home
***
CD-ROM
|
disk
|
FTP
|
other
***
search
/
Space & Astronomy
/
Space and Astronomy (October 1993).iso
/
mac
/
TEXT
/
DAILY_2
/
930627.DFC
< prev
next >
Wrap
Text File
|
1993-07-04
|
64KB
|
1,511 lines
"930627.DFC" (61728 bytes) was created on 06-27-93
27-Jun-93 Daily File Collection
These files were added or updated between 26-Jun-93 at 21:00:00 {Central}
and 27-Jun-93 at 21:00:21.
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_45_11_15.TXT
MCC Status Report #13
MISSION CONTROL CENTER
STS-57 Status Report #13
Sunday, June 27, 1993, 5 a.m. CDT
Endeavour's crew continues to work on experiments in the Spacehab module and
the shuttle's lower deck that includes studies of body posture, the spacecraft
environment, crystal growth, metal alloys, wastewater recycling and the
behaviour of fluids.
The crew was awakened at 11:37 p.m. CDT last night to begin their seventh day
aboard to the song "I Got You," performed by James Brown, a favorite tune of
Payload Commander David Low.
Included in the day's work will be a second day of test runs of the Fluid
Aquisition and Resupply Experiment by Mission Specialist Jeff Wisoff. FARE, in
the shuttle's middeck, consists of two transparent tanks linked by a series of
filters and special plumbing, studies technology for transferring fluid from
one container to another with a minimum of bubbling in weightlessness. Fluids
and gas do not naturally separate in weightlessness as they do in Earth's
gravity when fluid collecting at the bottom of a contaner and the air above.
FARE's technology may one day lead to a method for refueling spacecraft in
orbit.
Other experiments later today will include a study of an astronaut's body
posture in orbit. In weightlessness, the spine lengthens and other changes
take place which result in a unique posture. The study will photograph and
videotape crew members floating in a relaxed position, and is hoped to provide
assistance in improving the design of future spacecraft to make them as
comfortable and habitable as possible. For the same reasons, the crew will
evaluate lighting conditions and noise levels on the shuttle and in the
Spacehab today.
Endeavour remains in excellent mechanical health in an orbit of 256 by 209
nautical mile orbit circling Earth each 93 minutes.
--end--
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_45_2.TXT
STS-57 KEPLERIAN ORBITAL ELEMENTS
SPACELINK NOTE: Spacelink contains an IBM MS-DOS/Windows program (V2L9322.ZIP)
that will convert M-50 state vectors into the 2-line format preferred by many
callers. Enter IBM at the GO TO prompt and check out the section on satellite
tracking programs.
STS-57 element set GSFC-018 (orbit 85)
STS-57
1 22684U 93 37 A 93177.98146547 0.00002730 00000-0 50108-4 0 187
2 22684 28.4574 275.8454 0061185 55.8988 304.7398 15.44468792 850
Satellite: STS-57
Catalog number: 22684
Epoch time: 93177.98146547 (26 JUN 93 23:33:18.62 UTC)
Element set: GSFC-018
Inclination: 28.4574 deg
RA of node: 275.8454 deg Space Shuttle Flight STS-57
Eccentricity: 0.0061185 Keplerian Elements
Arg of perigee: 55.8988 deg
Mean anomaly: 304.7398 deg
Mean motion: 15.44468792 rev/day Semi-major Axis: 6811.0715 Km
Decay rate: 0.27E-04 rev/day*2 Apogee Alt: 474.36 Km
Epoch rev: 85 Perigee Alt: 391.01 Km
NOTE - This element set is based on NORAD element set # 018.
The spacecraft has been propagated to the next ascending
node, and the orbit number has been adjusted to bring it
into agreement with the NASA numbering convention.
R.A. Parise, Goddard Space Flight Center
G.L.CARMAN
STS-57
PREDICTED STATE VECTORS
ON ORBIT OPERATIONS
(Posted 06/27/93 by Steve Stich)
The following vector for the flight of STS-57 is provided by NASA Johnson
Space Center, Flight Design and Dynamics Division for use in ground track
plotting programs.
Lift-off Time : 1993/172/13:07:21.953
Lift-off Date : 06/21/93
ORBITER VECTOR
Vector Time (GMT) : 178/14:22:21.950
Vector Time (MET) : 006/01:15:00.000
Orbit Count : 094
Weight : 239848.0 LBS
Drag Coefficient : 2.00
Drag Area : 2750.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = -7492389.0 FT A = 3680.6820 NM
Y = 20808605.0 FT E = 0.005759
Z = -3823128.9 FT I (M50) = 28.22672 DEG
Xdot = -20422.147921 FT/S Wp (M50) = 72.37375 DEG
Ydot = -9261.695186 FT/S RAAN (M50) = 271.01631 DEG
Zdot = -11048.980119 FT/S / N (True) = 128.73575 DEG
Anomalies \ M (Mean) = 128.21962 DEG
Ha = 256.60 NM
Hp = 208.53 NM
Mean of 1950 (M50) : Inertial, right-handed Cartesian system whose
Coordinate System origin is the center of the earth. The epoch
is the beginning of the Besselian year 1950.
X axis: Mean vernal equinox of epoch
Z axis: Earth's mean rotational axis of epoch
Y axis: Completes right-hand system
A: Semi-major axis
E: Eccentricity N: True anomaly
I: Inclination M: Mean anomaly
Wp: Argument of perigee Ha: Height of apogee
RAAN: Right ascension of ascending node Hp: Height of perigee
Questions regarding these postings may be addressed to Roger Simpson,
Mail Code DM4, L. B. J. Space Center, Houston, Texas 77058,
Telephone (713) 483-1928.
Dear Customer, We are in the process of reviewing the contents of
this product and are interested in determining if it fits your needs.
If you use these state vectors, please drop us a postcard and
let us know what we can do to improve your use of this product.
POSTED BY SSTICH AT VMSPFHOU ON VMSPFHOU.VMBOARDS:PAONEWS
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_10.TXT
NOTE: This file is too large {52447 bytes} for inclusion in this collection.
The first line of the file:
ADVANCED COMMUNICATIONS TECHNOLOGY SATELLITE ACTS EXPERIMENTS PROGRAM
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_11.TXT
NOTE: This file is too large {15095 bytes} for inclusion in this collection.
The first line of the file:
ORBITING AND RETRIEVABLE FAR AND EXTREME ULTRAVIOLET SPECTROMETER
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_12.TXT
STS-51 ORFEUS/SPAS RENDEZVOUS OPERATIONS
The ORFEUS/SPAS will be released by Mission Specialist Dan
Bursch using Discovery's mechanical arm on the second day of the
mission.
While Bursch works with the arm to release the satellite, fellow
crew member Jim Newman will oversee the mechanical operations of the
ORFEUS instrument and the SPAS. The majority of commands to ORFEUS,
however, will come from ground controllers.
Once Bursch has released the satellite, Commander Frank
Culbertson will fire Discovery's small steering jets twice to
separate from the vicinity of ORFEUS/SPAS, moving at least 13
nautical miles ahead of the satellite.
For ORFEUS/SPAS operations, science ground controllers require
at least 1 1/2 hours of communications with ORFEUS/SPAS out of every
4 1/2 hours (three orbits). For these transmissions, Discovery must
act as a relay station -- ground communications will reach
ORFEUS/SPAS via Discovery and vice versa.
ORFEUS/SPAS will fly free of Discovery for almost 6 days.
Discovery will move from being ahead of the satellite to trailing it
the day before it is recaptured. The actual maneuvers to recapture
the satellite will begin about 5 1/2 hours before ORFEUS/SPAS is
captured, with Discovery trailing 30 n.m. behind the satellite.
Discovery then will perform an engine firing to begin closing in on
to a point 8 n.m. behind the satellite at a rate of about 11 n.m. per
orbit. After two orbits and one fine-tuning burn once the
ORFEUS/SPAS is in sight of the electronic star trackers on the
Shuttle's nose, Discovery will reach the 8 n.m. point.
From 8 n.m., the final rendezvous sequence begins with the
Terminal Intercept (TI) burn. The TI burn, occurring less than 2
hours before capture, will send Discovery on a final approach to
ORFEUS/SPAS. As Discovery closes in, four mid-course correction
firings will be done, if needed, with the Shuttle's small steering
jets. The dish-shaped Ku-band antenna on the Shuttle will obtain a
radar lock on the satellite.
About 1 hour, 10 minutes before capture, when Discovery is
passing about 1 statute mile below ORFEUS/SPAS, Culbertson will take
manual control of the rendezvous. Around that time, two laser
ranging devices that measure distance and closing rate by bouncing a
laser beam off of the satellite, will be used for navigation as well.
One laser ranging unit is hand-held and will be pointed by Pilot Bill
Readdy through the Shuttle cockpit window at ORFEUS/SPAS. A second
laser ranging unit, being flown for the first time, mounted in the
cargo bay of Discovery, will be remotely operated. These two units
will supplement onboard radar information.
Culbertson will brake Discovery, flying with the control stick
on the flight deck as it moves toward ORFEUS/SPAS, finally reaching a
point a few hundred feet in front of the satellite. While Discovery
is closing in, Bursch will extend the mechanical arm. With
Culbertson moving Discovery to within 35 feet of ORFEUS/SPAS and
holding position, Bursch will grapple the satellite and reberth it in
the cargo bay for the trip back to Earth.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_13.TXT
LIMITED DURATION SPACE ENVIRONMENT CANDIDATE MATERIALS EXPOSURE (LDCE)
The primary objective of the Limited Duration Space Environment
Candidate Material Exposure (LDCE) is to introduce development
composite materials to a flux atomic oxygen atoms in low-Earth orbit.
The candidate materials-polymeric, coated polymeric, and light
metallic composites will have undergone extensive ground based
material performance testing prior to being attached to reusable test
fixtures designed for multi-mission Space Shuttle use.
The LDCE, configuration C, consists of two standard 5-cubic-foot
GAS cans with Motorized Door Assemblies (MDA's). A crewmember uses
the Autonomous Payload Control System to control the payload from the
aft flight deck. The LDCE is a simple exposure experiment that
utilizes an MDA on each can but does not contain any batteries or
fluids.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_14.TXT
CHROMOSOMES AND PLANT CELL DIVISION IN SPACE
(CHROMEX-4)
Principal investigators:
Dr. Abraham Krikorian, State University of New York at Stony Brook
Dr. Mary Musgrave, Louisiana State University
Dr. Norman Lewis, Washington State University
The upcoming flight of the CHROMEX-4 experiment is the fourth in
a series of Life Sciences middeck experiments dealing with the growth
of plants in microgravity.
The CHROMEX-4 payload consists of three scientific experiments.
They are plant reproduction studies which are a reflight of the
CHROMEX-3 experiment; plant cell developmental studies which carry
the studies of CHROMEX-1 and CHROMEX-2 to another plant species; and
cell wall formation and gene expression studies. The CHROMEX-4
payload also will provide the opportunity to evaluate a new nutrient
support system developed at Washington State University.
The anticipated science benefits may lead to new strategies to
manipulate and exploit the effect of gravity in plant growth,
development, biochemistry and biotechnology. Such understandings
will directly benefit the agriculture, horticulture and forestry
industries which depend upon plant growth for their products.
The plants being studied on CHROMEX-4 are mouse-ear cress
(Arabidopsis thaliana) and a strain of wheat (Triticum aestivum).
Arabidopsis is a small, fast-growing plant widely studied by
plant scientists. It is found in the wild and cultivated for
research. This plant will self pollinate during the 9-day mission
and begin producing seeds. Dr. Musgrave will investigate the effects
of the microgravity environment on seed production and seed forming
structures of the plants.
Triticum is a superdwarf variety of wheat and has been widely
studied among plant researchers. Root and shoot development, cell
wall formation and gene expression studies are being conducted on
these specimens by Drs. Krikorian and Lewis.
These plant specimens and their nutrient support systems are
integrated with the Plant Growth Chambers (PGC) approximately 1 day
before launch. The PCGs are loaded into the Plant Growth Unit (PGU).
The PGU replaces one standard middeck locker and requires 28 volts of
power from the orbiter. This hardware provides lighting, limited
temperature control and data acquisition for post-flight analysis.
The payload crew is required to perform nominal experiment activities
consisting of a daily status check to monitor the PGU's systems'
function.
Following the flight of these plants, the investigators will
perform complete dissections of the entire plant structure and
preserve the tissues by chemical fixation or flash freezing.
The PGU was developed by NASA. The experiment is sponsored by
NASA's Office of Life and Microgravity Sciences and Applications.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_15.TXT
STS-51 EXTRAVEHICULAR ACTIVITY
STS-51 crewmembers Carl Walz and Jim Newman will perform a 6-
hour extravehicular activity (EVA), or spacewalk, on the fifth day of
the mission as a continuation of a series of test spacewalks NASA is
conducting to increase experience with spacewalks and refine
spacewalk training methods.
Walz will be designated extravehicular crew member 1 (EV1) and
Newman will be EV2. Pilot Bill Readdy will serve as the
intravehicular (IV) crew member inside Discovery, supervising the
coordination of spacewalk activities in the Shuttle's cargo bay.
In addition to performing tasks that investigate a spacewalker's
mobility in general, Walz and Newman will evaluate several tools that
may be used during the servicing of the Hubble Space Telescope (HST)
later this year on mission STS-61, including a power socket wrench, a
torque wrench, foot restraint, safety tethers and tool holder.
Unlike Shuttle mission STS-57, the astronauts will not use the
50-foot long robot arm during the spacewalk, since it will be
important for use several days after the spacewalk to retrieve the
ORFEUS-SPAS satellite. Walz and Newman will spend part of their time
outside Discovery testing various types of rigid and semi-rigid
tethers as well as moving up and down the bay carrying each other,
evaluating how well spacewalking astronauts can maneuver in
weightlessness with a large object.
Other tests include an evaluation of how well an astronaut must
be restrained in weightlessness to apply a large amount of tightening
to a bolt using the tools provided. In addition, the spacewalkers
will use a large tool onboard Discovery for use in case of a problem
with the ACTS/TOS satellite's deployment to evaluate methods of using
bulky tools.
As is the rule with the test spacewalks, the STS-51 EVA will be
one of the lowest priorities of the flight, subject to cancellation
if needed due to a problem with one of the primary payloads. It is
planned with a minimum of extra equipment flown on Discovery, making
optimum use of materials already aboard for other purposes.
The planned spacewalk will be the third such test spacewalk this
year. Previous spacewalk tests were conducted on STS-54 in January
and STS-57 in June. NASA plans to continue adding spacewalks to
Shuttle flights when they can be performed without interference to
the primary activities onboard. The STS-51 spacewalk is the final
test EVA planned for 1993. The spacewalks planned for STS-61 in
December will be performed to service the HST and not for test
purposes.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_16.TXT
STS-51 RADIATION MONITORING EQUIPMENT-III (RME-III)
The Radiation Monitoring Equipment-III (RME-III) measures
ionizing radiation exposure to the crew within the orbiter cabin.
RME-III measures gamma ray, electron, neutron and proton radiation
and calculates in real time exposure in RADS-tissue equivalent. The
information is stored in a memory module for post-flight analysis.
The hand-held instrument is stored in a middeck locker during
flight except for when the crew activates it and replaces the memory
module every two days. RME-III will be activated by the crew as soon
as possible after they achieve orbit and it will operate throughout
the mission. A crew member will enter the correct mission elapsed
time upon activation. ME-III is sponsored by the Department of
Defense in cooperation with NASA.
AIR FORCE OPTICAL SITE (AMOS)
This geophysical environmental study will test ground based
optical sensors. The experiment will also examine
contamination/exhaust plume phenomena using the Space Shuttle as a
calibration target.
AURORA PHOTOGRAPHY EXPERIMENT-B (APE-B)
The mission objectives of the Aurora Photography Experiment-B
(APE-B) are to photograph the airglow aurora, auroral optical
effects, the Shuttle glow phenomenon and thruster emissions in the
imaging mode of photography as well as in the Fabry-Perot and
spectrometer modes of photography.
COMMERCIAL PROTEIN CRYSTAL GROWTH (CPCG)
The Commercial Protein Crystal Growth (CPCG) payload is designed
to conduct experiments which supply information on the scientific
methods and commercial potential for growing large high-quality
protein crystals in microgravity. The CPCG payload consists of
Commercial Refrigerator/Incubator Modules (CR/IM's) and their
contents.
There are two possible configurations for this experiment, Block
I and Block II. This experiment is configured in Block II
configuration for the STS-51 mission, in which the CR/IM contents
consist of four cylinder containers of the same diameter but
different volumes. The four cylinders are 500 mm, 200 mm, 100 mm and
20 mm. Depending on the specific protein being flown, the
temperature is either lowered or raised in up to a five-step process
over Flight Day 1 and 2.
One CR/IM occupies the space of one middeck stowage locker.
Orbiter 28V dc power is provided to the CPCG CR/IM via single power
cables from a standard middeck outlet. The CPCG experiment is
installed at the pad within launch minus 24 hours.
HIGH RESOLUTION SHUTTLE GLOW SPECTROSCOPY
(HRSGS-A)
The High Resolution Shuttle Glow Spectroscopy-A (HRSGS-A) is an
experimental payload designed to obtain high resolution spectra in
the visible and near visible wavelength range (4000 angstroms to 8000
angstroms) of the Shuttle surface glow as observed on the orbiter
surfaces which face the velocity vector while in low Earth-orbit.
The spectral resolution of the spectrograph is 2 angstroms and it is
hoped this will help identify the cause of the Shuttle glow. The
HRSGS-A will look at the vertical tail, Orbital Maneuvering System
Pod or a suitable alternative.
IMAX
The IMAX payload is a 70mm motion picture camera system for
filming general orbiter scenes. The system consists of a camera,
lenses, rolls of film, two magazines with film, an emergency speed
control, a Sony recorder and associated equipment, two photographic
lights, supporting hardware in the form of mounting brackets to
accommodate the mode of use, two cables and various supplemental
equipment.
The IMAX and supporting equipment are stowed in the middeck for
in-cabin use. The IMAX uses two film magazines which can be
interchanged as part of the operation. Each magazine runs for
approximately 3 minutes. When both magazines are consumed, reloading
of the magazines from the stowed supply of film is required. Lenses
are interchanged based on scene requirements. The IMAX will be
installed in the orbiter middeck approximately 7 days prior to
launch.
INVESTIGATION INTO POLYMER MEMBRANES PROCESSING (IPMP)
The research objectives of the IPMP is to flash evaporate mixed
solvent systems in the absence of convection to control the porosity
of a polymer membrane. Two experimental units will be flown. Each
unit will consist of two 304L stainless steel sample cylinders
connected to each other by a stainless steel packless valve with an
aluminum cap. Before launch, the two larger canisters are evacuated
and sealed with threaded stainless steel plugs using a Teflon( tape
threading compound.
In the smaller units, a thin film polymer membrane is swollen in
a solvent compound. The film is rolled up and inserted into the
canisters. The small canisters are sealed at ambient pressure
(approximately 14.7 psia). The valves are secured with Teflon(
tape.
The locker containing the IPMP payload will be installed in the
orbiter during the period from L-6 to L-3 days.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_17.TXT
STS-51 CREW BIOGRAPHIES
Frank L. Culbertson, Jr., 44, Capt., USN, will command STS-51.
Selected as an astronaut in 1984, Culbertson will be making his
second space flight and considers Holly Hill, S.C., his hometown.
Culbertson graduated from Holly Hill High School in 1967 and
received a bachelor of science in aerospace engineering from the
Naval Academy in 1971.
After serving aboard the USS Fox in the Vietnam War, Culbertson
was designated a Naval aviator in 1973 and, from 1974-1976, he served
as an F-4 Phantom pilot aboard the USS Midway. Subsequently, he was
assigned as an exchange pilot with the Air Force, serving as a
weapons and tactics instructor at Luke Air Force Base, Ariz., until
1978. His next assignment was as the catapult and arresting gear
officer aboard the USS John F. Kennedy. In 1982, he graduated with
distinction from the Naval Test Pilot School and, subsequently,
served as a test pilot in the Carrier Systems Branch. He was engaged
in fleet replacement training in the F-14A Tomcat in 1984 until his
selection by NASA.
Culbertson's first shuttle flight was as pilot of STS-38, a
Department of Defense-dedicated mission in November 1990. He has
logged more than 117 hours in space, more than 4,500 hours flying
time in 40 different types of aircraft and 450 carrier landings.
William F. Readdy, 41, will serve as pilot. Selected as an
astronaut in 1987, Readdy will be making his second space flight and
considers McLean, Va., his hometown.
Readdy graduated from McLean High School in 1970 and received a
bachelor of science in aeronautical engineering from the U. S. Naval
Academy in 1974.
Readdy was designated a Naval aviator in 1975. From 1976-1980,
he served as an A-6 pilot aboard the USS Forrestal. He graduated from
the Naval Test Pilot School in 1981. His Navy assignments included
the Strike Aircraft Test Directorate, instructor duty at the Naval
Test Pilot School and strike operations officer aboard the USS Coral
Sea.
In 1986, Readdy accepted a reserve commission from the Navy to
join NASA as a research pilot and aerospace engineer at JSC. Prior
to his selection as an astronaut, he served as program manager for
the Shuttle Carrier Aircraft.
Readdy's first flight was on STS-42, the first flight of the
International Microgravity Lab (IML), in January 1992. Readdy has
logged more than 193 hours in space and more than 5,500 hours flying
time in 50 types of aircraft, including more than 550 carrier
landings.
James H. Newman, 36, will be Mission Specialist 1 (MS1).
Selected as an astronaut in 1990, Newman will be making his first
space flight and considers San Diego, Calif., his hometown.
Newman graduated from La Jolla High School, San Diego, in 1974;
received a bachelor of arts in physics from Dartmouth College in
1978; and received a master's and doctorate in physics from Rice
University in 1982 and 1984, respectively.
Newman performed post-doctoral work at Rice in atomic and
molecular physics and was appointed an adjunct assistant professor in
the Department of Space Physics in 1985. He later joined NASA,
serving as a simulation supervisor for astronaut training at the time
of his selection
Daniel W. Bursch, Commander, USN, will be Mission Specialist 2
(MS2). Selected as an astronaut in January 1990, Bursch will be
making his first space flight and considers Vestal, N.Y., his
hometown.
Bursch graduated from Vestal Senior High School in 1975;
received a bachelor of science in physics from the Naval Academy in
1979; and received a master's in engineering science from the Naval
Postgraduate School in 1991.
Bursch was designated a Naval flight officer in 1979 and was
assigned to Attack Squadron 34 as a bombardier/navigator in the A-6E
Intruder. He graduated from the Naval Test Pilot School in 1984 and
later returned to the school as a flight instructor. Later, he was
assigned as strike operations officer for Commander, Cruiser
Destroyer Group One. He had just completed work at the Naval
Postgraduate School at the time of his selection by NASA.
He has logged more than 1,800 flying hours in 35 types of
aircraft.
Carl E. Walz, 37, Major, USAF, will be Mission Specialist 3
(MS3). Selected as an astronaut in January 1990, Walz will be making
his first space flight and was born in Cleveland.
Walz graduated from Charles F. Bush High School, Lyndhurst,
Ohio., in 1973; received a bachelor of science in physics from Kent
State University in 1977; and received a master's in solid state
physics from John Carroll University in 1979.
Commissioned in the Air Force, from 1979-1982, Walz was assigned
as radiochemical project officer with the 1155th Technical Operations
Squadron at McClellan Air Force Base, Calif. He graduated as a
flight test engineer from the Air Force Test Pilot School in 1983.
From 1983-1987, Walz was assigned to the F-16 Combined Test Force,
and in 1987 he was assigned as a flight test program manager at Det.
3, Air Force Flight Test Center, where he served at the time of his
selection by NASA.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_18.TXT
STS-51 MISSION MANAGEMENT
NASA HEADQUARTERS, WASHINGTON, D.C.
Office of Space Flight
Jeremiah W. Pearson III - Associate Administrator
Bryan O'Connor - Deputy Associate Administrator
Tom Utsman - Space Shuttle Program Director
Brewster Shaw - Director, Space Shuttle Operations (JSC)
Loren Shriver - Technical Assistant to the Director of Space Shuttle
Operations (KSC)
Office of Advanced Concepts and Technology
Gregory M. Reck - Acting Associate Administrator
Jack Levine - Acting Director, Flight Projects Division
Andrew B. Dougherty - Spacehab Utilization Program Manager
Richard H. Ott - ActingDirector, Space Processing Division
Ana M. Villamil - Acting Deputy Director, Space Processing Division
Dan Bland - Commercial Middeck Augmentation Module Project Manager
(JSC)
Office of Safety and Mission Assurance
Col. Frederick Gregory - Associate Administrator
Charles Mertz - Acting Deputy Associate Administrator
Richard Perry - Director, Programs Assurance
Office of Life and Microgravity Sciences and Applications
Gary Martin - SAMS Program Manager
KENNEDY SPACE CENTER, FLA.
Robert L. Crippen - Director
James A. "Gene" Thomas - Deputy Director
Jay F. Honeycutt - Director, Shuttle Management and Operations
Robert B. Sieck - Launch Director
David King - Discovery Flow Director
J. Robert Lang - Director, Vehicle Engineering
Al J. Parrish - Director of Safety, Reliability and Quality Assurance
John T. Conway - Director, Payload Management and Operations
P. Thomas Breakfield - Director, Shuttle Payload Operations
Joann H. Morgan - Director, Payload Ground Operations
Mike Kinnan - STS-51 Payload Manager
MARSHALL SPACE FLIGHT CENTER, HUNTSVILLE, ALA.
Thomas J. Lee - Director
Dr. J. Wayne Littles - Deputy Director
Alexander A. McCool - Manager, Shuttle Projects Office
Harry G. Craft, Jr. - Manager, Payload Projects Office
Sid Saucier - Manager, Space Systems Projects Office
Alvin E. Hughes - Manager, Upper Stage Projects
Dr. George McDonough - Director, Science and Engineering
James H. Ehl - Director, Safety and Mission Assurance
Otto Goetz - Manager, Space Shuttle Main Engine Project
Victor Keith Henson - Manager, Redesigned Solid Rocket Motor Project
Cary H. Rutland - Manager, Solid Rocket Booster Project
Parker Counts - Manager, External Tank Project
JOHNSON SPACE CENTER, HOUSTON
Aaron Cohen - Director
Paul J. Weitz - Deputy Director
Daniel Germany - Manager, Orbiter and GFE Projects
David Leestma - Director, Flight Crew Operations
Eugene F. Kranz - Director, Mission Operations
Henry O. Pohl - Director, Engineering
Charles S. Harlan - Director, Safety, Reliability and Quality
Assurance
STENNIS SPACE CENTER, BAY ST. LOUIS, MISS.
Roy S. Estess - Director
Gerald Smith - Deputy Director
J. Harry Guin - Director, Propulsion Test Operations
AMES-DRYDEN FLIGHT RESEARCH FACILITY, EDWARDS AFB, CALIF.
Kenneth J. Szalai - Director
Robert R. Meyers, Jr. - Assistant Director
James R. Phelps - Chief, Shuttle Support Office.
AMES RESEARCH CENTER, MOUNTAIN VIEW, CALIF.
Dr. Dale L. Compton - Director
Victor L. Peterson - Deputy Director
Dr. Joseph C. Sharp - Director, Space Research
GODDARD SPACE FLIGHT CENTER, GREENBELT, MD.
Dr. John Klineberg - Director
Thomas E. Huber - Director, Engineering Directorate
Robert Weaver - Chief, Special Payloads Division
David Shrewsberry - Associate Chief, Special Payloads Division
GERMAN SPACE AGENCY (DARA), BONN, GERMANY
Heinz Stoewer - Managing Director Space Utilization
Gernot Hartmann - Head of Space Science Division
Roland Wattenbach - ASTRO-SPAS Program/Project Manager,
Klaus Steinberg - ORFEUS-SPAS Project Manager
Rolf Densing - ASTRO-SPAS System Scientist
Wolfgang Frings - ASTRO-SPAS representative at NASA-JSC
Franz-Peter Spaunhorst - Head of Public Affairs Office
Rudolf Teuwsen - ASTRO-SPAS Public Affairs Manager
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_19.TXT
NOTE: This file is too large {122000 bytes} for inclusion in this collection.
The first line of the file:
STS-51 PRESS KIT
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_2.TXT
STS-51 General News Release
ACTS DEPLOYMENT HIGHLIGHTS STS-51 MISSION
RELEASE: 93-121
The deployment of a satellite which will serve as a testbed for
technology leading to a new generation of communication satellites
and the deployment and retrieval of a U.S./German free-flying
scientific observation satellite highlight NASA's Shuttle Mission
STS-51.
The mission, which is scheduled for mid-July, 1993, also will
see Space Shuttle Discovery and her five-person crew conduct a
variety of experiments on the effects of microgravity on various
plants and materials along with other payloads which will perform
photographic observations during the mission.
The Advanced Communications Technology Satellite (ACTS) program
provides for the development and flight test of high-risk, advanced
communications satellite technology. Using sophisticated antenna
beams and advanced on-board switching and processing systems, ACTS
will pioneer new initiatives in communications satellite technology.
The Orbiting and Retrievable Far and Extreme Ultraviolet
Spectrometer - Shuttle Pallet Satellite (ORFEUS-SPAS) mission is the
first of a series of missions using the German built ASTRO-SPAS
science satellite. ASTRO-SPAS is a spacecraft designed for launch,
deployment and retrieval by the Space Shuttle.
Once deployed from the Shuttle by its Remote Manipulation
System (RMS), ASTRO-SPAS operates quasi-autonomously for several
days in the Shuttle vicinity. After completion of the free flight
phase, the satellite is retrieved by the RMS and returned to Earth.
ORFEUS-SPAS is an astrophysics mission, designed to investigate very
hot and very cold matter in the universe.
On the fifth day of the mission, two STS-51 crew members will
perform a 6-hour extravehicular activity (EVA), or spacewalk, as
part of a continuing series of test spacewalks NASA is conducting to
increase experience with spacewalks and refine spacewalk training
methods.
In addition to performing tasks that investigate a
spacewalker's mobility in general, the astronauts will evaluate
several tools that may be used during the servicing of the Hubble
Space Telescope (HST) later this year on mission STS-61, including a
power socket wrench, a torque wrench, foot restraint, safety tethers
and tool holder.
Leading the STS-51 crew will be Mission Commander Frank
Culbertson who will be making his second space flight. The pilot
for the mission is William Readdy, making his second flight. The
three mission specialists for this flight are Daniel Bursch (MS-1),
James Newman (MS-2) and Carl Walz (MS-3), all three of whom will be
making their first flight.
The mission duration for STS-51 is planned for 9 days with a
scheduled landing at the Kennedy Space Center, Fla.
This will be the 17th flight of Space Shuttle Discovery and the
57th flight of the Space Shuttle system.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_3.TXT
STS-51 MEDIA SERVICES INFORMATION
NASA Select Television Transmission
NASA Select television is available on Satcom F-2R, Transponder
13, located at 72 degrees west longitude; frequency 3960.0 MHz,
audio 6.8 MHz.
The schedule for television transmissions from the orbiter and
for mission briefings will be available during the mission at
Kennedy Space Center, Fla.; Marshall Space Flight Center,
Huntsville, Ala.; Ames-Dryden Flight Research Facility, Edwards,
Calif.; Johnson Space Center, Houston and NASA Headquarters,
Washington, D.C. The television schedule will be updated to reflect
changes dictated by mission operations.
Television schedules also may be obtained by calling COMSTOR
713/483-5817. COMSTOR is a computer data base service requiring the
use of a telephone modem. A voice update of the television schedule
is updated daily at noon Eastern time.
Status Reports
Status reports on countdown and mission progress, on-orbit
activities and landing operations will be produced by the
appropriate NASA newscenter.
Briefings
A mission press briefing schedule will be issued prior to
launch. During the mission, status briefings by a Flight Director
or Mission Operations representative and when appropriate,
representatives from the science team, will occur at least once per
day. The updated NASA Select television schedule will indicate when
mission briefings are planned.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_4.TXT
STS-51 QUICK-LOOK
Launch Date/Site: July 1993, Kennedy Space Center - Pad 39B
Launch Time: TBD
Orbiter: Discovery (OV-103) - 17th Flight
Orbit/Inclination: 160 nautical miles/28.45 degrees
Mission Duration: 8 days, 21 hours, 59 minutes
Landing Time/Date: TBD
Primary Landing Site: Kennedy Space Center, Fla.
Abort Landing Sites: Return to Launch Site - KSC, Fla.
Transatlantic Abort landing: Banjul, The Gambia;
Ben Guerir, Morocco; Moron, Spain
Abort Once Around: Edwards AFB, Calif.
Crew: Frank Culbertson, Commander (CDR)
William Readdy, Pilot (PLT)
Jim Newman, Mission Specialist 1 (MS1)
Dan Bursch, Mission Specialist 2 (MS2)
Carl Walz, Mission Specialist 3 (MS3)
Cargo Bay Payloads & Activities
Advanced Communication Technology Satellite/Transfer Orbit
Stage (ACTS/TOS)
Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer-
Shuttle
Pallet Satellite (ORFEUS-SPAS)
Limited Duration Space Environment Candidate Materials
Exposure (LDCE)
In-Cabin Payloads
Air Force Maui Optical Site (AMOS)
Auroral Photography Experiment-B (APE-B)
Commercial Protein Crystal Growth (CPCG)
Chromosome and Plant Cell Division in Space (CHROMEX)
High Resolution Shuttle Glow Spectroscopy-A (HRSGS-A)
IMAX
Investigations into Polymer Membrane Processing (IPMP)
Radiation Monitoring Equipment-III (RME-III)
STS- 51 PAYLOAD AND VEHICLE WEIGHTS
Vehicle/Payload Pounds
Orbiter (Discovery) empty and 3 SSMEs 173,117
Advanced Communications Satellite/Transfer Orbit Stage 26,756
ACTS Support Equipment 6,394
ORFEUS/SPAS 7,070
LDCE/GAS can 770
APE 41
CHROMEX 69
CPCG 70
HRSGS 91
IMAX Camera System 320
IPMP 20
RME 7
DSOs/DTOs 162
Total Vehicle at SRB Ignition 4,525,219
Orbiter Landing Weight 203,639
STS-51 SUMMARY TIMELINE
Flight Day One
Ascent
OMS-2 (160 n.m. x 161 n.m.)
Remote Manipulator System checkout
CHROMEX check
CPCG activation
RME activation
ACTS/TOS deploy
RCS, OMS Separation burns
(161 n.m. x 173 n.m.)
Flight Day Two
OMS, RCS burns (158 n.m. x 159 n.m.)
ORFEUS/SPAS checkout
ORFEUS/SPAS release
RCS Separation burns (158 n.m. x 159 n.m.)
CHROMEX check
Cabin depress to 10.2 psi
Flight Day Three
Stationkeeping burns (158 n.m. x 159 n.m.)
IPMP activation
CHROMEX check
Flight Day Four
EMU checkout
Stationkeeping burns (158 n.m. x 159 n.m.)
RME check
Flight Day Five
Extravehicular activity preparations
Extravehicular activity (six hours)
Stationkeeping burns (158 n.m. x 159 n.m.)
CHROMEX check
Flight Day Six
Stationkeeping burns (158 n.m. x 159 n.m.)
APE setup
HRSGS setup
CHROMEX check
LDCE operations
Flight Day Seven
Stationkeeping burns
(158 n.m. x 159 n.m.)
LDCE operations
APE operations
HRSGS operations
HRSGS stow
CHROMEX check
RME check
Flight Day Eight
ORFEUS/SPAS rendezvous
ORFEUS/SPAS berth
CHROMEX check
DTO 412: Fuel Cell shutdown
Flight Day Nine
Cabin repress to 14.7 psi
Flight Control Systems checkout
Reaction Control System hot-fire
AMOS
CHROMEX check
Cabin stow
DTO 412: Fuel Cell restart
Flight Day Ten
Deorbit preparations
Deorbit burn
Entry
Landing
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_5.TXT
SPACE SHUTTLE ABORT MODES
Space Shuttle launch abort philosophy aims toward safe and
intact recovery of the flight crew, Orbiter and its payload. Abort
modes include:
* Abort-To-Orbit (ATO) -- Partial loss of main engine thrust
late enough to permit reaching a minimal 105-nautical mile orbit
with orbital maneuvering system engines.
* Abort-Once-Around (AOA) -- Earlier main engine shutdown with
the capability to allow one orbit around before landing at Edwards
Air Force Base, Calif.
* Transatlantic Abort Landing (TAL) -- Loss of one or more main
engines midway through powered flight would force a landing at
either Banjul, The Gambia; Ben Guerir, Morocco; or Moron, Spain.
* Return-To-Launch-Site (RTLS) -- Early shutdown of one or more
engines, and without enough energy to reach Banjul, would result in
a pitch around and thrust back toward KSC until within gliding
distance of the Shuttle Landing Facility.
STS-51 contingency landing sites are the Kennedy Space Center,
Edwards Air Force Base, Banjul, Ben Guerir and Moron.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_6.TXT
STS-51 CREW RESPONSIBILITIES
TASK/PAYLOAD PRIMARY BACKUP
ACTS/TOS Walz Bursch
ORFEUS/SPAS Newman Newman
Middeck experiments:
APE Walz Newman
CHROMEX Newman Readdy
CPCG Bursch Culbertson
IMAX Readdy Walz
IPMP Newman Bursch
HRSGS Newman Walz
AMOS Readdy Bursch
RME Walz
DTO's/DSO's:
EVA Walz (EV1) Newman (EV2), Readdy (IV)
ET Photo Walz Newman
Fuel Cell Readdy Culbertson
PGSC Newman Walz
Thermal Print (TIPS) Newman Walz
ALBRT Culbertson Bursch
Laser Range (hand) Readdy Bursch
Laser Range (cargo bay) Bursch Readdy
GPS Walz Newman
PCMMU Newman Walz
VRCS Readdy Newman
Exercise Culbertson All
Entry ortho tolerance Newman Walz
Visual vestibular Newman
Posture Readdy Walz
Skeletal/muscle Readdy All
Gastro function Bursch Newman
Blood IV Readdy Bursch
ENH stand Culbertson Newman, Walz
Other Responsibilities:
Photography/TV Readdy Walz, Culbertson
Earth observations Readdy Culbertson
In-flight Maintenance Walz Readdy
Medic Readdy Bursch
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_7.TXT
ADVANCED COMMUNICATIONS TECHNOLOGY SATELLITE (ACTS) HARDWARE
The Advanced Communications Technology Satellite (ACTS) provides
for the development and flight test of high-risk, advanced
communications satellite technology. Using advanced antenna beams
and advanced on-board switching and processing systems, ACTS will
pioneer new initiatives in communications satellite technology.
ACTS provides new communications satellite technology for:
* Operating in the Ka-band (30/20 GHz) where there is 2.5 GHz of
spectrum available (five times that available at lower frequency
bands)
* Very high-gain, multiple hopping beam antenna systems which
permit smaller aperture Earth stations
* On-board baseband switching which permits interconnectivity
between users at an individual circuit level
* A microwave switch matrix which enables gigabit per second
communication between users.
These technologies provide for up to three times the
communications capacity for the same weight as today's satellites
(more cost effective), much higher rate communications between users
(20 times that offered by conventional satellites), greater
networking flexibility and on-demand digital services not currently
available from communications systems today. The development and
flight validation of this advanced space communications technology by
NASA's ACTS will allow industry to adapt this technology to their
individual commercial requirements at minimal risk. It also will aid
the U.S. industry in competing with European and Asian companies
which have, in the last decade, developed significant capabilities
for producing communications satellites and associated ground
equipment.
ACTS technologies, which are applicable for a variety of frequency
bands, will potentially lower the cost or technical threshold so that
such new services as remote medical image diagnostics, global
personal communications, real-time TV transmissions to airliners,
direct transmission of reconnaissance image data to battlefield
commanders and interconnection of supercomputers will be feasible.
Technology spin-off is already occurring.
Motorola currently is adapting the ACTS Ka-band and on-board
switching technologies for their $3 billion Iridium satellite system,
which will provide global voice/data communications services. Norris
Communications also is proceeding with a Ka spot-beam communications
satellite.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_8.TXT
ACTS Overall Description
ACTS is comprised of a spacecraft bus with basic housekeeping
functions and a payload, known as the multibeam communications
package (MCP).
At launch, ACTS weighs 6,108 pounds including the propellants
and the spacecraft adapter and clamp band which remain with the
Transfer Orbit Stage (TOS) upon separation. When in the stowed
configuration in the Shuttle payload bay, ACTS' overall height is
15.9 feet (5 m) from the spacecraft separation plane to the tip of
the highest antenna.
During the transfer orbit phase, the spacecraft is spin
stabilized, and the antenna reflectors and solar array panels are
retracted and stowed to provide better load support for these
appendages. During the on-orbit mission phase, the spacecraft is
three-axis stabilized with the large antenna reflectors facing the
Earth and the solar array panels rotating once per day to track the
Sun. On-orbit, ACTS measures 47.1 feet (14 m) from tip to tip of the
solar arrays and 29.9 feet (9 m) across the main receiving and
transmitting antenna reflectors.
Spacecraft Bus
The spacecraft bus structure is a rectangular box with a
cylindrical center structure that houses the apogee kick motor (AKM).
The multibeam antenna subsystem is mounted to the Earth facing panel
of the spacecraft bus. The North and South sides are each divided
into three panels. These panels are used to mount most of the
spacecraft bus and MCP electronics equipment. The spacecraft bus
provides support functions for the MCP such as electrical and
mechanical mounting surfaces, attitude control, electrical power,
thermal control, command reception, telemetry transmission and
ranging and propulsion for station keeping maneuvers.
Multibeam Communications Package
The multibeam communications package performs receiving,
switching, momentary storage, selectable coding and decoding,
amplifying and transmitting functions for Ka-band time division
multiple access (TDMA) communications signals. The multibeam antenna
(MBA) has fixed beams and hopping spot beams that can be used to
service traffic needs on a dynamic basis. (A hopping spot beam is an
antenna beam on the spacecraft that points at one location on the
ground for a fraction of a millisecond. It sends/receives voice or
data information and then the beam electronically "hops" to a second
location, then a third and so on. At the beginning of the second
millisecond the beam again points at the first location.)
In addition, the receiving antenna provides signals to the
autotrack receiver which generates input error signals to the
attitude control system for spacecraft pointing operations. Beam
forming networks (BFN) utilize hopping beams to provide independent
coverage of the East and West scan sectors, plus coverage for
isolated locations outside of either sector. The MBA also has three
fixed spot beams. A steerable beam antenna has been incorporated
into ACTS to provide antenna coverage of the entire disk of the Earth
as seen from l00 degrees west longitude and to any aircraft or low
Earth orbit spacecraft, including the Space Shuttle, within view of
the ACTS.
ACTS Deployment Sequence
ACTS will be deployed from Discovery's cargo bay approximately 8
hours after launch on orbit six. The TOS burn which will inject ACTS
into a geosynchronous transfer orbit. The spacecraft apogee kick
motor will inject ACTS into a drift orbit. Finally, ACTS will be
placed in a geostationary orbit at 100 degrees west longitude over
the equator, approximately in line with the center of the United
States. A geostationary orbit is one where a satellite takes 24
hours to complete one revolution, thus appearing to remain motionless
above a single place on the Earth.
About 2 hours before deployment from the orbiter, the astronauts
perform a sequence of events beginning with preliminary TOS checks,
unlatching the TOS cradle and elevating the ACTS/TOS flight element
to a 42 degree angle for deployment. The crew will fire the
"Super*Zip" separation system, and six springs on the TOS aft cradle
will push the flight element out of the cargo bay.
The TOS motor firing is controlled by an on-board timer and
occurs 45 minutes following deployment from the orbiter or about 8
hours and 45 minutes after STS-51 launch. The approximately two-
minute burn will place ACTS in a geotransfer orbit. The apogee kick
motor burn to inject ACTS into drift orbit will take place 42 1/2
hours after deployment, approximately 50 1/2 hours into the mission.
The 7-day drift will allow ACTS to move toward its final station
location of 100 degrees west longitude. Firing of the spacecraft's
thrusters will bring the perigee and apogee radii increasingly closer
to the geostationary orbit.
Upon reaching geostationary orbit, ACTS will transition from a
spinning to a three-axis stabilized spacecraft configuration and
deploy its solar arrays and antennas.
ACTS experiments will begin 12 weeks after launch following the
placement of the spacecraft on-station and spacecraft checkout. ACTS
is designed to have a minimum life of 2 years but will have enough
station keeping fuel for a 4-year-plus mission.
ACTS Ground Systems and Support
The facilities and support to be used for the ACTS mission
phases include the Guam and Carpentersville, N.J., C-band telemetry,
tracking and command stations and the ACTS ground segment.
Tracking, Telemetry and Command
The ACTS mission telemetry, tracking and command (TT&C) control
and monitor functions are distributed between two geographically
separate locations: Lewis Research Center, Cleveland and the Martin
Marietta Satellite Operations Center (SOC), East Windsor, N.J. The
SOC is used to control the ACTS housekeeping functions during both
the transfer orbit and the on-station phases.
During the transfer orbit phases, the SOC controls the ACTS through
the C-band ground stations. During the on-station phase, command
parameters generated at the SOC are routed via landlines to Lewis to
be uplinked to the ACTS via Ka-band. Status information is displayed
at the Lewis ACTS master ground station for both the transfer orbit
and on-station phases.
ACTS Ground Segment
The ACTS ground segment is comprised of the ACTS master ground
station, the satellite operations center and the experimenter
terminals.
ACTS Master Ground Station
The ACTS master ground station is located at the NASA Lewis
Research Center. It includes:
* The NASA ground station (NGS), which consists of a Ka-band
radio frequency terminal, two traffic terminals and a reference
terminal. It up-converts signals for the baseband processor
mode of perations to 30 GHz for transmission to ACTS and
amplifies and down-converts the 20 GHz baseband processor
modulated signals received from ACTS. Modulation and
demodulation of the baseband communications signals are
performed in the NASA ground station. It also transmits and
receives signals in support of the command, ranging and
telemetry functions for ACTS.
* The master control station provides network control for the
spacecraft baseband processor and backup to the satellite
operations center for configuring the multibeam communications
package. The master control station also enables experiment
execution and telemetry collection.
* The microwave switch matrix-link evaluation terminal provides
the capability for the on-orbit testing of the microwave switch
matrix and the multibeam antenna. It also will conduct
wideband communications experiments.
* The command, ranging and telemetry equipment interfaces with
theNASA ground station at intermediate frequency and exchanges
command, ranging and telemetry information to and from the
master control station, the G.E. SOC and the microwave switch
matrix-link evaluation terminal.
The SOC has primary responsibility for generating flight system
commands and for analyzing, processing and displaying flight system
telemetry data. Orbital maneuver planning and execution also are
handled by the SOC. The primary housekeeping function is performed
at the SOC which is linked via land line to the Ka-band command,
ranging and telemetry equipment at the ACTS master control station.
The Ka-band experimenter network consists of a variety of ground
stations to be operated by industry, universities and government
organizations. These ground stations have varying communication
services ranging from High Data Rate (HDR) at 1 gigabit per second,
to Very Small Aperture Terminal (VSAT) at 1.5 megabits per second,
aeronautical and ground mobile voice and data at 500 kilabits per
second and Ultra Small Aperture Terminal (USAT) data at 4800 bits per
second.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=--=START=--=--= NASA Spacelink File Name:6_2_2_46_3_9.TXT
TRANSFER ORBIT STAGE FOR THE STS-51 MISSION
The Transfer Orbit Stage (TOS) will boost NASA's Advanced
Communications Technology Satellite from low-Earth orbit into
geosynchronous transfer orbit with a maximum altitude of 21,519
nautical miles (34,624 km). This will be the second mission of the
Transfer Orbit Stage and the first time it has flown on a Space
Shuttle mission.
The Transfer Orbit Stage was first used in September 1992 as the
upper stage booster for NASA's Mars Observer mission. Following
launch on an expendable rocket, the TOS successfully propelled the
spacecraft on a trajectory from Earth orbit to the red planet.
The Space Systems Projects Office at NASA's Marshall Space
Flight Center, Huntsville, Ala., manages the TOS program for NASA.
That role involves ensuring TOS compliance with over all mission
requirements, including those for integration with the launch vehicle
and satellite and flight safety requirements.
Transfer Orbit Stage Description
The Transfer Orbit Stage, built by Martin Marietta Astronautics
Group in Denver, for Orbital Sciences Corp., Dulles, Va., is a
single-stage, solid-propellant rocket system. It is the latest
addition to NASA's upper stage fleet, which includes a range of
vehicles to boost satellites or spacecraft in the second step of
their journey to geostationary orbit or toward interplanetary
destinations.
TOS, constructed primarily of high-strength aluminum alloy,
weighs 20,780 pounds (9,426 kg) including solid propellant fuel. It
is almost 11 feet (3.3 m) long and about 7.5 feet (2.3 m) in
diameter. The satellite, weighing 6,108 pounds (2,771 kg), is
mounted on top of the Transfer Orbit Stage. Portions of both the
satellite and TOS are covered with gold foil multi-layered insulation
for thermal protection from the Sun.
Major elements of the TOS system are a solid rocket main
propulsion system, a navigation and guidance system, a reaction
control system which is used to adjust TOS attitude or local pointing
and an airborne support equipment cradle that holds the satellite and
upper stage in the Shuttle cargo bay and facilitates deployment from
the orbiter.
The ORBUS-21 solid rocket motor main propulsion system,
manufactured by United Technologies Chemical Systems Division, San
Jose, Calif., will give the primary thrust for the 110 seconds of
powered flight. To provide the 59,000 pounds of thrust (262,445
newtons) to inject the satellite into its transfer orbit, the motor
will use 18,013 pounds (8,171 kg) of the solid rocket propellant
HTPB (hydroxyl terminated polybutadiene).
Pitch (maneuvering upward or downward) and yaw (turning to the
left or right) will be controlled during the burn by gimballing the
nozzle of the solid rocket motor with two thrust vector control
actuators. Roll control is provided by the reaction control system
during motor burn.
TOS guidance and control avionics are based on a laser inertial
navigation system manufactured by Honeywell, Inc., Clearwater, Fla.
It acts as the brains of the vehicle, computing location and
providing signals to the propulsion system to maintain the proper
trajectory. All TOS operations are performed autonomously with no
ground commanding required. The guidance system uses laser
gyroscopes with no moving parts, thus reducing chances for
malfunctions in space. A telemetry and encoder unit records
performance data from all on-board electronics and sends it to
ground control at KSC.
The reaction control system thruster assembly, manufactured by
UTC/Hamilton Standard Division, Windsor Locks, Conn., correctly
positions the TOS and its payload, based on information from the
laser inertial navigation system. The three-axis control system
uses 12 small maneuvering rockets, which rely on decomposed
hydrazine as their propellant, to fine-tune the orientation of the
vehicle and its payload before solid rocket motor ignition.
The reaction control system also slowly turns the satellite-TOS
for thermal control to avoid overheating from the sun. The reaction
control system makes final attitude adjustments before TOS
separation from the satellite.
The equipment needed to adapt the satellite-TOS to the Space
Shuttle is called the airborne support equipment. This equipment is
manufactured by Martin Marietta. Prior to deployment, the TOS rests
in the aft cradle and is clamped firmly in the Shuttle's cargo bay
by the forward cradle.
ACTS/TOS deployment scenario
During the STS-51 mission, Discovery crew members will initiate
a predeployment checkout to ensure that all critical TOS systems are
healthy and ready to deploy. The upper forward cradle, similar to a
clamp, will then be unlatched and rotated open. The satellite-
booster will be elevated 45 degrees out of the cargo bay. If any
problems are detected in the combined payload up to this point, it
can be lowered, relatched and returned to Earth at the end of the
mission. If no anomalies are detected, a pyrotechnic system will
release the satellite-TOS and springs on the cradle will gently
nudge it out of the orbiter. The satellite-TOS will coast for 45
minutes while the Shuttle maneuvers to a safe distance, 11.7 miles
(18.8 km) away, to avoid a possible collision or damage from the TOS
solid rocket exhaust plume.
Once the Transfer Orbit Stage has positioned the satellite in
the proper attitude, the TOS solid rocket motor will fire for 110
seconds, accelerating to the 22,800-mph velocity (36,685 km/hr)
necessary to boost the satellite into its geosynchronous transfer
orbit. Then the Transfer Orbit Stage will make final attitude
adjustments as the satellite speeds toward apogee, the point
farthest from the Earth in its orbit.
Shortly after rocket burnout, the satellite will separate from
the TOS and the TOS will make a perpendicular turn to avoid being in
the satellite's path. Later, thrusters and a solid rocket motor on
the satellite itself will fire to place the satellite into its final
geosynchronous orbit. The actual timing of the satellite burn is
controlled by commands from the ground.
Extra-Vehicular Activity Tools
If a mechanical problem with the TOS airborne support equipment
were to develop prior to or after deployment of the satellite-TOS,
two astronauts can use one or more specially designed tools to
correct it. The tools were designed at Marshall Space Flight Center
and tested under simulated weightless conditions in the center's
Neutral Buoyancy Simulator water tank. The actual use of these
devices is considered unlikely since the airborne support equipment
itself is fully redundant, with all systems having built-in back-
ups.
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
=--=--=-END-=--=--=
=--=END OF COLLECTION---COLLECTED 20 FILES---COMPLETED 21:30:56=--=
