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23-Jul-93 Daily File Collection
These files were added or updated between 22-Jul-93 at 21:00:00 {Central}
and 23-Jul-93 at 21:00:43.
=--=--=START=--=--= NASA Spacelink File Name:930723.SHU
KSC SHUTTLE STATUS REPORT 7/23/93
KENNEDY SPACE CENTER SPACE SHUTTLE STATUS REPORT
Friday, July 23, 1993
KSC Contact: Bruce Buckingham
MISSION: STS-51 ACTS-TOS/ORFEUS-SPAS
LAUNCH MINUS 1 DAY
VEHICLE: Discovery/OV-103 ORBITAL ALTITUDE: 184 miles
LOCATION: Pad 39-B INCLINATION: 28.45 degrees
LAUNCH DATE: Saturday, July 24, 1993 CREW SIZE: 5
LAUNCH WINDOW: 9:27 - 10:21 a.m. (54 minutes)
KSC LANDING DATE/TIME: August 2/3, 1993 at 7:26 a.m.
MISSION DURATION: 8 days/22 hours + 1 day (An additional day on
orbit may be granted if orbiter cryogenics and allow.)
Work toward Discovery's launch on Saturday, July 24, con- tinues without
problem today at KSC's pad 39-B. Yesterday, opera- tions to load the onboard
cryogenic tanks with liquid oxygen and liquid hydrogen were completed and the
orbiter mid-body umbilical unit was demated and retracted into the service
structure.
Today, preparations continue to retract the rotating service structure to
launch position at about 10 a.m. Also today, time critical equipment and the
last two mid-deck payloads, CHROMEX and CPCG, are being installed into the
orbiter.
The countdown clock will begin counting at T-11 hours at 7:07 p.m. today.
At about 12:30 a.m. Saturday, the external tank will be ready for fueling
with more than 500,000 gallons of liquid hydrogen and liquid oxygen.
Forecasters continue to indicate a 10 percent probability of weather
prohibiting launch with a slight chance of showers and low ceilings being the
primary concerns. The winds at the pad are expected to be from the southwest
at 6 to 8 knots; temperature 83 degrees F.; visibility 7 miles; and clouds
scattered at 2,500 and 25,000 feet. A 48-hour delay will see about the same
conditions with a forecast 20 percent chance of violation. (No 24-hour forecast
is available since the 24-hour scrub turnaround is not an option for Saturday's
attempt.)
Today five-member astronaut crew are involved with checking out their
mission plans and taking part in orbiter and payload systems briefings. They
are scheduled for some free time this af- ternoon and will be ready for sleep
at about 6:30 p.m. They will be awakened tomorrow at about 4:17 a.m.
SUMMARY OF HOLDS AND HOLD TIMES FOR STS-51
T-TIME ------- LENGTH OF HOLD ---- HOLD BEGINS ---- HOLD ENDS
T-11 hours --- 3 hrs., 40 mins. -- 3:27 pm Fri.----- 7:07 pm Fri.
T-6 hours ---- 1 hour ----------- 12:07 am Sat.----- 1:07 am Sat.
T-3 hours ---- 2 hours ----------- 4:07 am Sat.----- 6:07 am Sat.
T-20 minutes - 10 minutes -------- 8:47 am Sat.----- 8:57 am Sat.
T-9 minutes -- 10 minutes -------- 9:08 am Sat.----- 9:18 am Sat.
CREW FOR MISSION STS-51
Commander (CDR): Frank Culbertson
Pilot (PLT): Bill Readdy
Mission Specialist (MS1): Jim Newman
Mission Specialist (MS2): Dan Bursch
Mission Specialist (MS3): Carl Walz
SUMMARY OF STS-51 LAUNCH DAY CREW ACTIVITIES
Saturday, July 24, 1993
4:17 a.m. Wake up
4:47 a.m. Breakfast
5:17 a.m. Weather briefing (CDR, PLT, MS2)
5:17 a.m. Don flight equipment (MS1, MS3)
5:27 a.m. Don flight equipment (CDR, PLT, MS2)
5:57 a.m. Depart for launch pad 39-B
6:27 a.m. Arrive at white room and begin ingress
7:42 a.m. Close crew hatch
9:27 a.m. Launch
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 {52617 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_13.TXT
LIMITED DURATION SPACE ENVIRONMENT CANDIDATE MATERIALS EXPOSURE (LDCE-02)
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.
The Limited Duration Space Environment Candidate Materials Exposure (LDCE-02)
experiment on STS-51 is sponsored by the NASA Office of Advanced Concepts and
Technology. LDCE-02 is a small, Shuttle cargo bay experiment developed by the
Center on Materials for Space Structures (CMSS), a NASA Center for the
Commercial Development of Space (CCDS) based at Case Western Reserve University
(CWRU), Cleveland, Ohio. The CMSS is designed to increase the U.S. private
sector's investment and involvement in industry-driven, space-based applied
research and development.
LDCE is a series of space flight experiments to study candidate materials for
space structures by exposing such materials to representative space
environments and obtain an analytical model of the performance of these
materials in space. It is expected that the results of these activities also
will provide important new insights to materials degradation processes and
preventive measures for ground-based applications.
Two primary commercial development goals exist for the LDCE flight project.
The first and foremost is that of supplying environmentally stable structural
materials to support the continued human habitation and commercial development
of the space frontier. The second is establishing a technology base with the
ability to service the ever-growing interest in space materials. The data base
would include environmental stability processing, preparation, space exposure
and evaluation information.
The overall objective of the LDCE project is to provide an engineering and
scientific service to those who are involved in the development of space
systems and structures. Specific objectives for LDCE-02 on the STS-51 mission
include the evaluation of candidate space structure composites materials for
degradation due to exposure to atomic oxygen flux and other environmental
aspects in Low Earth Orbit (LEO); understanding the mechanisms and processes by
which atomic oxygen erodes and oxidizes composite materials during space
flight; developing and maintaining a data base which contains the reaction
efficiency results of each of the materials flown; and effectively utilizing
the Get Away Special (GAS) canisters by populating the exposed surface and the
enclosed underside of the disk.
LDCE-02 consists of two separate payload elements. There are two payload
sample support systems involving an aluminum alloy disk about 49cm in diameter,
with a sample holder assembly about 38cm in diameter mounted on it. The disk
with the sample holder is about 3cm thick and weighs approximately 11kg. The
two payloads together host a total of 163 material specimens.
The Complex Autonomous Payload (CAP), LDCE-02 (the two disk and sample holder
assemblies) are mounted inside two GAS canisters, which are mounted on the port
side of the Orbiter's cargo bay 3 and equipped with a Motorized Door Assembly
(MDA). The MDA's will be opened only when Discovery's payload bay is pointed
toward the direction of travel in orbit -- the velocity vector -- and closed
when water dumps or other contamination from the Orbiter are expected.
One experiment element of LDCE-02 incorporates an optical baffle experiment
also attached to the bottom of the disk and contained within the GAS canister.
The objective of the optical baffle experiment element is to assess launch
survivability. Another experiment element incorporates a molecular absorber
experiment attached to the bottom of the disk and contained within the GAS
canister. The objective of the molecular absorber experiment element is to
evaluate methods of eliminating molecular contaminants from spacecraft
environment.
To expose the materials specimens to atomic oxygen at the planned 160 nautical
miles altitude, the Orbiter will orient the payload bay perpendicular to the
velocity vector and the MDA's will be opened for a total of 40 hours. Upon
completion of the exposure period, the MDA's will be closed. Crew interaction
is estimated at one hour, limited to only the opening and closing of the MDA's.
Upon Orbiter return, flight hardware will be de-integrated and returned to the
Center. The exposure effect on the materials will be assessed and compared to
pre-flight characterization. Sensitive surface analysis and electron
microscopy will be used to determine chemical and topographical changes.
The Center has partnered with eighteen industrial and academic sample sponsors
for STS-51, including: 3M, B.F. Goodrich, Chemfab, Hercules, Jaycor, NuSil
Technologies, NASA Lewis Research Center, Sandia Labs, TRW, Arlon Rogers/Ball
Aerospace, Bryte Technologies/Ball Aerospace, GE Aerospace, Hughes, Jet
Propulsion Labs, NASA Langley Research Center, Premix, Spire Corporation,
Wollam J.A. Each sponsor will perform post-flight surface analyses of its
materials' recession or growth to determine the reactions to the space
environment.
Lead investigator for LDCE and Center Director is Dr. Eric Baer. Ms. Dawn
Davis, LDCE Program Manager, is responsible for LDCE hardware development and
payload integration.
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.
The Commercial Protein Crystal Growth (CPCG) experiment on STS-51 is sponsored
by the NASA Office of Advanced Concepts and Technology. CPCG is developed and
managed by the Center for Macromolecular Crystallography (CMC) based at the
University of Alabama in Birmingham. The CMC is a NASA Center for the
Commercial Development of Space (CCDS), designed to increase the U.S. private
sector's investment and involvement in industry-driven, space-based applied
research and development.
The objective of the CPCG experiment on STS-51 is to grow larger, well-
ordered, very pure and more uniform protein crystals in batches using
temperature as a means to initiate and control crystallization. Pure, well-
ordered protein crystals of uniform size are in demand by the pharmaceutical
industry as special formulations for use in drug research and drug delivery.
The Center has partnered with numerous large U.S. pharmaceutical and
biotechnology companies to conduct space-based protein crystal growth
experiments, including: BioCryst Pharmaceuticals, Inc., Birmingham, Ala.; Eli
Lilly & Co., Indianapolis, Ind.; Schering-Plough Research, Bloomfield, N.J.;
DuPont Merck Pharmaceuticals, Wilmington, Del.; Sterling Winthrop, Inc.,
Malvern, Pa.; Eastman Kodak Co., Rochester N.Y.; The Upjohn Co., Kalamazoo,
Mich.; Smith Kline Beecham Pharmaceuticals, Philadelphia, Pa.; Vertex
Pharmaceuticals, Inc.; Cambridge, Mass.
Protein pharmaceuticals -- such as insulin, human growth hormone and tissue
plasminogen activator (a "clot buster" for heart attack victims) -- have been
used successfully for the past ten years in patient care. As a result, the
wide-ranging potential for commercial applications of protein pharmaceuticals
has driven industry's desire to conduct aggressive space- based protein crystal
growth experiments.
The equipment the Center will use on this mission to grow its protein crystals
is called the Protein Crystallization Facility (PCF). The PCF's unique
capability -- growing crystals in batches using temperature as a means to
initiate and control crystallization -- takes advantage of the lack of
convection currents in the unique environment of space. Temperature- induced
convection currents, similar to those found in boiling water on Earth,
interfere with protein crystal growth.
Through knowledge gained on previous space flights and in response to critical
industry needs, the PCF equipment has evolved from four sample cylinders with
the same diameter and varying heights, to four sample cylinders with the same
height and different diameters. The volumes of the cylinders are 500ml, 200ml,
100ml, and 20ml. This configuration allows for temperature changes over a
relatively long period of time and requires less protein solution to produce
quality crystals. The PCF equipment change is industry-driven to reduce cost
and the amount of protein sample needed to grow large quantities of protein
crystals in space, while at the same time increasing the quality and quantity
of crystals.
The PCF equipment will be inside a Commercial Refrigerator/Incubator Module
(CRIM) -- a state-of-the-art commercial temperature container -- which allows
for a pre-launch programmed temperature change sequence and a feedback loop
that monitors the temperatures during the space flight. The CRIM is developed
by Space Industries, Inc., League City, Texas.
Upon return to Earth, the protein crystals will be studied by scientists of the
Center and its industry partners. The technique most widely used to determine
a protein's three-dimensional structure is X-ray crystallography, which
requires sufficiently large, precisely-ordered crystals for analysis.
Space-grown crystals have been found to be large and well-ordered to facilitate
these analyses and aid in the future development of new and more effective
pharmaceuticals.
The Center Director and Principal and Lead Investigator is Charles Bugg, PhD.
The Deputy Director is Larry DeLucas, PhD., and the Associate Director for
Commercial Development and Lead Investigator is Marianna Long, PhD. The PCG
Flight Program Manager is W. R. Adams. The Deputy PCG Flight Program Manager is
John Nordness and the Senior Research Associate is Karen Moore, PhD.
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.
The Investigations into Polymer Membrane Processing (IPMP-09) experiment on
STS-51 is sponsored by the NASA Office of Advanced Concepts and Technology
(OACT) and developed and managed by the Battelle Advanced Materials Center,
Columbus, Ohio. The Advanced Materials Center is a NASA Center for the
Commercial Development of Space (CCDS), designed to increase the U.S. private
sector's investment and involvement in industry-driven, space-based applied
research and development.
The objective of the IPMP experiment is to investigate the physical and
chemical processes that occur during the formation of polymer membranes -- or
thin plastic films -- in the microgravity environment of space. The resulting
improved technology base can then be applied to commercial membrane processing
techniques on Earth.
The Center has partnered with leaders in the U.S. chemical industry to conduct
the IPMP experiments. Amoco Chemical Co., Naperville, Ill., DuPont,
Wilmington, Del., and Bend Research, Bend, Ore., have invested significant
leverage resources -- not only cash, but also their people and facilities --
into the IPMP program during the past three years.
Polymers have been used for more than 25 years in the separations industry, and
the Center's partners are specifically interested in polymers' impact upon gas
separation technology and the global trend toward stricter environmental
regulation. The enhanced knowledge base developed through the IPMP program can
be applied to commercial membrane processing techniques on Earth, such as in
separation and filtration devices for pollution control, enriching the oxygen
content of air, and chemical and drug purification.
The STS-51 flight marks the conclusion of the IPMP flight program by the Center
and its partners. Following the STS-51 mission, the team will review the
flight results as it prepares to advance the polymer membrane program to the
next phase.
The IPMP experiment equipment for STS-51 consists of two units and their
contents -- the same configuration used on previous IPMP missions. Each
experimental unit contains a vacuum cylinder, a sample cylinder and a quench
cylinder connected to one another by a valve.
The method used for preparing polymer membranes in the IPMP flight program is a
solvent evaporation/quench process. The process begins by applying a sample
mixture of polymer and solvents to a casting surface and inserting the sample
into the sample cylinders. In orbit, a crew member activates the experiment by
turning the units' valves to an initial position, initiating an evaporation
process. After a specified period of time, the valve is turned to a second
position, initiating a slow precipitation process -- quenching the membrane
with water to set each membrane's structure. The STS-51 flight will
investigate the effects of reducing the evaporation time to zero; that is, only
the quench step will be performed.
Following the flight, the IPMP samples will be retrieved and returned to the
Center for post-flight evaluation and comparison with control samples and
samples from earlier flights. Preliminary results from previous IPMP missions
indicate that polymer membranes can be obtained through space experiments with
significantly different porous qualities compared to membranes produced in
ground-based control experiments. Successful improvements in the physical
characteristics and performance of polymer membranes could strongly and
positively impact a multi-million dollar annual business in gaseous, liquid and
particle separation.
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
SPACELINK NOTE: ACTS is scheduled for launch aboard STS-51 in July 1993. To
access information about this mission use the GOTO feature and enter STS-51 as
the keyword.
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
SPACELINK NOTE: ACTS is scheduled for launch aboard STS-51 in July 1993. To
access information about this mission use the GOTO feature and enter STS-51 as
the keyword.
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
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NOTE: This file is too large {15438 bytes} for inclusion in this collection.
The first line of the file:
LAUNCH DELAY INFORMATION / PRE-LAUNCH INFORMATION
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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MAGELLAN STATUS 7/23/93
Magellan Significant Events for Week Ending 7/23/93
1. The Magellan Transition Experiment continues to go extremely well. All
subsystems are reported to be nominal. The apoapsis has been reduced below
1800 km (from its original 8460 km).
2. The latest aerobraking plan predicts the completion of aerobraking on
August 3rd with the first of several Exit OTMs to take the spacecraft out of
the upper atmosphere. The final orbit will be 205 x 525 km (from the surface
of Venus).
Magellan Significant Events for Next Week
1. Magellan will be performing two or three "full down" COTMs, followed by a
"double up" COTM, in order to aggressively pursue the desired orbit period and
apoapsis altitude. These maneuvers will be performed at two-day intervals.
2. Following EOTMs #1 and #2 on Tuesday, August 3rd, a series of up to three
EOTMs will be performed on August 4-5 to place Magellan in its final orbit for
circular orbit gravity data acquisition.
COTM = Corridor Orbit Trim Maneuver
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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STS-51 PRE-LAUNCH ELEMENTS (7/21/93) and STATE VECTORS (7/23/93)
STS-51 prelaunch elements (July 24 launch)
STS-51
1 00051U 93205.61095896 .00044522 00000-0 13742-3 0 21
2 00051 28.4662 335.5961 0004344 291.3491 68.6685 15.91099027 26
Satellite: STS-51
Catalog number: 00051
Epoch time: 93205.61095896 = (24 JUL 93 14:39:46.85 UTC)
Element set: 002
Inclination: 28.4662 deg
RA of node: 335.5961 deg Space Shuttle Flight STS-51
Eccentricity: .0004344 Prelaunch Element set JSC-002
Arg of perigee: 291.3491 deg Launch: 24 JUL 93 13:27 UTC
Mean anomaly: 68.6685 deg
Mean motion: 15.91099027 rev/day G. L. Carman
Decay rate: 4.4522e-04 rev/day~2 NASA Johnson Space Center
Epoch rev: 2
Checksum: 290
G.L.CARMAN
STS-51
PREDICTED STATE VECTOR
ON ORBIT OPERATIONS
(Posted 07/23/93 by Roger Simpson)
The following vector for the flight of STS-51 is provided by NASA Johnson Space
Center, Flight Design and Dynamics Division for use in ground track plotting
programs. The vector represents the trajectory of Discovery during on orbit
operations, after the OMS-2 maneuver. The vector assumes an on time launch.
UPDATE SCHEDULE
If we lanuch on Saturday, this notice will be updated Saturday afternoon.
Otherwise a new predicted vector will be posted prior to the next launch
attempt.
Lift off Time : 1993/205/13:27:00.000
Lift off Date : 07/24/93
ORBITER VECTOR
Vector Time (GMT) : 205/14:10:00.000
Vector Time (MET) : 000/00:43:00.000
Orbit Count : 001
Weight : 235000.0 LBS
Drag Coefficient : 2.00
Drag Area : 1250.0 SQ FT
M50 Elements Keplerian Elements
----------------------- --------------------------
X = -16655780.5 FT A = 3606.9197 NM
Y = -10937429.3 FT E = 0.000752
Z = -9086466.9 FT I (M50) = 28.35837 DEG
Xdot = 15702.561734 FT/S Wp (M50) = 252.56096 DEG
Ydot = -19034.082545 FT/S RAAN (M50) = 335.63668 DEG
Zdot = -5862.551792 FT/S / N (True) = 348.30932 DEG
Anomalies \ M (Mean) = 348.32678 DEG
Ha = 160.614 NM
Hp = 159.846 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,
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.
***NOTE***
A special thank you is sent to those who took the time to respond to our
request. It was good talking to everyone and hearing how you use these vectors
and what we can do to improve the product. All of your coments are being
considered. If you have other coments or need more information please call me
during standard work hours. Again, Thank You. POSTED BY RSIMPSON AT VMSPFHOU
ON VMSPFHOU.VMBOARDS:PAONEWS
Source:NASA Spacelink Modem:205-895-0028 Internet:192.149.89.61
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