Database (PDB). The configuration problems were resolved on 3
March. Another MOSO System Test of V18 CMD will be performed prior to 8 March.
The System Test Review for V18 CMD is scheduled for 8 March.
TRAJECTORY
As of noon Thursday, March 4, 1993, the Galileo Spacecraft trajectory
status was as follows:
Distance from Earth 72,166,500 km (0.48 AU)
Distance from Sun 220,187,100 km (1.47 AU)
Heliocentric Speed 109,300 km per hour
Distance from Jupiter 624,151,800 km
Round Trip Light Time 8 minutes, 4 seconds
SPECIAL TOPIC
1. As of March 4, 1993, a total of 65099 real-time commands have been
transmitted to Galileo since Launch. Of these, 59993 were initiated in the
sequence design process and 5106 initiated in the real-time command process.
In the past week, 33 real time commands were transmitted: 32 were initiated in
the sequence design process and 1 initiated in the real time command process.
Major command activities included commands to uplink the AACS cone controller
parameter update mini-sequence, update the cone controller and spin detector
parameters, reactivate the HGA unlatch function, and turn the RTG boom heaters
on and enable their temperature control monitors.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_2_5_49.TXT
GALILEO STATUS 3/10/93
PUBLIC INFORMATION OFFICE
JET PROPULSION LABORATORY
CALIFORNIA INSTITUTE OF TECHNOLOGY
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
PASADENA, CALIF. 91109.
GALILEO MISSION STATUS
March 10, 1993
The Galileo spacecraft is 81 million kilometers (51 million miles) from
Earth, travelling in its orbit at 29.6 kilometers per second or about 66,000
miles per hour. It is headed out away from the Sun (at almost a million miles
per day), toward its flyby of the asteroid Ida on August 28, 1993 and its
arrival in Jupiter orbit on December 7, 1995.
The spacecraft health and performance continue to be excellent, except
that the high-gain antenna is still only partly deployed. It is transmitting
telemetry at 1200 bits per second over its low-gain antenna.
Galileo's spin rate was increased to 10.5 rpm today to demonstrate the
high spin rate required for probe release (July 1995) and subsequent activities
using the large, 400-newton rocket engine. The spin rate will be returned to
3.15 rpm on Friday.
Yesterday Galileo carried out a trajectory-correction maneuver (about 2.1
meters per second or 4.7 mph) to target it for the Ida encounter.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_4_11.TXT
MARS OBSERVER ORBITAL ELEMENTS
March 1, 1993
The following are orbital elements for the Mars Observer
spacecraft during its interplanetary cruise, during its initial
capture orbit at Mars and during its final mapping orbit at Mars.
These orbital elements are predicts generated by the Mars
Observer Navigation Team. The actual set of orbital elements
achieved by the spacecraft will deviate somewhat.
_________________________________________________________________
INTERPLANETARY CRUISE
Semi-major axis 197163351.177 km
Eccentricity 0.23885397 deg
Inclination 1.294 deg
Argument of periapsis -173.656 deg
Ascending node -177.619 deg
Mean anomaly of epoch 110.042 deg
Epoch of elements: March 18, 1993 18:53:38.38 Ephemeris Time
Coordinate system: Sun-centered, Earth Mean Orbit and Equinox
of Epoch J2000
_________________________________________________________________
CAPTURE ORBIT
Semi-major axis 42923.941 km
Eccentricity 0.907977 deg
Inclination 89.000 deg
Argument of periapsis 112.990 deg
Ascending node -106.453 deg
Mean anomaly of epoch -180.000 deg
Epoch of elements: August 26, 1993 10:10:52.78 Ephemeris Time
Coordinate system: Mars-centered, Mars Mean Equator and IAU
Vector of Epoch
_________________________________________________________________
MAPPING ORBIT
Semi-major axis 3766.159 km
Eccentricity 0.004049 deg
Inclination 92.869 deg
Argument of periapsis -90.0 deg
Ascending node 261.590 deg
Mean anomaly of epoch 0.000 deg
Epoch of elements: December 6, 1993 00:00:00.00 Ephemeris Time
Coordinate system: Mars-centered, Mars Mean Equator and IAU
Vector of Epoch
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_8_4_9_29.TXT
MARS OBSERVER STATUS REPORTS 2/18 Thru 3/01.93
MARS OBSERVER STATUS REPORT
February 18, 1993
3:30 PM PST
Flight sequence C7 B is active. The Flight Team reports that spacecraft
subsystems and the instrument payload are performing nominally. The spacecraft
is in Array Normal Spin in outer cruise configuration, with uplink and downlink
via the High Gain Antenna; uplink at 125 bps, downlink at the 4 K Science and
Engineering data rate.
The Payload Data System is active and the Gamma Ray Spectrometer is taking
calibration data.
The Flight Software Build 8.0 Final Design Review is scheduled for tomorrow
morning. The Power-In maneuver Aim Point selection meeting is also scheduled
for tomorrow.
Today the spacecraft is 38,373,013 km (23,843,885 miles) from Mars, traveling
at a velocity of 4.8237 kilometers per second (10,790 miles per hour) with
respect to Mars. One way light time is approximately 315 seconds.
MARS OBSERVER STATUS REPORT
February 19, 1993
1:30 PM PST
Flight sequence C7 B is active. The Flight Team reports that spacecraft
subsystems and the instrument payload are performing nominally. The spacecraft
is in Array Normal Spin in outer cruise configuration, with uplink and downlink
via the High Gain Antenna; uplink at 125 bps, downlink at the 4 K Science and
Engineering data rate.
The Payload Data System is active and the Gamma Ray Spectrometer is taking
calibration data.
Yesterday's status report stated that the Flight Software Build 8.0 Design
Review which took place this morning was the Final Review. In fact, today's
review was the Preliminary Design Review. Flight Software engineers presented
their rationale for changes in the Flight Software to the Mission Manager, the
Flight Engineering Office Manager and various FEO team members, and Flight
Operations Office management.
The selection of the Power-In maneuver Aim Point was made today, finalizing the
overall maneuver design process. The Power-In maneuver, so named by the burn
of bi-propellant powered thrusters required to perform it, is being undertaken
to shorten the length of time between the Mars Orbit Insertion maneuver and
achievement of the desired orbit for Mapping activities to begin. Utilization
of Power-In will allow more time for successful deployment of the spacecraft
into the mapping configuration prior to the beginning of the command moratorium
during solar conjunction. Science will be able to advance the start of the
mapping phase, allowing clear observations of the planet surface before the
beginning of the Martian dust storm season which begins just after solar
conjunction. Science data will be acquired for one complete mapping cycle
prior to solar conjunction.
MARS OBSERVER STATUS REPORT
February 24, 1993
3:30 PM PST
Flight sequence C7 B is active. The Flight Team reports that spacecraft
subsystems and the instrument payload are performing nominally. The spacecraft
is in Array Normal Spin in outer cruise configuration, with uplink and downlink
via the High Gain Antenna; uplink at 125 bps, downlink at the 4 K Science and
Engineering data rate. The Gamma Ray Spectrometer is taking calibration data.
The MOS Uplink Manager (P. Varghese) presented an overview of the
Non-Interactive Non-Stored Command process to the Project Science Group this
morning. The presentation served to clarify the process to the Science Teams,
and described the level of activity and dependencies to be expected during
non-stored instrument commanding during the Mapping phase of operations. Phil
described the activities of the Process Action Team in finding ways to refine
and improve the process.
This afternoon, the Data Quality Tiger Team formally presented its findings to
date and recommendations to NASA MO Program Management, Project Management and
Project Science, including the Mars Observer Camera Team.
Today the spacecraft is 36,203,720 km (22,495,949 miles) from Mars, traveling
at a velocity of 4.4263 kilometers per second (9,901 miles per hour) with
respect to Mars. One way light time to Earth is approximately 344 seconds.
MARS OBSERVER STATUS REPORT
March 1, 1993
11:00 AM PST
Flight sequence C7 B is active. The Flight Team reports that spacecraft
subsystems and the instrument payload are performing nominally. The spacecraft
is in Array Normal Spin in outer cruise configuration, with uplink and downlink
via the High Gain Antenna; uplink at 125 bps, downlink at the 4 K Science and
Engineering data rate. The Gamma Ray Spectrometer is taking calibration data.
The Navigation and Spacecraft teams are developing parameters to update Flight
Sequence C8 for performance of Trajectory Correction Maneuver 3, scheduled for
March 18. The Maneuver Performance Data File meeting is scheduled for 9:00 AM
Friday.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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ULYSSES MISSION OPERATIONS REPORT 2/23/93 Thru 3/01/93
PERIOD: 23rd February to 1st March 1993
1. MISSION OPERATIONS
Experiment reconfigurations have been carried out as required.
On 24th February a HED (Magnetic Field instrument) calibration was carried
out.
On 1st March a KEP (Energetic Particles instrument) in-flight calibration
was carried out.
Routine Earth pointing manoeuvres were performed on 23rd, 25th, and 27th
February and 1st March.
An average of 98.45 % data recovery was achieved during the reporting
period.
The percentage of data acquired as a function of bit rate is as follows:
1024 bps 45.13 %
512 bps 53.37 %
2. SPACECRAFT STATUS
POWER
Nominal.
Estimated S/C power consumption 256 watts.
AOCS
Nominal.
TTC
The spacecraft is currently configured with receiver 2 as the prime unit
fed via the high gain antenna and with receiver 1 as backup fed through
the low gain antenna (LGA-F). The downlink is provided through
EPC2/TWTA2.
The 34 meter ground stations are in use to support TTC operations.
Ranging from 34 meter ground stations is performed when the spacecraft is
configured for bit rates of 1024 bps or less. Ranging passes from 70
meter ground stations are also being taken periodically.
Received downlink level -137 dBm.(34 meter) X-band.
(Variations of up to 10 db. can be expected as a result of station antenna
in use, local weather conditions, and spacecraft antenna off-pointing).
Received uplink level -123 dBm.
DATA HANDLING
Nominal.
THERMAL
Nominal.
3. FLIGHT DYNAMICS
Solar Aspect The angle reduced from 4.82 on
Angle (deg.) 23rd February to 4.71 on 1st March.
Sun-Probe-Earth The angle reduced from 4.81 on
Angle (deg.) 23rd February to 4.62 on 1st March.
Spin Rate 4.979 rpm.
4. ORBITAL DATA
Data taken at 13:00 PDT on 1st March.
Distance from Earth 600,126,827 km.
Velocity relative to the Earth 108,782 km/hr.
Velocity relative to the Sun 35,509 km/hr.
Ecliptic latitude 19.1 deg/south
5. PLANNED OPERATIONS
Routine data gathering operations will continue together with experiment
reconfigurations as required.
On 2nd March a HET calibration will be carried out.
On 3rd March HET will be reset.
On 8th March a KEP in-flight calibration will be carried out.
Earth pointing manoeuvres will be carried out on 3rd, 5th, 7th and 9th
March.
Periods of 2048 bps at low antenna elevations will now be avoided only
when using DSS42, which shows poorer performance due to larger tracking
errors. Playback at low elevations will, however, continue to be avoided.
6. GROUND SEGMENT
The ground segment performed nominally during the reporting period.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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