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20-May-93 Daily File Collection
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5/20/93:  METABOLIC SPACEWALK STUDIES SUBJECT OF AMES RESEARCH

Charles Redmond
Headquarters, Washington, D.C.
  Ma


Jane Hutchison
Ames Research Center, Mountain View, Calif.



RELEASE:  93-93

        Scientists at NASA's Ames Research Center, Mountain View, Calif., are
measuring how the human body reacts to exercise here on Earth that is similar
to astronauts working in the microgravity environment of spaceflight.

        Astronauts have used spacewalks to rescue and repair satellites and
perform other important tasks outside the Space Shuttle. Spacewalks are not now
a routine method of exploration.  But assembly, maintenance and repair of the
Space Station will require spacewalks to become an everyday part of working in
space, said Rebecca Williamson, one of the Ames co-investigators.

        "A logical step is to try to improve the productivity of the space
walking astronaut to increase the amount of labor performed per spacewalk
hour," she said.  Current technology requires the astronaut to control the
temperature of the liquid cooling garment manually.  The garment is a
tight-fitting system inside the spacesuit to remove heat generated when the
astronaut works.

        "Experience with the current extravehicular activity system shows that
heat balance inside the suit is poorly controlled," Williamson said. "Some
areas of the body are too warm, while others are uncomfortably cold."

        The Ames researchers hope an advanced heat balance control system could
determine an astronaut's metabolic rate by analyzing the air exhaled by the
astronaut.  The system then would automatically change its cooling function.
"This would lead to greater comfort for the astronaut, resulting in less
fatigue and greater productivity," she added.

        "The exercise involves using the arms rather than legs to crank a
device similar to a bicycle while lying on their back," Williamson said.  Known
as an ergometer, the device measures the amount of work done by the muscles.
The ergometer can be locked in place or allowed to "float," producing a feeling
of weightlessness.  Restraints, simulating footholds in the Space Shuttle's
payload bay, hold the volunteer's feet in place.

        The ergometer is inside a controlled atmosphere chamber.  This allows
scientists to measure changes in air temperature and humidity inside the
chamber as the volunteer exercises.  A nose clip and mouth piece permit
measurement of the amount of carbon dioxide and oxygen exhaled.  Heart rate and
skin temperature are monitored and recorded as well.

        The 10 male volunteers, ages 20 to 45, exercise according to five
different profiles.  These include low, moderate and high level, constant
workloads.

        Another exercise profile is called maximum output, in which the subject
cranks as hard as possible for 1 minute after a five-minute warm-up period.
The final profile involves exercise at workloads that change every 5 minutes.
Each volunteer will perform each profile three times over a period of several
weeks.  The length of each profile varies from about 14 minutes to 45 minutes.

        Previous research has shown that exercise on the ergometer results in
physiological and thermal responses similar to those achieved during
extravehicular activities (spacewalks) performed by astronauts in space.

        Dr.  Bruce Webbon, Chief of the ExtraVehicular Systems Branch at the
Ames Advanced Life Support Division, is thsystem.  Williamson and Peter Sharer,
both of Sterling Federal Systems Inc., are co-investigators.  The team expects
to complete the current phase of their research by September 1993.
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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KSC SHUTTLE STATUS REPORT 5/20/93


         KENNEDY SPACE CENTER SPACE SHUTTLE STATUS REPORT
                      Thursday, May 20, 1993

 KSC Contact: Bruce Buckingham
 -----------------------------------------------------------------

 Mission: STS-57/Spacehab/EURECA-Retrieval  Orbital Alt. 287 miles
 Vehicle: Endeavour/OV-105                 Inclination: 28 degrees
 Location: Pad 39-B                        Crew Size: 6
 Target Launch Date/Window: June 3, 6:17 - 7:28 p.m.
 Target KSC Landing Date/Time: June 11, 5:14 p.m.
 Expected Mission Duration: 7 days/23 hours (if cryogenics allow)

 IN WORK TODAY:
 * Continue analysis of flexible joints in main propulsion system
 * Main engine number 1 heatshield installation
 * Install and checkout extravehicular mobility units (Spacesuits)
 * Spacehab late stowage demonstration

 WORK SCHEDULED:
 *  Helium signature test
 *  Main engine number 1 flight control checks
 *  Flight Readiness Review (Friday)
 *  Begin aft compartment closeouts

 WORK COMPLETED:
 *  Main engine number 1 high pressure fuel pump leak checks
 *  Open payload bay doors
 *  Auxiliary power unit leak checks
 *  Launch Readiness Review

 -----------------------------------------------------------------
 Mission: STS-51/ACTS-TOS/ORFEUS-SPAS      Orbital Alt.: 184 miles
 Vehicle: Discovery/OV-103                 Inclination: 28 degrees
 Location: OPF bay 3                       Crew Size: 5
 Mission Duration: 9 days/22 hours  Target Launch Period: mid-July

 IN WORK TODAY:
 *  Inspections of flexible joints in main propulsion system
 *  Orbital maneuvering system (OMS) redundancy tests
 *  ACTS-TOS interface verification test
 *  Main engine installation preparations
 *  Move forward reaction control system (FRCS) to OPF

 WORK SCHEDULED:
 *  ORFEUS-SPAS end-to-end test (Friday)
 *  Flight control checkouts
 *  FRCS installation

 WORK COMPLETED:
 *  Removal of thruster from OMS
 *  Ku-band antenna checks

 -----------------------------------------------------------------

 Mission: STS-58/SLS-2              Orbital Altitude: 176 miles
 Vehicle: Columbia/OV-102           Inclination: 39 degrees
 Location: OPF bay 2                Crew Size: 7
 Mission Duration: 14 days
 Target launch period: Early September


 IN WORK TODAY:
 *  Preparations for hypergolic deservice
 *  Removal of GAS cans from payload bay
 *  Auxiliary power unit catch bottle drain
 *  Main propulsion system post flight inspections
 *  Main engine post flight inspections

 WORK SCHEDULED:
 *  SLS-2 mission sequence test (May 24-27)

 WORK COMPLETED:
 *  Removal of Spacelab D-2 and transport to Operations and Checkout Building
 *  Hydraulic power-up and reposition elevons
 *  Payload bay doors latch and functional tests
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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Daily News/TV Sked 5-20-93

Daily News
Thursday, May 20, 1993
Two Independence Square, Washington, D.C.
Audio Service: 202/358-3014


 % Preparations for upcoming STS-57 continue;
 % ULYSSES and Mars Observer Update;
 % Aerospace Industry to tests NASA computers;
 % Graduate students help to commercialize NASA inventions;
 % Magellan to perform aerobraking maneuver.

Technicians at the Kennedy Space Center plan to install a heatshield to main
engine number 1 on the Space Shuttle Endeavour and conduct flight control
checks on the engine as well.  They also plan to begin aft compartment
closeouts and conduct a Flight Readiness Review test on Friday. Workers have
completed the hypergolic fuel and oxidizer loading operations.  The STS-57
mission is still scheduled for launch on June 3, 1993.

* * * * * * * * * * * * * * * *

JPL reported last week that all spacecraft and science operations are
performing well on the ULYSSES spacecraft.  Ground-controllers are conducting
routine data-gathering activities and experiment reconfigurations as needed.

JPL also reported that the Mars Observer spacecraft has returned to normal
cruise mode.  To repair the problem that was causing the spacecraft to go into
the contingency mode, technicians made a relatively minor parameter change to
the celestial body sensing software.  The upgraded flight software should allow
the spacecraft to better identify its orientation in space.

All of the spacecraft subsystems are performing well.  The science payload will
be turned on again and two-way communication has been reestablished using the
high- gain antenna.

* * * * * * * * * * * * * * * *

NASA, along with the nation's large aerospace companies, will team up to see
how NASA computer programs can help industry design and produce aircraft more
efficiently.

Members of the Multidisciplinary Analysis and Design Industrial Consortium
(MADIC) plan to work with NASA to complete a 1-year evaluation of NASA computer
simulation programs to find out how they work on real aircraft design problems.

One project goal is to give engineers and designers the ability design aircraft
systems simultaneously.  At present, an aircraft's shape is designed first then
the plane's other systems such as propulsion, flight controls and cockpit
displays are designed later.

Researchers from NASA, Rice University, Syracuse University, Argonne National
Laboratory and the MADIC consortium are taking part in the research efforts.

* * * * * * * * * * * * * * * *

The Lewis Research Center, Case Western University and the Battelle Memorial
Institute recently announced the kick-off of a new initiative to commercialize
NASA inventions.  They plan to use top graduate students from Case Western to
develop new product ideas and strategies.  The program is known as the
Strategic Technology Evaluation Program.

Guided by an industrial advisory group, students will examine inventions from
the materials, electrical and electronic and mechanical fields.  This new
venture is a precedent-establishing program in which the top graduate students,
chosen from diverse fields, work together to develop commercialization
strategies from selected inventions developed at the Lewis Research Center over
the past several years.

* * * * * * * * * * * * * * * *

The Magellan spacecraft will enter Venus' atmosphere and perform a first-of-its
kind "aerobraking" maneuver, lowering the spacecraft's orbit to start a new
experiment beginning May 25, 1993 at 1:30 p.m.  EDT. The aerobraking technique
will use the drag created by Venus' atmosphere to slow down the spacecraft and
circularize the Magellan orbit.  At present, Magellan is circling Venus in a
highly elliptical orbit.

Using the data collected during the aerobraking experiment, scientist plan to
study Venus' atmosphere and gain the engineering experinece to enable future
mission to use aerobraking to enter planetary orbit or to change orbit without
using large thrusters.

* * * * * * * * * * * * * * * *

         Here's the broadcast schedule for Public Affairs events on NASA TV.
Note that all events and times may change without notice and that all times
listed are Eastern.


Thursday, May 20, 1993

STS-57 Validation Testing from 8:30 am to 4:00 pm

Regular programming will resume at 4:00 pm




NASA TV is carried on GE Satcom F2R, transponder 13, C-Band, 72 degrees West
Longitude, transponder frequency is 3960 MHz, audio subcarrier is 6.8 MHz,
polarization is vertical.
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:930520A.REL

5/20/93:  NASA TO FEATURE VIDEOWALL AT PARIS AIR SHOW

Debra J. Rahn
Headquarters, Washington, D.C.          May 20, 1993


RELEASE:  93-92

        A 50-monitor videowall will highlight the NASA exhibit at the 40th
Paris Air Show, Le Bourget, France, June 10-20.  The video presentation
features interviews with Carl Sagan, James Michener, Roald Sagdeev, Norman
Augustine and Kathy Sullivan, discussing space station, space technology, space
science, space exploration and aeronautics.

        This year's exhibit theme, "A New Age of Exploration-- Expanding the
Frontiers of Air and Space for the Benefit of All," incorporates a large
panoramic mural at the exhibit's entrance acknowledging the many contributions
of NASA's international partners in human and robotic spaceflight and the
importance of continued international cooperation to meet the challenges of the
1990's and beyond.

        In addition to the videowall, a new 10-foot model of a High Speed Civil
Transport aircraft, a Pratt and Whitney mixer-ejector nozzle, and a high
altitude Perseus model will be displayed.  The display also will highlight
NASA's work to develop technology for a new generation supersonic airliner
focusing on exhaust emissions, airport noise and sonic boom research.


NASA will conduct the following press briefings in the USA Pavilion at
LeBourget:

June 11   Aeronautics Overview
           Dr. Wesley Harris, Associate Administrator, Office of Aeronautics


June 14   Hubble Space Telescope Servicing Mission Overview,.
           Astronaut Pierre Thuot

June 15   High Speed Research Program Overview, Louis Williams,
           Director, High Speed Research Division

          U.S./Russian Cooperation Overview, Guy Gardner, Deputy
           Associate Administrator (Russian Programs), Office of Space Flight
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:930520B.REL

5/20/93:  HUBBLE BRIEFING:  WHAT HAPPENS WHEN GALAXIES COLLIDE?

Paula Cleggett-Haleim
Headquarters, Washington, D.C.
 May

Jim Elliott
Goddard Space Flight Center, Greenbelt, Md.


N93-27

        A new Hubble image revealing details of the heart of a head-on
collision between two galaxies will be the subject of a media briefing Tuesday,
May 25, 1993, at NASA Headquarters, 300 E. Street S.W., Washington, D.C.

        This new discovery is the best evidence to date for solving more than
half a century of theory about how elliptical galaxies may form.

        Presenting the new findings will be Dr. Brad Whitmore, astronomer,
Space Telescope Science Institute, Baltimore, Md. Commenting on the
significance of the discoveries will be Dr. Francois Schweizer, astronomer, the
Carnegie Institution of Washington, Washington, D.C.

        Host Dr. Stephen Maran, NASA's Goddard Space Flight Center, Greenbelt,
Md., will be joined by Dr. Bruce Margon, Professor of Astronomy and Chairman of
the Department of Astronomy, University of Washington, Seattle, and Dr. Daniel
Weedman, Professor of Astronomy, Pennsylvania State University, University
Park.
        This event will be carried live on NASA Select television, Satcom F-2R,
Transponder 13, located at 72 degrees West Longitude, frequency 3960.0 MHz,
audio 6.8 MHz.
     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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- Current Two-Line Element Sets #194 -

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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GET AWAY SPECIAL EXPERIMENTS

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:6_2_2_45_3_11.TXT

STS-57 EXTRAVEHICULAR ACTIVTY:
DETAILED TEST OBJECTIVE 1210

     STS-57 crew members David Low and Jeff Wisoff will perform a 4-hour
extravehicular activity (EVA) on the fifth day of the flight as a continuation
of a series of spacewalks NASA plans to conduct to prepare for the construction
of the space station.

     STS-57 will be launched as a 6-day, 22-hour, 40-minute flight.  After
launch, if calculations of the amount of fuel and energy required to retrieve
EURECA and operate Spacehab match preflight projections, the flight will be
extended by 24 hours.  The EVA is the lowest priority of any objective or
experiment on the flight, and the spacewalk will be performed only if the
flight is extended by one day to become about a 7-day, 23-hour flight.

     The space station demonstration EVAs, the first of which was performed on
STS-54 in January 1993, are designed to refine training methods for spacewalks,
expand the EVA experience levels of astronauts, flight controllers and
instructors, and aid in better understanding the differences between true
microgravity and the ground simulations used in training.

     In addition, since the Shuttle's remote manipulator system (RMS)
mechanical arm will be aboard Endeavour to retrieve EURECA, the STS-57
spacewalk will assist in refining several procedures being developed to service
the Hubble Space Telescope on mission STS-61 in December 1993.

     Low will be designated extravehicular crew member 1 (EV1) and Wisoff will
be designated extravehicular crew member 2 (EV2).  Pilot Brian Duffy will serve
as intravehicular crew member 1 (IV1), assisting the spacewalkers from inside
the crew cabin of Endeavour.

     During the spacewalk, Low and Wisoff first will take turns in a foot
restraint mounted on the end of the robot arm, holding their fellow crew member
in various ways to imitate moving a large, inanimate piece of equipment.  Next,
they will investigate different methods of managing their safety tethers while
mounted in the robot arm restraint.

     Another objective is planned to have each crew member, mounted in the
robot arm restraint, practice aligning their fellow crew member into a foot
restraint mounted on the side of the cargo bay, simulating the task of aligning
a large object into a tightly fitting restraint.  The crew members also will
practice working with various tools while in the robot arm restraint and gauge
the ability of the restraint to hold them steady as they tighten or loosen a
bolt.

     The information gathered by these tests is expected to apply to both the
HST servicing spacewalks and space station construction planning, since moving,
aligning and installing objects with large masses from the end of the robot arm
will be integral to both jobs.

     Among the items hoped to be better determined are the speed at which the
arm can be moved while an astronaut holds an object on the end, how large an
object it is feasible to handle while in the arm foot restraint, the amount of
time required for such tasks using an EVA crew member and the arm and how much
stability is supplied by the arm during hands-on work such as tightening bolts
and other attachment equipment.


     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:6_2_2_45_3_12.TXT

STS-57 MIDDECK PAYLOADS
FLUID ACQUISITION AND RESUPPLY EXPERIMENT II

Principal Investigator: Susan L. Driscoll Marshall Space Flight Center,
Huntsville, Ala.

     The Fluid Acquisition and Resupply Experiment (FARE II) will investigate
the dynamics of fluid transfer in microgravity.  The experiment previously flew
as FARE I on STS-53 in 1992 and also as the Storable Fluid Management
Demonstration (SFMD) on STS 51-C in 1985.

     In space, liquid in a container does not readily settle on the bottom or
leave a pocket of gas on top as it does on Earth. The position of liquids in
weightlessness is highly unpredictable because the liquid and gas may locate or
mix in any area within the container.  To replenish on-board fluids and prolong
the life of space vehicles such as the space station, satellites and extended
duration orbiters, methods for transferring gas-free propellants and other
liquids must be developed.

     FARE I was conducted primarily to assess the ability of a screen channel
capillary system to drain liquids while working in a microgravity environment.
Additionally, some experimentation was conducted regarding the control of
liquid motion during tank refill sequences.

     Housed in four middeck lockers of the orbiter Endeavour, FARE II is
designed to demonstrate the effectiveness of a device to alleviate the problems
associated with vapor-free liquid transfer.  The device exploits the surface
tension of the liquid to control its position within the tank.

     The basic flight hardware consists of a 12.5 inches (30.48 cm) spherical
supply tank and a 12.5 inches (30.48 cm) spherical receiver tank made of
transparent acrylic.  Additional items include liquid transfer lines, two
pressurized air bottles, a calibrated cylinder and associated valves, lines,
fittings, pressure gauges and a flowmeter display unit.

     The experiment is essentially self-contained, with the exception of a
water- fill port, air-fill port and an overboard vent connected to the orbiter
waste management system.

     Mission specialists will conduct this experiment eight times during the
flight, using a sequence of manual valve operations.  Air from the pressurized
bottles will be used to force fluid from the supply tank to the receiver tank
and back to the supply tank.  This process should take about 1 hour each time
it is performed.  An overboard vent will remove the vapor from the receiver
tank as the fluid level rises.

     The FARE II control panel, containing four pressure gauges and one
temperature control gauge, will be used by the crew to monitor and control the
experiment.  Camcorder video tapes and 35-mm photographs will be made during
the transfer process.  The crew also will have the option of using air-to-
ground communication to consult with the principal investigator, if necessary.

     The test fluid used for this experiment is water with iodine, used as a
disinfectant; blue food coloring, which will allow better visibility of the
liquid movement; a wetting solution, known as Triton X-100, to give the fluid
the consistency of a propellant; and an anti-foaming emulsion agent to prevent
bubbles from forming in the receiver tank.

     Post-mission analysis of FARE II will include evaluation of the experiment
equipment, as well as review of camcorder video tapes and 35-mm photographs.
Because there will be no real-time data downlink during this experiment,
detailed study and analysis of test data will not be conducted until after the
mission.

     Historically, problems dealing with fluid orbital transfer have been dealt
with by using bellows to move liquid without any pressurant gas or vapor
surface.  These systems are heavier, more complex, more expensive and more
prone to leakage during the transfer process than conventional methods of
liquid containment, such as the FARE II equipment.

     The mission managed by NASA's Marshall Space Flight Center, Huntsville,
Ala., will utilize equipment developed by Martin Marietta. At Marshall, Susan
L. Driscoll is the Principal Investigator for FARE II.

Air Force Maui Optical System

     The Air Force Maui Optical System (AMOS) is an electrical-optical facility
on the Hawaiian island of Maui. No hardware is required aboard Endeavour to
support the experimental observations.  The AMOS facility tracks the orbiter as
it flies over the area and records signatures from thruster firings, water
dumps or the phenomena of "Shuttle glow," a well-documented fluorescent effect
created as the Shuttle interacts with atomic oxygen in Earth orbit.  The
information obtained by AMOS is used to calibrate the infrared and optical
sensors at the facility.

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:6_2_2_45_3_13.TXT

STS-57 SPECIAL EVENTS & EDUCATIIONAL ACTIVITIES

Get-Away-Special #324 -- CAN DO

     The Charleston County School District's CAN DO experiment (GAS #324) is
designed to take 1,000 photos of the Earth allowing students to make
observations and document global change by comparing the CAN DO photos with
matched Skylab photos.  The canister also contains 350 small passive student
experiments.  CAN DO is sponsored by NASA's Langley Research Center, Hampton,
Va., and supported by the South Carolina Space Grant Consortium.

     The CAN DO payload uses GAS hardware and is housed in a 5 cubic foot
canister.  The canister is sealed with a 0.92 inch fused silica window, which
is optically flat and ground to a quarter wave tolerance, permitting
photography in visible light, infrared and ultraviolet wavelengths.

     The primary payload of CAN DO, known as GEOCAM, contains four Nikon 35-mm
cameras equipped with 250 exposure film backs.  The GEOCAM system will match
closely the larger Skylab film format in both coverage and quality allowing
direct examination and comparison of the changes that have occurred to the
planet in the last 20 years.

     One thousand photographs will be taken by the four cameras over the course
of the Shuttle mission.  Photographic targets will be chosen by teachers and
students based on weather, Sun angle, orbiter orientation and crew activities.
Targets selected will be sent to the Shuttle once a day as crew notes.


     These efforts will be managed through a student-run mission control room
at the Medical University of South Carolina. Student-teacher teams of 12 to 20
will operate four desks monitoring crew activities and mission timeline,
monitoring weather data, targeting geological or environmental interests and
communicating the target objectives with NASA's Johnson Space Center's Earth
Observations Lab and the Shuttle Small Payload Customer Support Room.

     Activities and reports from the control room will be televised to students
throughout the state by the South Carolina Educational Television Network. The
Medical University of South Carolina will provide technical assistance.

     The CAN-DO teachers have designed classroom activities for grades K- 12
using the 1,000 photos to make observations.  The photos comprise the first
educational payload to photograph the Earth from space.  Students will search
for natural and human-induced environmental changes that may have taken place
during the past 20 years.  Comparison between the photos, past and present,
enables students to discover for themselves the major effects caused by
deforestation, urbanization, river sediment loads, desertification, coastal
erosion, lake levels wetlands and pollution.

     With assistance from atmospheric scientists, the photos should provide
clues to the degradation of the air quality often mentioned by astronauts.
Faculty members of the College of Charleston will aid in the interpretation of
the results.

     The second experiment carried on CAN DO is 350 student-designed
experiments.  No other GAS payload in the history of the space program has ever
undertaken this many different experiments.  These experiments have been
submitted from more than 60 Charleston County classrooms and from invited
school districts from Maryland, Virginia, Texas, Arizona and Massachusetts.

     These experiments allow students to participate directly in research by
testing the effect of space on various materials.  Students from K-12 have
chosen materials ranging from brine shrimp eggs to bubble solution to lipstick
to cotton seeds to fly in space.  A major goal of the student experiments is to
teach the skills of proper experimental design as well as execution of valid
scientific experiments.

     Each student team has five samples of their materials in small 5 ml
cryovials: one to fly in space, one to serve as a passive control and one each
to be exposed to high doses of radiation, extreme cold and centrifuge.  The
control procedures will be carried out at the Medical University of South
Carolina as part of its Business/Education Partnership Program with the
Charleston County School District Office of Math, Sciences and Technology.

     In addition to the students' vial experiments, the WESTVACO Forestry
Division has donated Sycamore and Loblolly Pine seeds to be placed into the
canister.  Classes participating in CAN DO will receive seedlings grown from
space-exposed seeds and encouraged to raise "space trees."

     Students and teachers from the Poquoson School District in Poquoson, Va.,
are participating in the payload's student-designed experiments.  Also, a team
of Poquoson secondary students will travel to Charleston and operate the
weather desk at the student mission control.  NASA Langley atmospheric research
scientists will provide appropriate training to the Poquoson students for their
weather desk assignment.

Shuttle Amateur Radio Experiment-II

     The Shuttle Amateur Radio Experiment-II (SAREX-II) provides for public
participation in the space program, supports educational initiatives and
demonstrates the effectiveness of making contact between the Space Shuttle and
low-cost amateur "ham" radio stations on the ground.

     On STS-57, Pilot Brian Duffy, call sign N5WQW, and Janice Voss, call sign
to be determined, will operate SAREX. Duffy has operated SAREX in flight before
during Shuttle mission STS-45. Operating times for school contacts are planned
into the crew's activities.  The school contacts generate interest in science
as students talk directly with Voss or Duffy. There will be voice contacts with
the general ham operator community as time permits. and short wave listeners
(SWL's) worldwide also may listen.  When Voss or Duffy are not available,
SAREX- II will be in an automated digital response mode.

     On STS-57, SAREX-II will include VHF FM voice and VHF packet.  The primary
voice frequency that SAREX-II uses is 145.55 MHz downlink.  There are a variety
of uplink frequencies.  Contacts with Endeavour will be possible between 42
degrees north latitude to 42 degrees south latitude, covering the lower half of
the continental United States and Hawaii, all of Africa, most of South America,
Australia, the East and the Far East.

     SAREX has flown previously on STS-9, STS-51F, STS-35, STS-37, STS-45,
STS-50, STS-47, STS-55 and STS-56. SAREX is a joint effort of NASA, the
American Radio Relay League (ARRL), the Amateur Radio Satellite Corp. (AMSAT),
and the Johnson Space Center's Amateur Radio Club. Information about orbital
elements, contact times, frequencies and crew operating schedules will be made
available during the mission by these agencies and by amateur radio clubs at
some other NASA centers.

     Hams from the JSC club, W5RRR, will be operating on amateur short wave
frequencies, and the ARRL station, W1AW, will include SAREX information in its
regular voice and teletype bulletins.  The amateur radio station at the Goddard
Space Flight Center, WA3NAN, in Greenbelt, Md., will operate around-the- clock
during the mission, providing information and re-transmitting live Shuttle
air-to- ground audio.  The JSC Public Affairs Office will operate a SAREX
information desk during the mission, and mission information also will be
available on the dial-up computer bulletin board (BBS) at JSC.SAREX
Frequencies.

                Shuttle Transmitting    Shuttle Receiving
                Frequency               Frequency

U.S.            145.55 MHz              144.99 MHz
South America   145.55                  144.97
& Asia          145.55                  144.95
                145.55                  144.93
                145.55                  144.91

Europe          145.55 MHz              144.70 MHz
                145.55                  144.75
                145.55                  144.80

South Africa    145.55 MHz              144.95 MHz
Packet          145.55                  144.49

GSFC Amateur Radio Club (WA3NAN) planned HF operating frequencies

3.860 MHz               7.185 MHz
14.295 Mhz             21.395 MHz
28.395 Mhz

To connect to the JSC Compute Bulletin Board, BBS, (8 N 1 1200 baud)
dial 713/483-2500 then type 62511.

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STS-57 CREW BIOGRAPHIES

     Ronald J. Grabe, 47, Col., USAF, will be Commander (CDR) of STS-57.
Selected as an astronaut in August 1981, Grabe considers New York, N.Y., his
hometown and will be making his fourth space flight.

     Grabe graduated from Stuyvesant High School, New York, in 1962.  He
received a bachelors degree in engineering from the United States Air Force
Academy in 1966 and studied aeronautics as a Fulbright Scholar at the

Technische Hochschule, Darmstadt, West Germany in 1967.

     Grabe first flew as Pilot for Shuttle mission STS-51J in October 1985.  On
his second flight, he was Pilot for Shuttle mission STS-30 in May 1989.  On his
most recent flight he was Commander of Shuttle mission STS-42 in January 1992.
Grabe has logged more than 387 hours in space.

     Brian Duffy, 39, Col., USAF, will serve as Pilot (PLT).  Selected as an
astronaut in June 1985, Duffy was born in Boston, Mass., and will be making his
second space flight.

     Duffy graduated from Rockland High School, Rockland, Mass., in 1971.  He
received a bachelors degree in mathematics from the Air Force Academy in 1975
and a masters degree in systems management from the University of Southern
California in 1981.

     Duffy first flew as Pilot of STS-45 in March 1992 and has logged more than
214 hours in space.

     G.  David Low, 37, will serve as Payload Commander and Mission Specialist
1 (MS1).  Selected as an astronaut in May 1984, Low was born in Cleveland and
will be making his third spaceflight.

     Low graduated from Langley High School, McLean, Va., in 1974.  He received
a bachelors degree in physics-engineering from Washington and Lee University in
1978, a bachelors degree in mechanical engineering from Cornell University in
1980 and a masters degree in aeronautics and astronautics from Stanford
University in 1983.

     Low first flew as a mission specialist aboard STS-32 in January 1990.  His
next flight was as a mission specialist on STS-43 in August 1991.  He has
logged more than 474 hours in space.

     Nancy Jane Sherlock, 34, Capt., USA, will serve as Mission Specialist 2
(MS2).  Selected as an astronaut in January 1990, Sherlock considers Troy,
Ohio, her hometown and will be making her first space flight.

     Sherlock graduated from Troy High School in 1977.  She received a
bachelors degree in biological science from Ohio State University in 1980 and a
masters degree in safety engineering from the University of Southern California
in 1985.

     After serving as a Neuropathology Research Assistant for 3 years at the
Ohio State University College of Medicine, Sherlock was commissioned in the U.
S. Army in 1981.  She attended the Army Aviation School and later served as a
UH-1H instructor pilot and a standardization instructor pilot for all phases of
rotary wing flight.  She has logged more than 2,900 hours flying time in rotary
wing and fixed wing aircraft.

     Sherlock was assigned to NASA as a flight simulation engineer on the
Shuttle Training Aircraft at the Johnson Space Center in 1987, developing and
directing engineering flight tests, a position she held at the time of her
selection.

     Peter J. K. (Jeff) Wisoff, 34, will serve as Mission Specialist 3 (MS3).
Selected as an astronaut in January 1990, Wisoff was born in Norfolk, Va., and
will be making his first space flight.

     Wisoff graduated from Norfolk Academy in 1976.  He received a bachelors
degree in physics from the University of Virginia in 1980, a masters degree in
applied physics from Stanford University in 1982 and a doctorate in applied
physics from Stanford in 1986.

     After completing his doctorate, Wisoff joined the Rice University faculty
in the Electrical and Computer Engineering Department, researching the
development of new vacuum ultraviolet and high intensity laser sources and the
medical application of lasers to the reconstruction of damaged nerves.  He is
currently collaborating with researchers at Rice University on developing new
techniques for growing and evaluating semiconductor materials using lasers.

     Janice Voss, 36, will serve as Mission Specialist 4 (MS4).  Selected as an
astronaut in January 1990, Voss considers Rockford, Ill., her hometown and will
be making her first space flight.

     Voss graduated from Minnechaug Regional High School in Wilbraham, Mass.,
in 1972.  She received a bachelors degree in engineering science from Purdue
University in 1975, a masters degree in electrical engineering from the
Massachusetts Institute of Technology (MIT) in 1977 and a doctorate in
aeronautics and astronautics from MIT in 1987.

     Voss was a cooperative education employee at the Johnson Space Center from
1973 to 1975, working with computer simulations in the Engineering and
Development Directorate. In 1977, she returned to JSC to work as a crew
trainer, teaching entry guidance and navigation.  After completing her
doctorate, she joined Orbital Sciences Corp., working on mission integration
and flight operations support for the Transfer Orbit Stage, a position she held
at the time of her selection.


STS-57 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
Leonard Nicholson - Space Shuttle Program Manager (JSC)
Brewster Shaw - Deputy Space Shuttle Program Manager (KSC)

Office of Space Systems Development

Arnold D. Aldrich - Associate Administrator
Michael T. Lyons - Deputy Associate Administrator (Flight Systems)
Lewis Peach, Jr. - Director, Advanced Programs
George Levin - Chief, Advanced Space Systems
Michael Card - Program Manager, SHOOT

Office of Advanced Concepts and Technology

Gregory M. Reck - Associate Administrator (Acting)
Jack Levine - Director (Acting), Flight Projects Division
Andrew B. Dougherty - Spacehab Utilization Program Manager
Richard H. Ott - Director (Acting), Space Processing Division
Ana M. Villamil - Deputy Director (Acting), 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
John "Tip" Talone - Endeavour 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

MARSHALL SPACE FLIGHT CENTER, HUNTSVILLE, ALA.

Thomas J. Lee - Director
Dr. J. Wayne Littles - Deputy Director
Harry G. Craft, Jr. - Manager, Payload Projects Office
Alexander A. McCool - Manager, Shuttle Projects Office
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, 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


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STS-57 PRESS KIT

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STS-57 General Release
FIRST SPACEHAB FLIGHT HIGHLIGHTS STS-57 SHUTTLE MISSION

RELEASE:  93-78


     The beginning of a new era in the commercial development of space and the
retrieval of a European satellite highlight NASA's Shuttle Mission STS-57. The
mission, scheduled for early June 1993, also will see Space Shuttle Endeavour
and her six-person crew use experiments designed by and for students, operate a
payload which may improve crystal growth techniques and demonstrate possbile
on-orbit refueling techniques.

     A rendezvous with the European Space Agency's European Carrier (EURECA)
satellite is scheduled to take place on the fourth day of the mission.  The
Shuttle's robot arm will be used to grapple the satellite.  It then will be
lowered into Endeavour's cargo bay and stowed so it can be returned to Earth.
The EURECA satellite has been on-orbit collecting data since its deployment
during Shuttle Mission STS-46 in July 1992.

     On STS-57, NASA will be leasing a privately-developed mid-deck
augmentation module known as SPACEHAB. The primary objective is to support the
agency's commercial development of space program by providing additional access
to crew-tended, mid-deck locker or experiment rack space.  This access is
necessary to test, demonstrate or evaluate techniques or processes in
microgravity.

     NASA's secondary objective is to foster the development of space
infrastructure which can be marketed by private firms to support commercial
microgravity research payloads.  In this instance, SPACEHAB, Inc., has the
capability of leasing SPACEHAB facility space to other commercial customers on
upcoming flights of the module.

     The experiments flying inside this first SPACEHAB include investigations
ranging from drug improvement, feeding plants, cell splitting, the first
soldering experiment in space by American astronauts and high-temperature
melting of metals.

     Included are 13 commercial development of space experiments in material
processing and biotechnology, one NASA biotechnology experiment and five other
NASA investigations related to human factors and the Endeavor's environment and
a space station environmental control system test.

     Three other payloads, the Get Away Special (GAS), the Consortium for
Materials Development in Space Complex Autonomous Payload-IV (CONCAP-IV) and
the Superfluid On-Orbit Transfer (SHOOT) payload will be carried in Endeavour's
cargo bay.

     The GAS system, which has flown many times on the Space Shuttle, allows
indiviudals and organizations around the world access to space for scientific
research.  During the STS-57 mission, 10 GAS payloads from the United States,
Canada, Japan and Europe will perform a variety of microgravity experiments.

     The CONCAP-IV payload is the fourth area of investigation in a series of
payloads.  It will investigate the growth of nonlinear organic crystals by a
novel method of physical vapor transport in the weightlessness of the space
environment.  Nonlinear optical materials are the key to many optical
applications now and in the future with optical computing being a prime
example.

     The SHOOT payload is designed to develop and demonstrate the technology
required to re-supply liquid helium containers in space.  Because so little
experience exists with cryogen management in microgravity, SHOOT is designed to
gather data about how the liquid feeds to pumps, the behavior of the
liquid/vapor discriminators and the slosh and cool down of the liquid.  Middeck
Experiments

     Two experiments which previously have flown aboard the Shuttle will be
carried in Endeavour's middeck area.  The Fluid Acquisition and Resupply
Experiment (FARE), which last flew on Shuttle Mission STS-53 in November 1992,
will continue to investigate the fill, refill and expulsion characteristics of
simulated propellant tanks.  It also will study the behavior of liquid motion
in microgravity.

     The Air Force Maui Optical System (AMOS) is an electro-optical facility
located on the Hawaiian Island of Maui. The primary objectives of AMOS are to
use the orbiter during flights over Maui to obtain imagery and/or signature
data from the ground-based sensors.

Spacewalk on STS-57

     STS-57 crew members David Low and Jeff Wisoff will perform a 4-hour
extravehicular activity (EVA) on the fifth day of the flight as a continuation
of a series of spacewalks NASA plans to conduct to prepare for construction of
the space station.

     The spacewalk tests, the first of which was performed on STS-54 in January
1993, are designed to refine training methods for spacewalks, expand the EVA
experience levels of astronauts, flight controllers and instructors, and aid in
better understanding the differences between true weightlessness and the ground
simulations used in training.

     In addition, since the Shuttle's remote manipulator system mechanical arm
will be aboard Endeavour to retrieve EURECA, the STS-57 spacewalk will assist
in refining several procedures being developed to service the Hubble Space
Telescope on mission STS-61 in December.

Education

     NASA's on-going educational efforts will be represented by two payloads.
The Get-Away Special (GAS) #324 - CAN DO experiment is designed to take 1,000
photos of the Earth allowing students to make observations and document global
change by comparing the CAN DO photos with matched Skylab photos.

     The primary payload of CAN DO, known as GEOCAM, contains four Nikon 35mm
cameras equipped with 250 exposure film backs.  The GEOCAM system will match
closely the larger Skylab film format in both coverage and quality allowing
direct examination and comparison of the changes that have occurred to the
planet in the last 20 years.  The canister also contains 350 small, passive,
student experiments.

     STS-57 crew members will take on the role of teacher as they educate
students from around the world about their mission objectives and what it is
like to live and work in space by using the Shuttle Amateur Radio Experiment
(SAREX) experiment.  Brian Duffy and Janet Voss will operate SAREX. Operating
times for school contacts are planned into the crew's activities.

Mission Summary

     Leading the six-person STS-57 crew will be Mission Commander Ronald Grabe
who will be making his fourth space flight.  Pilot for the mission is Brian
Duffy, making his second flight.  Leading the science team will be Payload
Commander David Low who also is designated as Mission Specialist 1 (MS1) and is
making his third flight.  The three other mission specialists for this flight
are Nancy Sherlock (MS2), Jeff Wisoff (MS3) and Janice Voss (MS4), all of whom
will be making their first flight.

     The mission duration for STS-57 is planned for 6 days, 23 hours, 19
minutes.  However, the mission may be extended by 1 day immediately after
launch if projections calculated at that time for energy and fuel use during
the EURECA rendezvous permit.  If for some reason STS-57 remains a 7-day
flight, the extravehicular activity scheduled for flight day five would be
cancelled.  The STS- 57 mission will conclude with a landing at Kennedy Space
Center's Shuttle

Landing Facility.

     This will be the fourth flight of Space Shuttle Endeavour and the 56th
flight of the the Space Shuttle system.

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STS-57 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.



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STS-57 Quick Look

Launch Date/Site:       June 3, 1993/Kennedy Space Center - Pad 39A
Launch Window:          6:13 p.m. - 7:24 p.m. EDT
Orbiter:                        Endeavour (OV-105) - 4th Flight
Orbit/Inclination:      250 nautical miles/28.45 degrees
Mission Duration:       6 days, 23 hours, 19 minutes
Landing Date:           June 10
Primary Landing Site:   Kennedy Space Center, Fla.
Abort Landing Sites:    Return to Launch Site - KSC, Fla.
 TransAtlantic Abort landing     - Banjul, The Gambia
                        - Ben Guerir, Morroco
                        - Moron, Spain
 Abort Once Around      - Edwards AFB, Calif.

Crew:   Ronald Grabe, Commander (CDR)
        Brian Duffy, Pilot (PLT)
        David Low, Payload Commander/Mission Specialist 1 (MS1)
        Nancy Sherlock, Mission Specialist 2 (MS2)
        Jeff Wisoff, Mission Specialist 3 (MS3)
        Janice Voss, Mission Specialist 4 (MS4)

Cargo Bay Payloads:     EURECA-1R (European Retrievable Carrier - Retrieval)
                        SPACEHAB (Space Habitation Module)
                        SHOOT (Super-fluid Helium On-Orbit Transfer)
                        CONCAP-IV (Consortium for Materials Development in
                                Space Complex Autonomous Payload-IV)
                        GAS Bridge (Get-Away Special Bridge)

In-Cabin Payloads:      AMOS (Air Force Maui Optical Site)
                        FARE (Fluid Acquisition and Resupply Experiment)
                        SAREX-II (Shuttle Amateur Radio Experiment-II)

DTOs/DSOs:
   DTO 412:        On-orbit Fuel Cell Shutdown
   DTO 623:        Cabin Air Monitoring
   DTO 700-2:      Laser Range, Range-Rate Device
   DSO 603B:       Orthostatic Function During Entry, Landing and Egress
   DSO 604 OI-1:   Visual Vestibular Integration as a Function of Adaptation
   DSO 618:        Effects of Intense Exercise During Space Flight on
                   Aerobic Capacity and Orthostatic Function
   DSO 624:        Pre-Flight and Post-Flight Measurement of
                   Cardiorespiratory Response
   DSO 901:        Documentary Television
   DSO 902:        Documentary Motion Picture Photography
   DSO 903:        Documentary Still Photography


STS-57 VEHICLE AND PAYLOAD WEIGHTS


Vehicle/Payload Pounds

Orbiter (Endeavour) empty and 3 Shuttle Main Engines    173,023

Spacehab-1/support hardware     9,628

EURECA (berthed)        9,800

GAS bridge, cans        5,652

SHOOT/support hardware  3,570

FARE    126

SAREX-II        46

Total Vehicle at solid rocket booster Ignition  4,516,091

Orbiter Landing Weight  224,111



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STS-57 SUMMARY TIMELINE

   NOTE: The STS-57 mission is planned to be 6 days, 23 hours, 19 minutes long.
However, it may be extended by 1 day immediately after launch if projections
calculated at that time for energy and fuel use during the EURECA rendezvous
permit.  If STS-57 remains a 6-day (MET) flight, the extravehicular activity
scheduled for flight day five would be cancelled.  Activities planned for the
first four flight days would be unchanged.  Flight control system checkout,
reaction control system hot-fire and Spacehab deactivation would take place on
flight day seven.  Entry and landing would be on flight day eight.

   The following is a schedule for the extended, 7-day, 23-hour (MET) mission:

Flight Day One                       Flight Day Six
Ascent                               Spacehab operations
OMS-2 (251 n.m. x 169 n.m.)          FARE operations
Spacehab activation
Spacehab operations
NC-1 burn (251 n.m. x 174 n.m.)

Flight Day Two                       Flight Day Seven
Remote manipulator system checkout   Spacehab operations
SHOOT operations                     FARE operations
Spacehab operations
NC-2 burn (251 n.m. x 178 n.m.)

Flight Day Three                     Flight Day Eight
SHOOT operations                     Spacehab operations
Spacehab operations                  Flight control systems checkout
NC-3 burn (251 n.m. x 184 n.m.)      Reaction control system hot-fire
                                     Spacehab deactivation
Flight Day Four                      Cabin stow
EURECA retrieval
NSR burn (251 n.m. x 248 n.m.)       Flight Day Nine
NH-4 burn (257 n.m. x 250 n.m.)      Spacehab deactivation completed
TI-burn (259 n.m. x 256 n.m.)        Deorbit preparations
EURECA grapple                       Deorbit burn
EURECA berth                         Entry
Spacehab operations                  Landing

Flight Day Five
Extravehicular activity preparations
Extravehicular activity (4 hours)


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:

        o 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.

        o Abort-Once-Around (AOA) -- Earlier main engine shutdown with the
capability to allow one orbit around before landing at Edwards Air Force Base,
Calif.

        o 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.

        o 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-57 contingency landing sites are the Kennedy Space Center, Edwards Air
Force Base, Banjul, Ben Guerir and Moron.




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STS-57 Orbital Events Summary (for 1-day extended mission)

EVENT           START TIME                      VELOCITY CHANGE       ORBIT
               (dd/hh:mm:ss)                   (feet per second)      (n.m.)

OMS-2           00/00:44:00                        241 fps         251 x 169

NC-1            00/05:21:00                        8 fps           251 x 174
(adjusts the rate at which Endeavour is closing on EURECA)

SH-1            00/22:18:00                        3.4 fps         251 x 176
(performed as part of the Super Fluid Helium On-Orbit Transfer experiment)

NPC             01/03:04:00                        6.2 fps         251 x 175
(aligns Endeavour's orbit directly below EURECA's orbit)

NC-2            01/04:28:00                        4 fps           251 x 178
(adjusts the rate at which Endeavour is closing on EURECA)

SH-2            01/19:53:00                        3.6 fps         251 x 180
(performed for the SHOOT experiment)

SH-3            01/21:26:00                        3.6 fps         251 x 182
(performed as part of the SHOOT experiment)

NC-3            02/03:36:00                          4 fps         251 x 184
(adjusts the rate at which Endeavour is closing on EURECA)

NSR             02/19:03:00                        109 fps         251 x 248
(circularizes Endeavour's orbit)

NH              02/21:27:00                         15 fps         257 x 250
(adjusts the altitude of Endeavour's orbit)

NC-4            02/21:27:00                         8.6 fps        258 x 255
(adjusts the rate at which Endeavour is closing on EURECA)

TI              03/00:35:00                         3.1 fps        258 x 256
(begins Endeavour's proximity operations with EURECA)

GRAPPLE         03/02:50:00                                        259 x 256

DEORBIT         07/21:36:00                         414 fps

LANDING         07/23/19:00

NOTE: Engine firings are likely to change slightly after launch as they are
recalculated by flight controllers.  In addition, some of the smaller firings
may be deleted altogether if navigation information during the rendezvous
allows.  However, the time frame and other information regarding the larger
burns is unlikely to change dramatically.

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STS-57 CREW RESPONSIBILITIES

TASK/PAYLOAD            PRIMARY         BACKUP

EURECA-RMS              Low             Sherlock
EURECA systems          Sherlock        Duffy
EURECA rendezvous       Grabe           Duffy, Wisoff
EVA                     Low, Wisoff     N/A
EVA-RMS                 Sherlock        Voss
Spacehab systems        Low             Voss
SHOOT                   Voss            Wisoff
FARE                    Wisoff          Duffy
GBA                     Sherlock        Grabe
SAREX                   Duffy           Voss

SPACEHAB experiments:

ASPECS                  Wisoff          Sherlock
BPL                     Sherlock        Wisoff
CR/IM-VDA               Low             Voss
HFA: EPROC              Voss            Sherlock
HFA: Light, sound       Grabe           Duffy
HFA: Trans              Sherlock        Grabe
NBP                     Duffy           Grabe
PSE                     Grabe           Voss
SCG                     Voss            Low
TES-COS                 Voss            Grabe
APCF                    Voss            Low
ASC-2                   Sherlock        Duffy
CGBA                    Wisoff          Voss, Low
CPDS                    Voss            Low
3DMA                    Voss            Low
ECLIPSE-HAB             Voss            Low
EFE                     Low             Sherlock
GPPM                    Voss            Low
IPMP                    Grabe
LEMZ-1                  Voss            Wisoff
ORSEP                   Voss            Low
SAMS                    Voss            Low
ZCG                     Voss            Low





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SPACEHAB-01

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EUROPEAN RETRIEVABLE CARRIER (EURECA)

F. Schwan - Industrial Project Manager
  Deutsche Aerospace, ERNO Raumfahrttechnik
  Bremen, Germany

W. Nellessen - ESA Project Manager
  ESTEC Noordwijk, The Netherlands

     The European Space Agency's (ESA) EURECA spacecraft was launched on July
31, 1992, by the Space Shuttle Atlantis (STS-46) and deployed at an altitude of
230 nautical miles (425 km).  It ascended using its own propulsion to the
operational orbit of 270 nautical miles (500 km).  Several weeks prior to the
STS 57 launch, ground controllers will lower EURECA's altitude where it will be
retrieved by Endeavour and brought back to Earth.

     The EURECA-1 mission primarily has been devoted to research in the fields
of material and life sciences and radiobiology, all of which require a
controlled microgravity environment.  The selected microgravity experiments
have been carried out in seven facilities.  The remaining payload comprises
space science and technology.

     During the mission, EURECA's residual carrier accelerations have not
exceeded 10-5g.  The platform's altitude and orbit control system made use of
magnetic torquers augmented by cold gas thrusters to keep disturbance levels
below 0.3 Nm during the operational phase.

Physical characteristics

o Launch mass   9,900 lbs (4491 kg)
o Electrical power solar array  5000 W
o Continuous power to EURECA experiments        1000 W
o Launch configuration  dia: 14.76 ft (4.5 m.)
        length:  8.33 ft (2.54 m)
o Volume        132 cubic ft (40.3 m)
o Solar array extended  66 ft x 11.5 ft (20 m x 3.5 m)

User friendliness

     Considerable efforts have been made during the design and development
phases to ensure that EURECA is a "user friendly" system.  As is the case for
Spacelab, EURECA has standardized structural attachments, power and data
interfaces.  Unlike Spacelab, however, EURECA has a decentralized payload
control concept.  Most of the onboard facilities have their own data handling
device so that investigators can control the internal operations of their
equipment directly.  This approach provides more flexibility as well as
economical advantages.


Operations

     All EURECA operations are controlled by ESA's Space Operations Centre
(ESOC) in Darmstadt, Germany. During the deployment and retrieval operations,
ESOC functions as a Remote Payload Operations Control Centre to NASA's Mission
Control Center, Houston, and the orbiter is used as a relay station for all the
commands.

     Throughout the operational phase, ESOC has controlled EURECA through two
ground stations at Maspalomas, Canary Islands (Spain), and Kourou, French
Guiana. EURECA has been in contact with its ground stations for a relatively
short period each day.  When it was out of contact, its systems operated with a
high degree of autonomy, performing failure detection, isolation and recovery
activities to safeguard ongoing experimental processes.

     An experimental advanced data relay system, the Inter-orbit Communication
Package, was included in the payload.  This package communicated with the
European Olympus Communication Satellite to demonstrate the possible
improvements for future communications with data relay satellites.  Such a
system will significantly enhance real time data coverage.

EURECA Retrieval Operations

     The EURECA free-flying experiment platform will be retrieved on the fourth
day of STS-57. EURECA was deployed from Atlantis on STS-46 on Aug. 1, 1992.
During its approximately10-month stay in orbit, EURECA has supported
investigations in processing metallurgical samples, growing crystals and
conducting biological and biochemical studies.  Several weeks before the STS-57
launch, EURECA controllers will lower the spacecraft's orbit from 270 nautical
miles (500 km) high to 257 nautical miles (300 km) in preparation for the
retrieval.

     David Low will grasp the 5-ton EURECA with the Shuttle's robot arm and
lower the platform into latches in the aft cargo bay.



     Beginning on flight day one, a series of engine firings will adjust
Endeavour's catch-up rate so that on the morning of flight day four, a final
altitude adjustment burn will move Endeavour up to the 257-nautical-mile EURECA
orbit.  During the catch-up maneuvers, Endeavour's onboard navigational star
trackers will sight on EURECA during the best lighting period, from noon to
sunset of each orbit, to provide the most accurate course correction
information for each maneuver.

     For the final mid-course corrections, the crew will use Endeavour's
rendezvous radar to refine their information about the position of EURECA in
relation to Endeavour. For about the final one and a half miles of Endeavour's
approach to EURECA, Commander Ron Grabe will fly the Shuttle's maneuvers
manually.

EURECA RETRIEVABLE CARRIER

Structure

     The EURECA structure is made of high strength carbon-fibre struts and
titanium nodal points joined together to form a framework of cubic elements.
This provides relatively low thermal distortions, allows high alignment
accuracy and simple analytical verification, and is easy to assemble and
maintain.

Larger assemblies are attached to the nodal points.  Instruments weighing less
than 220 lbs (100 kg) are assembled on standard equipment support panels
similar to those on a Spacelab pallet.

Thermal Control

     Thermal control for EURECA combines active and passive heat transfer and
radiation systems.  Active transfer, required for payload facilities which
generates more heat, is achieved by means of a freon cooling loop which
dissipates the thermal load through two radiators into space.  The passive
system makes use of multilayer insulation blankets combined with electrical
heaters.  During nominal operations, the thermal control subsystem rejects a
maximum heat load of about 2300 W.

Electrical Power

     The electrical power subsystem generates, stores, conditions and
distributes power to all the spacecraft subsystems and to the payload.  The
deployable and retractable solar arrays, with a combined raw power output of
some 5000 W together with four 40 Ah nickel-cadmium batteries, provide the
payload with a continuous power of 1000 W, nominally at 28 V, with peak power
capabilities of up to 1500 W for several minutes.

Attitude and Orbit Control

     A modular attitude and orbit control subsystem (AOCS) was used for
attitude determination and spacecraft orientation and stabilization during all
flight operations and orbit control maneuvers.

     An orbit transfer assembly, consisting of two redundant sets of four
thrusters was used to boost EURECA to its operation attitude at 500 km and to
return it to its retrieval orbit at about 300 km.

     EURECA has been developed under ESA contract by DASA (Deutsche
Aerospace/ERNO Raumfahrttechnik) (Germany), and their subcontractors Sener
(Spain), AIT (Italy), SABCA (Belgium), AEG (Germany), Fokker (The Netherlands),
Matra (France), Snia BPD (Italy), BTM (Belgium) and Laben (Italy).

EURECA SCIENCE

Solution Growth Facility - a multi-user facility dedicated to the growth of
monocrystals from solution, consisting of a set of four reactors and their
associated control system.

Protein Crystallization Facility - a multi-user solution growth facility for
protein crystallization in space.  The object of the experiments is the growth
of single, defect-free protein crystals of high purity and of a size sufficient
to determine their molecular structure by x-ray diffraction.

Exobiology and Radiation Assembly - a multi-user life science facility for
experiments on the biological effects of space radiation.

Multi-Furnace Assembly - a multi-user facility dedicated to material science
experiments.  It is a modular facility with a set of common system interfaces
which incorporates 12 furnaces of three different types, giving temperatures of
up to 1400 degrees C.

Automatic Mirror Furnace - an optical radiation furnace designed for the growth
of single, uniform crystals from the liquid or vapor phases, using the
traveling heater or Bridgman methods.

Surface Forces Adhesion Instrument - studies the dependence of surface forces
and interface energies on physical and chemical-physical parameters such as
surface topography, surface cleanliness, temperature and the deformation
properties of the contacting bodies.

High Precision Thermostat Instrument - an instrument designed for long term
experiments requiring microgravity conditions and high precision temperature
measurement and control.

Solar Constant And Variability Instrument - designed to investigate the solar
constant, its variability and its spectral distribution, and measure:

 o       fluctuations of the total and spectral solar irradiance
 o       short term variations of the total and spectral solar irradiance
         within time scales ranging from hours to few months, and
 o       long term variations of the solar luminosity in the time scale
         of years (solar cycles) by measuring the absolute solar irradiance.

Solar Spectrum Instrument - designed to study solar physics and the solar-
terrestrial relationship in aeronomy and climatology.  It measures the absolute
solar irradiance and its variations in the spectral range from 170 to 3200 nm,
with an expected accuracy of 1 percent in the visible and infrared ranges and 5
percent in the ultraviolet range.

Occultation Radiometer Instrument - designed to measure aerosols and trace gas
densities in the Earth's mesosphere and stratosphere.

Wide Angle Telescope - designed to detect celestial gamma and X-ray sources
with photon energies in the range 5 to 200 keV and determine the position of
the source.

Timeband Capture Cell Experiment - an instrument to study the microparticle
population in near-Earth space -- typically Earth debris, meteoroids and
cometary dust.

Radio Frequency Ionization Thruster Assembly - designed to evaluate the use of
electric propulsion in space and to gain operational experience before
endorsing its use for advanced spacecraft technologies.

Advanced Solar Gallium Arsenide Array - to provide valuable information on the
performance of gallium arsenide (GaAs) solar arrays and on the effects of the
low Earth orbit environment on their components.

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:6_4_3.TXT

PROPELLANTS

     Sir Isaac Newton stated in his Third Law of Motion that "every
action is accompanied by an equal and opposite reaction." A rocket
operates on this principle. The continuous ejection of a stream of
hot gases in one direction causes a steady motion of the rocket in
the opposite direction.
     A jet aircraft operates on the same principle, using oxygen in
the atmosphere to support combustion for its fuel. The rocket engine
has to operate outside the atmosphere, and so must carry its own
oxidizer.
     The gauge of efficiency for rocket propellants is specific
impulse, stated in seconds. The higher the number, the "hotter" the
propellant.
     Specific impulse is the period in seconds for which a 1-pound
(0.45-kilogram) mass of propellant (total of fuel and oxidizer) will
produce a thrust of 1 pound (0.45 kilogram) of force. Although
specific impulse is a characteristic of the propellant system, its
exact value will vary to some extent with the operating conditions
and design of the rocket engine. It is for this reason that different
numbers are often quoted for a given propellant or combination of
propellants.
     NASA and commercial launch vehicles use four types of
propellants: (1) petroleum; (2) cryogenics; (3) hypergolics; and (4)
solids.


Petroleum

     The petroleum used as a rocket fuel is a type of kerosene
similar to the sort burned in heaters and lamps. However, the rocket
petroleum is highly refined, and is called RP-1 (Refined Petroleum).
It is burned with liquid oxygen (the oxidizer) to provide thrust.
     RP-1 is a fuel in the first-stage boosters of the Delta and
Atlas/Centaur rockets. It also powered the first stages of the Saturn
1B and Saturn V. RP-1 delivers a specific impulse considerably less
than that of cryogenic fuels.


Cryogenic

     Cryogenic propellants are liquid oxygen (LOX), which serves as
an oxidizer, and liquid hydrogen (LH2), which is a fuel. The word
cryogenic is a derivative  of the Greek kyros, meaning "ice cold."
LOX remains in a liquid state at temperatures of minus 298 degrees
Fahrenheit (-183 degrees Celsius). LH2 remains liquid at temperatures
of minus 423 degrees Fahrenheit (-253 degrees Celsius).
     In gaseous form, oxygen and hydrogen have such low densities
that extremely large tanks would be required to store them aboard a
rocket. But cooling and compressing them into liquids vastly
increases their density, making it possible to store them in large
quantities in smaller tanks.
     The distressing tendency of cryogenics to return to gaseous
form unless kept supercool makes them difficult to store over long
periods of time, and hence less satisfactory as propellants for
military rockets, which must be kept launch-ready for months at a
time.
     But the high efficiency of the liquid hydrogen/liquid oxygen
combination makes the low-temperature problem worth coping with when
reaction time and storability are not too critical. Hydrogen has
about 40 percent more "bounce to the ounce" than other rocket fuels,
and is very light, weighing about one-half pound (0.45 kilogram) per
gallon (3.8 liters). Oxygen is much heavier, weighing about 10 pounds
(4.5 kilograms) per gallon (3.8 liters).
     The RL-10 engines on the Centaur, the United States' first
liquid hydrogen rocket stage, have a specific impulse of 444 seconds

The J-2 engines used on the Saturn V second and third stages, and on
the second stage of the Saturn 1B, also burned the LOX/LH2
combination. They had specific impulse ratings of 425 seconds.
      For comparison purposes, the liquid oxygen/kerosene combination
used in the cluster of five F-1 engines in the Saturn V first stage
had specific impulse ratings of 260 seconds. The same propellant
combination used by the booster stages of the Atlas/Centaur rocket
yielded 258 seconds in the booster engine and 220 seconds in the
sustainer.
     The high efficiency engines aboard the Space Shuttle orbiter use
liquid hydrogen and oxygen and have a specific impulse rating of 455
seconds. The fuel cells in an orbiter use these two liquids to
produce electrical power through a process best described as
electrolysis in reverse. Liquid hydrogen and oxygen burn clean,
leaving a by-product of water vapor.
     The rewards for mastering LH2 are substantial. The ability to
use hydrogen means that a given mission can be accomplished with a
smaller quantity of propellants (and a smaller vehicle), or
alternately, that the mission can be accomplished with a larger
payload than is possible with the same mass of conventional
propellants. In short, hydrogen yields more power per gallon.

Hypergolic

     Hypergolic propellants are fuels and oxidizers which ignite on
contact with each other and need no ignition source. This easy start
and restart capability makes them attractive for both manned and
unmanned spacecraft maneuvering systems. Another plus is their
storability -- they do not have the extreme temperature requirements
of cryogenics.
     The fuel is monomethyl hydrazine (MMH) and the oxidizer is
nitrogen tetroxide (N2O4).
     Hydrazine is a clear, nitrogen/hydrogen compound with a "fishy"
smell. It is similar to ammonia. Nitrogen tetroxide is a reddish
fluid. It has a pungent, sweetish smell. Both fluids are highly
toxic, and are handled under the most stringent safety conditions.
Hypergolic propellants are used in the core liquid propellant stages
of the Titan family of launch vehicles, and on the second stage of
the Delta.
     The Space Shuttle orbiter uses hypergols in its Orbital
Maneuvering Subsystem (OMS) for orbital insertion, major orbital
maneuvers and deorbit. The Reaction Control System (RCS) uses
hypergols for attitude control.
     The efficiency of the MMH/N2O4 combination in the Space Shuttle
orbiter ranges from 260 to 280 seconds in the RCS, to 313 seconds in
the OMS. The higher efficiency of the OMS system is attributed to
higher expansion ratios in the nozzles and higher pressures in the
combustion chambers.


Solid

     The solid propellant motor is the oldest and simplest of all
forms of rocketry, dating back to the ancient Chinese. It's simply a
casing, usually steel, filled with a mixture of solid-form chemicals
(fuel and oxidizer) which burn at a rapid rate, expelling hot gases
from a nozzle to achieve thrust.
     Solids require no turbopumps or complex propellant-feed systems.
A simple squib device at the top of the motor directs a
high-temperature flame along the surface of the propellant grain,
igniting it instantaneously.
     The propellant, a rubbery substance with the consistency of a
hard rubber eraser, has a star-shaped (other shapes are possible)
hollow channel extending through the center.  When ignited, the
propellant burns from the center out towards the sides of the casing.
The shaped center channel exposes more or less burning area at any
given point in time, providing a means to vary the thrust of the
expelled gases.
     Solid propellants are stable and easily storable. Unlike
liquid-propellant engines, though, a solid-propellant motor cannot be
shut down. Once ignited, it will burn until all the propellant is
exhausted.
     Solids have a variety of uses for space operations. Small solids
often power the final stage of a launch vehicle, or attach to payload
elements to boost satellites and spacecraft to higher orbits.
     Medium solids such as the Payload Assist Module (PAM) and the
Inertial Upper Stage (IUS) provide the added boost to place
satellites into geosynchronous orbit or on planetary trajectories.
     The PAM-DII provides a boost for Delta and Space Shuttle
payloads. The IUS goes on the Space Shuttle and the Titan III class
of launch vehicles.
     Only one of the nation's stable of launch vehicles, Scout, uses
solids exclusively. This four-stage rocket launches small satellites
to orbit.
     Titan, Delta and Space Shuttle vehicles depend on solid rockets
to provide added thrust at liftoff.
     The Space Shuttle uses the largest solid rocket motors ever
built and flown. Each reusable booster contains 1.1 million pounds
(453,600 kilograms) of propellant.
     This propellant consists of an aluminum powder (16 percent) as a
fuel; ammonium perchlorate (69.93 percent) as an oxidizer; iron
oxidizer powder (0.07 percent) as a catalyst; polybutadiene acrylic
acid acrylonitrile (12.04 percent) as a rubber-based binder; and an
epoxy-curing agent (1.96 percent). The binder and epoxy also burn as
a fuel, adding thrust.
     The specific impulse of the Space Shuttle solid rocket booster
propellant is 242 seconds at sea level and 268.6 seconds in a vacuum.

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
=--=--=-END-=--=--=

=--=--=START=--=--= NASA Spacelink File Name:6_5_2_3.TXT

                            ION PROPULSION THEORY


In an Ion Propulsion Engine, the Sun provides energy, which is converted into
electric power by solar cells.  The power is then conditioned to the current
and voltage needed by the ion thruster.  Propellant is ionized in the thruster
and electrically exhausted to produce thrust.  For many missions, the power
source can serve the dual roles of providing both thruster power and power
for mission objectives subsequent to the thrusting period.  The thruster
will be of appropriate size to satisfy the thrust requirements for the
particular propulsion task.

    The main advantage of using electric propulsion  is that the electric
energy added to the exhaust propellant greatly increases its velocity, or
specific impulse; and hence more thrust is produced with the same propellant
flow rate.  The mass of propellant required to produced a given thrust
decreases with increasing specific impulse.  The saving in propellant mass,
however, is offset by the increasingly massive powerplant required to
accelerate the exhaust to higher velocities.  The maximum payload of a
spacecraft is achieved at the optimum specific impulse.

    At low specific impulse the propellant mass can be excessively large, while
at high specific impulse the powerplant mass becomes excessive.
Between these two extremes is a broad useful range where sufficient payload
remains for design of a practical spacecraft.  Payload includes the mass of the
spacecraft itself and the useful payload.  The optimum value of specific
impulse to maximize payload usually is between 2000 and 5000 seconds, and thus
the optimum value of exhaust velocity is between 20 000 and 50 000 meters per
second.  This range of exhaust velocity is easily achieved with ion thrusters
and, as is discussed later, results in large increases in spacecraft payload
over a large variety of missions.

     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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=--=--=START=--=--= NASA Spacelink File Name:9_11_4_6_4_2.TXT

Program STSORBIT PLUS

Space Shuttle and Satellite Orbit Simulation

(Enhanced Version for 286/386/486 Computers)




INTRODUCTION
------------

     Program STSORBIT PLUS is an enhanced version of STSORBIT, my original
orbital tracking and display program. As a general rule, a 286 or better
computer (AT-class IBM compatible) is recommended. A math coprocessor chip
will significantly improve performance and is REQUIRED for acceptable
performance in orthographic modes. Some users report acceptable performance
on faster XT-class machines WITH a math coprocessor. The program is
intended for use during Space Shuttle missions and for general satellite
tracking using NASA/NORAD 2-Line Orbital Elements.

     Program STSORBIT PLUS (which I will usually refer to as STSPLUS from
here on) is intended to display the position and ground track of an
orbiting satellite on a selection of maps ranging from a full map of the
world to zoom maps showing considerable detail. The program has special
features implemented at the request of NASA astronauts and others for use
during a NASA Space Shuttle mission. With the appropriate 2-line elements,
STSPLUS displays the position and ground track of a variety of satellites,
such as the Space Shuttle, the Hubble Space Telescope, the Gamma Ray
Observatory, or the Soviet MIR Space Station. Accurate TDRS coverage is
calculated for satellites which use that network for communications.
Special Location and Tracking Station displays show concentric isocontours,
circles of equal satellite altitude; these special maps can be especially
valuable for visual or amateur radio sightings.


HARDWARE AND SOFTWARE REQUIREMENTS
----------------------------------

     An AT-class computer equipped with a 286 processor (running at 8 MHz)
and a 287 math coprocessor chip is the minimum system used for all program
testing and development. While other systems may give acceptable
performance, this minimum configuration assures that most features will
execute as described and in real time. Performance with 386/387 and 486
systems will be considerably superior to 286 systems. Note that NO TESTING
is performed on systems not equipped with a math coprocessor chip. The
following minimum hardware is recommended:

          286/386/486 IBM-compatible computer
          287/387 math coprocessor chip
          VGA color display
          Hard disk with 3MB available
          RAM disk with at least 500K space

     The 287/387 math coprocessor chip is HIGHLY RECOMMENDED and is
required for some processors to operate in real time. The calculations
relating to orbital mechanics are very complex and STSPLUS will use the
coprocessor chip if one is equipped; performance is improved by about an
order of magnitude. Other "fast" processor and coprocessor combinations may
yield acceptable performance. A SLOW MODE is provided to accommodate slower
machines. However, math coprocessor chips are now reasonably inexpensive,
particularly for 286 systems, and the performance improvement is impressive
and well worth the modest cost. As an example, my vintage Zenith laptop is
equipped with an 80C88 processor and an 8087 math coprocessor and is just
able to keep up in real time when running at a clock speed of 8 MHz
(although map drawing times are very slow). However, an 8 MHz 286 (AT-
class) computer without a math coprocessor is NOT able to execute the
program correctly except in the SLOW mode and map drawing times are
painfully slow.

     STSPLUS is intended to be used with an EGA or VGA video adapter and a
color monitor; with these adapters, the display is in color. Because of its
improved vertical resolution, the VGA is recommended over the EGA. A
monochrome VGA display with shades of gray may also be used with the
program (with the "/M" command line option). Because of hardware
limitations, CGA and HGC systems can only present graphics in monochrome;
although those display adapters are supported in current versions of
STSPLUS, that support may NOT continue in future versions. The original
STSORBIT will continue to support CGA and HGC monitors.

     A hard disk is recommended for performance in program and file loading
and for storage of orbital elements files. A RAM disk with sufficient space
to hold the program and its various data files is also recommended for
improved performace, especially for reduced map drawing times.

     Although the program may execute properly on other software operating
systems, STSPLUS has been designed and tested using standard configurations
of Microsoft DOS 3.3 and 5.0. No optional Terminate and Stay Resident
programs (TSR's) or "shell" programs have been tested. Third party memory
management programs and Digital Research DRDOS 6.0 may experienc problems
with internal memory allocation performed by the Microsoft BASIC Compiler;
however, I'm told that the latest release of DRDOS 6.0 works correctly.


STSORBIT PLUS FILES
-------------------

     STSORBIT PLUS is normally distributed via bulletin board systems in
archived form using the ZIP format by PKWare. Note that all files (except
map databases) for STSORBIT PLUS are called "STSPLUS" in order to conform
to DOS filename requirements and to avoid confusion with the similarly
named files for the original STSORBIT. The following files are available on
NASA SpaceLink BBS:

          SOP9320A.ZIP       STSORBIT PLUS Version 9320, Part 1 of 2
          SOP9320B.ZIP       STSORBIT PLUS Version 9320, Part 2 of 2
          EARTH3.ZIP         Level 3 Map Database for STSORBIT PLUS

Note that the number, "9320" in the file names above, may change from time
to time as new versions are released. The map database files do not
normally change. The first two files, SOP9320A.ZIP and SOP9320B.ZIP are
REQUIRED. The EARTH3.ZIP adds significantly improved map detail and its
files will be used by STSPLUS if present.
     The program PKUNZIP Version 1.10 or higher is REQUIRED to unpack the
ZIP files. Each ZIP file is unpacked with a command of the form:

          PKUNZIP <filename>

where "<filename>" is the actual name of the file without the quotation
marks.
     The following files are usually included in the standard distribution
(files marked with "*" are available separately):

          STSPLUS.EXE        Main STSPLUS Program     (required)
          STSPLUS.DOC        Documentation            (not required)
          STSPLUS.ICO        Icon for WINDOWS 3       (optional)
          STSPLUS.KEY        STSPLUS Active Keys      (optional)
          STSPLUS.LOC        Map Locations & Features (optional)
          STSPLUS.TRK        NASA Tracking Stations   (optional)
          STSPLUS.CTY        City Coordinates         (optional)
          STSPLUS.INI        Initialization data      (see below)

          EARTH4.MCX         Level 4 Map Index        (required)
          EARTH4.MCP         Level 4 Rect Map Data    (required)
          EARTH4.XYZ         Level 4 Ortho Map Data   (required)
          EARTH3.MCX         Level 3 Map Index        (optional)
          EARTH3.MCP         Level 3 Rect Map Data    (optional)
          EARTH3.XYZ         Level 3 Ortho Map Data   (optional)

          EARTH2.MCX         Level 2 Map Index        (optional) *
          EARTH2.MCP         Level 2 Rect Map Data    (optional) *
          EARTH2.XYZ         Level 2 Ortho Map Data   (optional) *
          EARTH1.MCX         Level 1 Map Index        (optional) *
          EARTH1.MCP         Level 1 Rect Map Data    (optional) *
          EARTH1.XYZ         Level 1 Ortho Map Data   (optional) *

          MSHERC.COM         Hercules driver          (required for HGC)

          NASAnnn.TXT        2-Line Elements          (optional)

          NASA.TRK           NASA Tracking Stations   (not required)
          CIS.TRK            Russian Tracking Stations(not required)
          INTELSAT.TRK       INTELSAT Tracking Stns   (not required)
          SPACENTR.TRK       Other Tracking Stations  (not required)

          README             STSPLUS Questionnaire and Registration
          QUICK.DOC          Quick Start Instructions

Files noted as "(required)" must be in the current default directory for
program operation. Files noted as "(optional)" do not need to be in the
default directory when STSPLUS is operated but provide additional features
or information if present. Files noted as "(optional) *" are too large to
be downloaded on most BBS systems and are available on disk separately. In
order to minimize the disk space required, all .EXE files have been
compressed with PKWare's PKLITE Professional; these files require a brief
additional time to begin execution since they are decompressed "on the fly"
at load time.

     STSPLUS can use map databases with different degrees of map detail.
Level 4, required for operation and included in the minimum distribution
package, contains the minimum detail. Level 1 contains the maximum detail.
As noted in the list above, three files are used for each level of map
detail. MCX files contain an index of the map data, MCP files contain map
coordinates for rectangular projection, and XYZ files contain map
coordinates for orthographic projection. STSPLUS checks for the levels that
are present and uses the level appropriate for the zoom factor in effect
or, if that level is not present, the maximum level that is present. Level
1 is checked first, then Level 2, etc. Level 4 files MUST be present or an
error message is displayed and the program aborts.

                          ***  IMPORTANT NOTE ***

     STSPLUS assumes that if a particular level of map database is
     found ALL lower levels of map database are present. Missing
     levels of map database will cause a program error.

     File NASAnnn.TXT (where "nnn" will be a number such as "072") is a set
of NASA/NORAD 2-line elements as of the date of the file. Note that the
2-line elements should only be used for ten to twenty days after the epoch
date for each satellite if reasonable accuracy is to be maintained. Current
orbital elements are posted on my bulletin board system two or three times
per week. Other files with 2-line elements are also available; they
typically have names like GSFCnnn.TXT or N2L-nnn.TXT for general
satellites, and STSmmNnn.TXT for Space Shuttle missions. Space Shuttle
orbital elements are usually posted at least daily during missions; because
of orbital maneuvers, Space Shuttle elements more than 24 hours old may
yield inaccurate positions.

     Other files, such as 2-line elements for an upcoming Space Shuttle
mission or a mission in progress, may be included from time to time. Files
with filetype .TXT are normally 2-line orbital elements. Some common
satellite name abbreviations are:

          STS       Space Shuttle missions
          HST       Hubble Space Telescope
          GRO       Compton Gamma Ray Observatory
          UARS      Upper Atmosphere Research Satellite
          TOPEX     Topex/Poseidon Earth Resources Satellite
          ROSAT     Roentgen Satellite Observatory
          MIR       Russian Space Station

There are many other satellites for which data is available. US Space
Command currently tracks some 7000+ objects, of which data for more than
700 is usually included in the NASAnnn.TXT files. NASA SpaceLink BBS, (205)
895-0028, usually posts 2-line elements for Space Shuttle missions (usually
labeled as "Keplerian Elements") from time to time prior to and during a
mission.


                                        David H. Ransom, Jr.
                                        7130 Avenida Altisima
                                        Rancho Palos Verdes, CA  90274




     Source:NASA Spacelink    Modem:205-895-0028  Internet:192.149.89.61
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