Suzy B Software 2/Suzy B Software CD-ROM 2 (1994).iso/nasa/nasa34/sts_34.txt

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              SPACE SHUTTLE MISSION STS-34

                   PRESS KIT



                  OCTOBER 1989




















































              SPACE SHUTTLE MISSION STS-34


PUBLIC AFFAIRS CONTACTS

Sarah Keegan/Barbara Selby
Office of Space Flight
NASA Headquarters, Washington, D.C.
(Phone:  [phone])

Charles Redmond/Paula Cleggett-Haleim
Office of Space Science and Applications
NASA Headquarters, Washington, D.C.
(Phone:  [phone])

Jim Ball
Office of Commercial Programs
NASA Headquarters, Washington, D.C.
(Phone:  [phone])

Lisa Malone
Kennedy Space Center, Fla.
(Phone:  [phone])

Kyle Herring
Johnson Space Center, Houston, Texas
(Phone:  [phone])

Jerry Berg
Marshall Space Flight Center, Huntsville, Ala.
(Phone:  [phone])

Mack Herring
Stennis Space Center, Bay St. Louis, Miss.
(Phone:  [phone])

Nancy Lovato
Ames-Dryden Flight Research Facility, Edwards, Calif.
(Phone:  [phone])

Robert J. MacMillin
Jet Propulsion Laboratory, Pasadena, Calif.
(Phone:  [phone])

Jim Elliott
Goddard Space Flight Center, Greenbelt, Md.
(Phone:  [phone])
















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              SPACE SHUTTLE MISSION STS-34


    --TABLE OF CONTENTS

    GENERAL RELEASE                          4
    GENERAL INFORMATION                         6
    LAUNCH PREPARATIONS, COUNTDOWN & LIFTOFF             7
    MAJOR COUNTDOWN MILESTONES                     9
    TRAJECTORY SEQUENCE OF EVENTS                    11
    SPACE SHUTTLE ABORT MODES                    11
    SUMMARY OF MAJOR ACTIVITIES                    12
    LANDING AND POST LANDING OPERATIONS                13
    GALILEO                             14
    GALILEO MISSION EVENTS                        14
    EARTH TO JUPITER                        15
    VENUS                                15
    FIRST EARTH PASS                        15
    FIRST ASTEROID                            16
    SECOND EARTH PASS                        16
    SECOND ASTEROID                         16
    APPROACHING JUPITER                        17
    AT JUPITER                            17
        The probe at Jupiter                    17
        The orbiter at Jupiter                    18
    SCIENTIFIC ACTIVITIES                        19
        Spacecraft scientific activities            19
        Probe scientific activities                20
        Orbiter scientific activities                20
    GROUND SYSTEMS                            22
    JUPITER'S SYSTEM                        23
    WHY JUPITER INVESTIGATIONS ARE IMPORTANT            24
    GALILEO MANAGEMENT                        27
    STS-34 INERTIAL UPPER STAGE (IUS-19)                27
        Specifications                        27
        Airborne Support Equipment                28
        IUS Structure                        28
        Equipment Support Section                28
        IUS Avionics Subsystems                 28
        IUS Solid Rocket Motors                 29
        Reaction Control System                 29
        IUS to Spacecraft Interfaces                29
        Flight Sequence                     30
    SHUTTLE SOLAR BACKSCATTER ULTRAVIOLET INSTRUMENT (SSBUV)    31
    GROWTH HORMONE CONCENTRATIONS AND DISTRIBUTION IN PLANTS    32
    POLYMER MORPHOLOGY                        32
    STUDENT EXPERIMENT                        34
    MESOSCALE LIGHTNING EXPERIMENT                    35
    IMAX                                36
    AIR FORCE MAUI OPTICAL SITE CALIBRATION TEST            36
    SENSOR TECHNOLOGY EXPERIMENT                    37
    PAYLOAD AND VEHICLE WEIGHTS                    37
    SPACEFLIGHT TRACKING AND DATA NETWORK                37
    CREW BIOGRAPHIES                        38
    NASA PROGRAM MANAGEMENT                     41








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              SPACE SHUTTLE MISSION STS-34


--GENERAL RELEASE

RELEASE:  89-151


--SHUTTLE ATLANTIS TO DEPLOY GALILEO PROBE TOWARD JUPITER


    Space Shuttle mission STS-34 will deploy the Galileo planetary exploration
spacecraft into low-Earth orbit starting Galileo on its journey to explore
Jupiter.  Galileo will be the second planetary probe deployed from the Shuttle
this year following Atlantis' successful launch of Magellan toward Venus
exploration in May.

    Following deployment about 6 hours after launch, Galileo will be propelled
on a trajectory, known as Venus-Earth-Earth Gravity Assist (VEEGA) by an Air
Force-developed, inertial upper stage (IUS).  Galileo's trajectory will swing
around Venus, the sun and Earth before Galileo makes it's way toward Jupiter.

    Flying the VEEGA track, Galileo will arrive at Venus in February 1990.
During the flyby, Galileo will make measurements to determine the presence of
lightning on Venus and take time-lapse photography of Venus' cloud circulation
patterns.  Accelerated by Venus' gravity, the spacecraft will head back to
Earth.

    Enroute, Galileo will activate onboard remote-sensing equipment to gather
near-infrared data on the composition and characteristics of the far side of
Earth's moon.  Galileo also will map the hydrogen distribution of the Earth's
atmosphere.

    Acquiring additional energy from the Earth's gravitational forces, Galileo
will travel on a 2-year journey around the sun spending 10 months inside an
asteroid belt.    On Oct. 29, 1991, Galileo wlll pass within 600 miles of the
asteroid Gaspra.

    On the second Earth flyby in December 1992, Galileo will photograph the
north pole of the moon in an effort to determine if ice exists.  Outbound,
Galileo will activate the time-lapse photography system to produce a "movie" of
the moon orbiting Earth.

    Racing toward Jupiter, Galileo will make a second trek through the asteroid
belt passing within 600 miles of asteroid Ida on Aug. 29, 1993.  Science data
gathered from both asteroid encounters will focus on surface geology and
composition.

    Five months prior to the Dec. 7, 1995, arrival at Jupiter, Galileo's
atmospheric probe, encased in an oval heat shield, will spin away from the
orbiter at a rate of 5 revolutions per minute (rpm) and follow a ballistic
trajectory aimed at a spot 6 degrees north of Jupiter's equator.  The probe
will enter Jupiter's atmosphere at a shallow angle to avoid burning up like a
meteor or ricocheting off the atmosphere back into space.

    At approximately Mach 1 speed, the probe's pilot parachute will deploy,
removing the deceleration module aft cover.  Deployment of the main parachute
will follow, pulling the descent module out of the aeroshell to expose the
instrument-sensing elements.  During the 75-minute descent into the Jovian
atmosphere, the probe will use the orbiter to transmit data back to Earth.
After 75 minutes, the probe will be crushed under the heavy atmospheric


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              SPACE SHUTTLE MISSION STS-34


pressure.

    The Galileo orbiter will continue its primary mission, orbiting around
Jupiter and four of its satellites, returning science data for the next 22
months.

    Galileo's scientific goals include the study of the chemical composition,
state and dynamics of the Jovian atmosphere and satellites, and the
investigation of the structure and physical dynamics of the powerful Jovian
magnetosphere.

    Overall responsibility for management of the project, including orbiter
development, resides at NASA's Jet Propulsion Laboratory, Pasadena, Calif.  The
NASA Ames Research Center, Mountain View, Calif., manages the probe system.
JPL built the 2,500-lb. spacecraft and Hughes Aircraft Co. built the 740-lb.
probe.

    Modifications made to Galileo since flight postponement in 1986 include the
addition of sunshields to the base and top of the antenna, new thermal control
surfaces, blankets and heaters.  Because of the extended length of the mission,
the electrical circuitry of the thermoelectric generator has been revised to
reduce power demand throughout the mission to assure adequate power supply for
mission completion.

    Joining Galileo in the payload bay of Atlantis will be the Shuttle Solar
Backscatter Ultraviolet (SSBUV) instrument.  The SSBUV is designed to provide
calibration of backscatter ultraviolet instruments currently being flown on
free-flying satellites.  SSBUV's primary objective is to check the calibration
of the ozone sounders on satellites to verify the accuracy of the data set of
atmospheric ozone and solar irradiance data.

    The SSBUV is contained in two Get Away Special canisters in the payload bay
and weighs about 1219 lbs .  One canister contains the SSBUV spectrometer and
five supporting optical sensors.  The second canister houses data, command and
power systems.    An interconnecting cable provides the communication link
between the two canisters.

    Atlantis also will carry several secondary payloads involving radiation
measurements, polymer morphology, lightning research, microgravity effects on
plants and a student experiment on ice crystal growth in space.

    Commander of the 31st Shuttle mission is Donald E. Williams, Captain, USN.
Michael J. McCulley, Commander, USN, is Pilot.    Williams flew as Pilot of
mission STS 51-D in April 1985.  McCulley will be making his first Shuttle
flight.

    Mission Specialists are Shannon W. Lucid, Ph.D.; Franklin R. Chang-Diaz,
Ph.D.; and Ellen S. Baker, M.D.   Lucid previously flew as a Mission Specialist
on STS 51-G in June 1985.  Chang-Diaz flew as a Mission Specialist on STS 61-C
in January 1986.  Baker is making her first Shuttle flight.

    Liftoff of the fifth flight of orbiter Atlantis is scheduled for 1:29 p.m.
EDT on Oct. 12 from Kennedy Space Center, Fla., launch pad 39-B, into a
160-nautical-mile, 34.3-degree orbit.  Nominal mission duration is 5 days, 2
hours, 45 minutes.  Deorbit is planned on orbit 81, with landing scheduled for
4:14 p.m. EDT on Oct. 17 at Edwards Air Force Base, Calif.




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              SPACE SHUTTLE MISSION STS-34


    Liftoff on Oct. 12 could occur during a 10-minute period.  The launch
window grows each day reaching a maximum of 47 minutes on Nov. 2.  The window
then decreases each day through the remainder of the launch opportunity which
ends Nov. 21.  The window is dictated by the need for a daylight landing
opportunity at the trans-Atlantic landing abort sites and the performance
constraint of Galileo's inertial upper stage.

    After landing at Edwards AFB, Atlantis will be towed to the NASA
Ames-Dryden Flight Research Facility, hoisted atop the Shuttle Carrier Aircraft
and ferried back to the Kennedy Space Center to begin processing for its next
flight.





--GENERAL INFORMATION


--NASA Select Television Transmission

NASA Select television is available on Satcom F-2R, Transponder 13, C-band
located at 72 degrees west longitude, frequency 3960.0 MHz, vertical
polarization, audio monaural 6.8 MHz.

The schedule for tv transmissions from the orbiter and for the change-of-shift
briefings from Johnson Space Center, Houston, will be available during the
mission at Kennedy Space Center, Fla.; Marshall Space Flight Center,
Huntsville, Ala.; Johnson Space Center; and NASA Headquarters, Washington, D.C.
The  schedule will be updated daily to reflect changes dictated by mission
operations.

TV 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.  Voice
updates of the TV schedule may be obtained by dialing 202/755-1788.  This
service is updated daily at noon EDT.


--Special Note to Broadcasters

In the 5 workdays before launch, short sound bites of astronaut interviews with
the STS-34 crew will be available to broadcasters by calling 202/755-1788
between 8 a.m. and noon EDT.


--Status Reports

Status reports on countdown and mission progress, on-orbit activities and
landing operations will be produced by the appropriate NASA news center.


--Briefings

An STS-34 mission press briefing schedule will be issued prior to launch.
During the mission, flight control personnel will be on 8-hour shifts.
Change-of-shift briefings by the off-going flight director will occur at
approximately 8-hour intervals.



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              SPACE SHUTTLE MISSION STS-34


--LAUNCH PREPARATIONS, COUNTDOWN AND LIFTOFF


    Processing activities began on Atlantis for the STS-34 mission on May 16
when Atlantis was towed to Orbiter Processing Facility (OPF) bay 2 after
arrival from NASA's Ames-Dryden Flight Research Facility in California.  STS-30
post-flight deconfiguration and inspections were conducted in the processing
hangar.

    As planned, the three main engines were removed the last week of May and
taken to the main engine shop in the Vehicle Assembly Building (VAB) for the
replacement of several components including the high pressure oxidizer
turbopumps. The engines were reinstalled  the first week of July, while the
ship was in the OPF.  Engine 2027 is installed in the number one position,
engine 2030 is in the number two position and engine 2029 is in the number
three position.

    The right hand Orbital Maneuvering System (OMS) pod was removed in mid-June
for repairs.  A propellant tank needed for Atlantis' pod was scheduled for
delivery too late to support integrated testing.  As a result, Discovery's
right pod was installed on Atlantis about 2 weeks later.  The left OMS pod was
removed July 9 and reinstalled 2 1/2 weeks later.  Both pods had dynatubes and
helium isolation valve repairs in the Hypergolic Maintenance Facility.

     About 34 modifications have been implemented since the STS-30 mission.
One significant modification is a cooling system for the radioisotope
thermoelectric generators (RTG).  The RTG fuel is  plutonium dioxide which
generates heat as a result of its normal decay.  The heat is converted to
energy and used to provide electrical power for the Galileo spacecraft.  A
mixture of alcohol and water flows in the special cooling system to lower the
RTG case temperature and maintain a desired temperature to the payload
instrumentation in the vicinity of the RTGs.  These cooling lines are mounted
on the port side of the orbiter from the aft compartment to a control panel in
bay 4.

    Another modification, called "flutter buffet," features special
instrumentation on the vertical tail and right and left outboard elevons.  Ten
accelerometers were added to the vertical tail and one on each of the elevons.
These instruments are designed to measure in-flight loads on the orbiter's
structure.  Atlantis is the only vehicle that will be equipped with this
instrumentation.

    Improved controllers for the water spray boilers and auxiliary power units
were installed.  Other improvements were made to the orbiter's structure and
thermal protection system, mechanical systems, propulsion system and avionics
system.

    Stacking of solid rocket motor (SRM) segments for flight began with the
left aft booster on Mobile Launcher Platform 1 in the VAB on June 15.  Booster
stacking operations were completed by July 22 and the external tank was mated
to the two boosters on July 30.

    Flight crew members performed the Crew Equipment Interface Test on July 29
to become familiar with Atlantis' crew compartment, vehicle configuration and
equipment associated with the mission.

    The Galileo probe arrived at the Spacecraft Assembly and Encapsulation
Facility (SAEF) 2 on April 17 and the spacecraft arrived on May 16.  While at


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              SPACE SHUTTLE MISSION STS-34


SAEF-2, the spacecraft and probe were joined and tested together to verify
critical connections.  Galileo was delivered to the Vertical Processing
Facility (VPF) on Aug. 1.  The Inertial Upper Stage (IUS) was delivered to the
VPF on July 30.  The Galileo/IUS were joined together on Aug. 3 and all
integrated testing was performed during the second week of August.

    The Shuttle Solar Backscatter Ultraviolet (SSBUV) experiment, contained in
two Get Away Special (GAS) canisters, was mounted on a special GAS beam in
Atlantis' payload bay on July 24.  Interface verification tests were performed
the next day.

    Atlantis was transferred from the OPF to the VAB on Aug. 21, where it was
mated to the external tank and SRBs.  A Shuttle Interface Test was conducted in
the VAB to check the mechanical and electrical connections between the various
elements of the Shuttle vehicle and onboard flight systems.

    The assembled Space Shuttle vehicle was rolled out of the VAB aboard its
mobile launcher platform for the 4.2 mile trip to Launch Pad 39-B on Aug. 29.
Galileo and its IUS upper stage were transferred from the VPF to Launch Pad
39-B on Aug. 25.  The payload was installed in Atlantis' payload bay on Aug.
30.

    The payload interface verification test was planned for Sept. 7 to verify
connections between the Shuttle and the payload.  An end-to-end test was
planned for Sept. 8 to verify communications between the spacecraft and ground
controllers.  Testing of the IUS was planned about 2 weeks prior to launch in
parallel with Shuttle launch preparations.

    A Countdown Demonstration Test, a dress rehearsal for the STS-34 flight
crew and KSC launch team, is designed as a practice countdown for the launch.
At press time, it was planned for Sept. 14 and 15.

    One of the unique STS-34 processing milestones planned was a simulation
exercise for the installation of the RTGs.  Simulated RTGs were to be used in
the 2-day event scheduled within the first week after Atlantis arrives at the
launch pad.  The test is designed to give workers experience for the
installation of the RTGs, a first in the Shuttle program.  In addition, access
requirements will be identified and procedures will be verified.

    Another test scheduled at the pad is installation of the flight RTGs and an
associated test and checkout of the RTG cooling system planned for the third
week of September.  This test will verify the total RTG cooling system and
connections.  The RTGs will be removed at the completion of the 3-day cooling
system test and returned to the RTG facility.  The two flight RTGs will be
reinstalled on the spacecraft 6 days before launch.

    Launch preparations scheduled the last 2 weeks prior to launch countdown
include final vehicle ordnance activities, such as power-on stray-voltage
checks and resistance checks of firing circuits; loading the fuel cell storage
tanks; pressurizing the hypergolic propellant tanks aboard the vehicle; final
payload closeouts; and a final functional check of the range safety and SRB
ignition, safe and arm devices.

    The launch countdown is scheduled to pick up at the T-minus 43-hour mark,
leading up to the STS-34 launch.  Atlantis' fifth launch will be conducted by a
joint NASA/industry team from Firing Room 1 in the Launch Control Center.




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              SPACE SHUTTLE MISSION STS-34


--MAJOR COUNTDOWN MILESTONES


Countdown        Event
---------        -----
T-43 Hours        Power up Space Shuttle vehicle.
T-34 Hours        Begin orbiter and ground support equipment closeouts
            for launch.
T-30 Hours        Activate orbiter's navigation aids.
T-27 Hours (holding)    Enter first built-in hold for 8 hours.
T-27 Hours (counting)    Begin preparations for loading fuel cell storage tanks
            with liquid oxygen and liquid hydrogen reactants.
T-25 Hours        Load orbiter's fuel cell tanks with liquid oxygen.
T-22 Hours, 30 minutes    Load orbiter's fuel cell tanks with liquid hydrogen.
T-22 Hours        Perform interface check between Houston Mission
            Control and Merritt Island Launch Area (MILA) tracking
            station.
T-20 Hours        Activate and warm up inertial measurement units (IMU).
T-19 Hours (holding)    Enter 8-hour built-in hold. Activate orbiter
            communications system.
T-19 hours (counting)    Resume countdown.  Continue preparations to load
            external tank, orbiter closeouts and preparations to
            move the Rotating Service Structure (RSS).
T-11 Hours (holding)    Start 14-hour, 40 minute built-in hold orbiter flight
            and middecks.
T-11 Hours (counting)    Retract RSS from vehicle to launch position.
T-9 Hours        Activate orbiter's fuel cells.
T-8 Hours        Configure Mission Control communications for launch.
            Start clearing blast danger area.
T-6 Hours, 30 minutes    Perform Eastern Test Range open loop command test.
T-6 Hours (holding)    Enter 1-hour built-in hold.  Receive management "go"
            for tanking.
T-6 Hours (counting)    Start external tank chilldown and propellant loading.
T-5 Hours        Start IMU pre-flight calibration.
T-4 Hours        Perform MILA antenna alignment.
T-3 Hours (holding)    2-hour built-in hold begins.  Loading of external tank
            is complete and in a stable replenish mode.  Ice team
            goes to pad for inspections.  Closeout crew goes to
            white room to begin preparing orbiter's cabin for
            flight crew's entry.  Wake flight crew (launch minus
            4 hours, 55 minutes).
T-3 Hours (counting)    Resume countdown.
T-2 Hours, 55 minutes    Flight crew departs O&C Building for Launch Pad 39-B
            (Launch minus 3 hours, 15 minutes).
T-2 Hours, 30 minutes    Crew enters orbiter vehicle (Launch minus 2 Hours,
            50 minutes).
T-60 minutes        Start pre-flight alignment of IMUs.
T-20 minutes (holding)    10-minute built-in hold begins.
T-20 minutes(counting)    Configure orbiter computers for launch.
T-10 minutes        White room closeout crew cleared through launch danger
            are roadblocks.
T-9 minutes (holding)    40-minute built-in hold begins.  Perform status check
            and receive Launch Director and Mission Management
            Team "go."
T-9 minutes (counting)    Start ground launch sequencer.
T-7 minutes, 30 sec.    Retract orbiter access arm.
T-5 minutes        Pilot starts auxiliary power units.  Arm range safety,
            solid rocket booster (SRB) ignition systems.


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              SPACE SHUTTLE MISSION STS-34


T-3 minutes, 30 sec.    Orbiter goes on internal power.
T-2 minutes, 55 sec.    Pressurize liquid oxygen tank for flight and retract
            gaseous oxygen vent hood.
T-1 minute, 57 sec.    Pressurize liquid hydrogen tank.
T-31 seconds        "Go" from ground computer for orbiter computers to
            start the automatic launch sequence.
T-28 seconds        Start SRB hydraulic power units.
T-21 seconds        Start SRB gimbal profile test.
T-6.6 seconds        Main engine start.
T-3 seconds        Main engines at 90 percent thrust.
T-0            SRB ignition, holddown post release and liftoff.
T+7 seconds        Shuttle clears launch tower an control switches to
            JSC.


Note: This countdown timeline may be adjusted in real time as necessary.












































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              SPACE SHUTTLE MISSION STS-34


--TRAJECTORY SEQUENCE OF EVENTS

                                  RELATIVE
EVENT                   MET          VELOCITY      MACH      ALTITUDE
                (d:h:m:s)      (fps)            (ft.)
--------------------------------------------------------------------------
Launch                00/00:00:00
Begin Roll Maneuver        00/00:00:09      165      .15        627
End Roll Maneuver        00/00:00:17      374      .33      2,898
SSME Throttle Down to 65%    00/00:00:34      833      .75     11,854
Max. Dyn. Pressure (Max Q)    00/00:00:52    1,260     1.20     28,037
SSME Throttle Up to 104%    00/00:01:01    1,499     1.49     38,681
SRB Staging            00/00:02:04    4,316     3.91    153,873
Negative Return         00/00:03:54    6,975     7.48    317,096
Main Engine Cutoff (MECO)    00/00:08:27    24,580    22.41    366,474
Zero Thrust            00/00:08:33    24,596    22.17    368,460
ET Separation            00/00:08:45
OMS 2 Burn            00/00:39:48
Galileo/IUS Deploy (orbit  5)    00/06:21:36
Deorbit Burn (orbit 81)     05/01:45:00
Landing (orbit 82)        05/02:45:00

Apogee, Perigee at MECO:    157 x  39 nm
Apogee, Perigee post-OMS 2:    161 x 161 nm
Apogee, Perigee post deploy:    177 x 161 nm





--SPACE SHUTTLE ABORT MODES


Space Shuttle launch abort philosophy aims toward safe and intact recovery of
the flight crew, orbiter and its payload.  Abort modes include:

* Abort-To-Orbit (ATO) -- Partial loss of main engine thrust late enough to
  permit reaching a minimal 105-nautical mile orbit with orbital maneuvering
  system engines.

* Abort-Once-Around (AOA) -- Earlier main engine shutdown with the capability
  to allow one orbit around before landing at Edwards Air Force Base, Calif.;
  White Sands Space Harbor (Northrup Strip), N.M.; or the Shuttle Landing
  Facility (SLF) at Kennedy Space Center (KSC), Fla.

* Trans-Atlantic Abort Landing (TAL) -- Loss of two main engines midway
  through powered flight would force a landing at Ben Guerir, Morocco; Moron,
  Spain; or Banjul, The Gambia.

* Return-To-Launch-Site (RTLS) -- Early shutdown of one or more engines and
  without enough energy to reach Ben Guerir, would result in a pitch around
  and thrust back toward KSC until within gliding distance of the SLF.

STS-34 contingency landing sites are Edwards AFB, White Sands, KSC, Ben Guerir,
Moron and Banjul.





                  - Page 11 -


              SPACE SHUTTLE MISSION STS-34


--SUMMARY OF MAJOR ACTIVITIES


Day One

1. Ascent
2. Post-insertion checkout
3. Pre-deploy checkout
4. Galileo/Inertial Upper Stage (IUS) deploy
5. Detailed Secondary Objective (DSO)
6. Polymer Morphology (PM)
7. Sensor Technology Experiment (STEX) activation


Day Two

1. Galileo/IUS backup deploy opportunity
2. DSO
3. IMAX
4. PM
5. Shuttle Solar Backscatter Ultraviolet (SSBUV) activation
6. Shuttle Student Involvement Program (SSIP)


Day Three

1. DSO
2. IMAX
3. Mesoscale Lightning Experiment (MLE)
4. PM


Day Four

1. DSO
2. IMAX
3. MLE
4. PM
5. SSBUV deactivation


Day Five

1. DTO/DSO
2. GHCD operations
3. PM
4. STEX deactivation
5. Flight control systems (FCS) checkout
6. Cabin stow
7. Landing preparations


Day Six

1. PM stow
2. Deorbit preparation
3. Deorbit burn
4. Landing at Edwards AFB


                  - Page 12 -


              SPACE SHUTTLE MISSION STS-34


--LANDING AND POST LANDING OPERATIONS


    Kennedy Space Center, Fla., is responsible for ground  operations of the
orbiter once it has rolled to a stop on the runway at Edwards Air Force Base,
Calif.    Those operations include preparing the Shuttle for the return trip to
Kennedy.

    After landing, the flight crew aboard Atlantis begins "safing" vehicle
systems.  Immediately after wheel stop, specially garbed technicians will first
determine that any residual hazardous vapors are below significant levels for
other safing operations to proceed.

    A mobile white room is moved into place around the crew hatch once it is
verified that there are no concentrations of toxic gases around the forward
part of the vehicle.  The flight crew is expected to leave Atlantis about 45 to
50 minutes after landing.  As the crew exits, technicians enter the orbiter to
complete the vehicle safing activity.

    Once the initial aft safety assessment is made, access vehicles are
positioned  around the rear of the orbiter so that lines from the ground purge
and cooling vehicles can be connected to the umbilical panels on the aft end of
Atlantis.

    Freon line connections are completed and coolant begins circulating through
the umbilicials to aid in heat rejection and protect the orbiter's electronic
equipment.  Other lines provide cooled, humidified air to the payload bay and
other cavities to remove any residual fumes and provide a safe environment
inside Atlantis.

    A tow tractor will be connected to Atlantis and the vehicle will be pulled
off the runway at Edwards and positioned inside the Mate/Demate Device (MDD) at
nearby Ames-Dryden Flight Research Facility.  After the Shuttle has been jacked
and leveled, residual fuel cell cryogenics are drained and unused pyrotechnic
devices are disconnected prior to returning the orbiter to Kennedy.

    The aerodynamic tail cone is installed over the three main engines, and the
orbiter is bolted on top of the 747 Shuttle Carrier Aircraft for the ferry
flight back to Florida.  Pending completion of planned work and favorable
weather conditions, the 747 would depart California about 6 days after landing
for the cross-country ferry flight back to Florida.  A refueling stop is
necessary to complete the journey.

    Once back at Kennedy, Atlantis will be pulled inside the hangar-like
facility for post-flight inspections and in-flight anomaly troubleshooting.
These operations are conducted in parallel with the start of routine systems
reverification to prepare Atlantis for its next mission.













                  - Page 13 -


              SPACE SHUTTLE MISSION STS-34


--GALILEO


    Galileo is a NASA spacecraft mission to Jupiter to study the planet's
atmosphere, satellites and surrounding magnetosphere.  It was named for the
Italian renaissance scientist who discovered Jupiter's major moons by using the
first astronomical telescope.

    This mission will be the first to make direct measurements from an
instrumented probe within Jupiter's atmosphere and the first to conduct
long-term observations of the planet and its magnetosphere and satellites from
orbit around Jupiter.  It will be the first orbiter and atmospheric probe for
any of the outer planets.  On the way to Jupiter, Galileo also will observe
Venus, the Earth-moon system, one or two asteroids and various phenomena in
interplanetary space.

    Galileo will be boosted into low-Earth orbit by the Shuttle Atlantis and
then boosted out of Earth orbit by a solid rocket Inertial Upper Stage.  The
spacecraft will fly past Venus and twice by the Earth, using gravity assists
from the planets to pick up enough speed to reach Jupiter.  Travel time from
launch to Jupiter is a little more than 6 years.

    In December 1995, the Galileo atmospheric probe will conduct a brief,
direct examination of Jupiter's atmosphere, while the larger part of the craft,
the orbiter, begins a 22-month, 10-orbit tour of major satellites and the
magnetosphere, including long-term observations of Jupiter throughout this
phase.

    The 2-ton Galileo orbiter spacecraft carries 9 scientific instruments.
There are another six experiments on the 750-pound probe.  The spacecraft radio
link to Earth serves as an additional instrument for  scientific measurements.
The probe's scientific data will be relayed to Earth by the orbiter during the
75-minute period while the probe is descending into Jupiter's atmosphere.
Galileo will communicate with its controllers and scientists through NASAUs
Deep Space Network, using tracking stations in California, Spain and
Australia.



--GALILEO MISSION EVENTS

Launch Window (Atlantis and IUS)     Oct. 12 to Nov. 21, 1989
(Note:    for both asteroids, closes in mid-October)
Venus flyby ( 9,300 mi)         *Feb. 9, 1990
Venus data playback             Oct. 1990
Earth 1 flyby ( about 600 mi)        *Dec. 8, 1990
Asteroid Gaspra flyby (600 mi)        *Oct. 29, 1991
Earth 2 flyby (200 mi)            *Dec. 8, 1992
Asteroid Ida flyby (600 mi)        *Aug. 28, 1993
Probe release                 July 1995
Jupiter arrival              Dec. 7, 1995
(includes Io flyby, probe entry and relay, Jupiter orbit insertion)
Orbital tour of Galilean satellites  Dec '95-Oct '97

*Exact dates may vary according to actual launch date





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              SPACE SHUTTLE MISSION STS-34


--EARTH TO JUPITER


    Galileo will make three planetary encounters in the course of its
gravity-assisted flight to Jupiter.  These provide opportunities for scientific
observation and measurement of Venus and the Earth-moon system.  The mission
also has a chance to fly close to one or two asteroids, bodies which have never
been observed close up, and obtain data on other phenomena of interplanetary
space.

    Scientists are currently studying how to use the Galileo scientific
instruments and the limited ability to collect, store and transmit data during
the early phase of flight to make the best use of these opportunities.
Instruments designed to observe Jupiter's atmosphere from afar can improve our
knowledge of the atmosphere of Venus and sensors designed for the study of
Jupiter's moons can add to our information about our own moon.



--VENUS

    The Galileo spacecraft will approach Venus early in 1990 from the night
side and pass across the sunlit hemisphere, allowing observation of the clouds
and atmosphere.  Both infrared and ultraviolet spectral observations are
planned, as well as several camera images and other remote measurements.  The
search for deep cloud patterns and for lightning storms will be limited by the
fact that all the Venus data must be tape-recorded on the spacecraft for
playback 8 months later.

    The spacecraft was originally designed to operate between Earth and
Jupiter, where sunlight is 25 times weaker than at Earth and temperatures are
much lower.  The VEEGA mission will expose the spacecraft to a hotter
environment from Earth to Venus and back.  Spacecraft engineers devised a set
of sunshades to protect the craft.  For this system to work, the front end of
the spacecraft must be aimed precisely at the Sun, with the main antenna furled
for protection from the Sun's rays until after the first Earth flyby in
December 1990.    This precludes the use of the Galileo high-gain antenna and
therefore, scientists must wait until the spacecraft is close to Earth to
receive the recorded Venus data, transmitted through a low-gain antenna.



--FIRST EARTH PASS

    Approaching Earth for the first time about 14 months after launch, the
Galileo spacecraft will observe, from a distance, the nightside of Earth and
parts of both the sunlit and unlit sides of the moon.  After passing Earth,
Galileo will observe Earth's sunlit side.  At this short range, scientific data
are transmitted at the high rate using only the spacecraft's low-gain antennas.
The high-gain antenna is to be unfurled like an umbrella, and its high-power
transmitter turned on and checked out, about 5 months after the first Earth
encounter.








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              SPACE SHUTTLE MISSION STS-34


--FIRST ASTEROID

    Nine months after the Earth passage and still in an elliptical solar orbit,
Galileo will enter the asteroid belt, and two months later, will have its first
asteroid encounter.  Gaspra is believed to be a fairly representative main-belt
asteroid, about 10 miles across and probably similar in composition to stony
meteorites.

    The spacecraft will pass within about 600 miles at a relative speed of
about 18,000 miles per hour.  It will collect several pictures of Gaspra and
make spectral measurements to indicate its composition and physical
properties.



--SECOND EARTH PASS

    Thirteen months after the Gaspra encounter, the spacecraft will have
completed its 2-year elliptical orbit around the Sun and will arrive back at
Earth.    It will need a much larger ellipse (with a 6-year period) to reach as
far as Jupiter.  The second flyby of Earth will pump the orbit up to that size,
acting as a natural apogee kick motor for the Galileo spacecraft.

    Passing about 185 miles above the surface, near the altitude at which it
had been deployed from the Space Shuttle almost three years earlier, Galileo
will use Earth's gravitation to change the spacecraft's flight direction and
pick up about 8,000 miles per hour in speed.

    Each gravity-assist flyby requires about three rocket-thrusting sessions,
using Galileo's onboard retropropulsion module, to fine-tune the flight path.
The asteroid encounters require similar maneuvers to obtain the best observing
conditions.

    Passing the Earth for the last time, the spacecraft's scientific equipment
will make thorough observations of the planet, both for comparison with Venus
and Jupiter and to aid in Earth studies.  If all goes well, there is a good
chance that Galileo will enable scientists to record the motion of the moon
about the Earth while the Earth itself rotates.



--SECOND ASTEROID

    Nine months after the final Earth flyby, Galileo may have a second
asteroid-observing opportunity.  Ida is about 20 miles across.    Like Gaspra,
Ida is believed to represent the majority of main-belt asteroids in
composition, though there are believed to be differences between the two.
Relative velocity for this flyby will be nearly 28,000 miles per hour, with a
planned closest approach of about 600 miles.











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              SPACE SHUTTLE MISSION STS-34


--APPROACHING JUPITER

    Some 2 years after leaving Earth for the third time and 5 months before
reaching Jupiter, Galileo's probe must separate from the orbiter.  The
spacecraft turns to aim the probe precisely for its entry point in the Jupiter
atmosphere, spins up to 10 revolutions per minute and releases the
spin-stabilized probe.    Then the Galileo orbiter maneuvers again to aim for its
own Jupiter encounter and resumes its scientific measurements of the
interplanetary environment underway since the launch more than 5 years before.

    While the probe is still approaching Jupiter, the orbiter will have its
first two satellite encounters.  After passing within 20,000 miles of Europa,
it will fly about 600 miles above Io's volcano-torn surface, twenty times
closer than the closest flyby altitude of Voyager in 1979.



--AT JUPITER

--The Probe at Jupiter


    The probe mission has four phases:    launch, cruise, coast and
entry-descent.    During launch and cruise, the probe will be carried by the
orbiter and serviced by a common umbilical.  The probe will be dormant during
cruise except for annual checkouts of spacecraft systems and instruments.
During this period, the orbiter will provide the probe with electric power,
commands, data transmission and some thermal control.

    Six hours before entering the atmosphere, the probe will be shooting
through space at about 40,000 mph.  At this time, its command unit signals
"wake up" and instruments begin collecting data on lightning, radio emissions
and energetic particles.

    A few hours later, the probe will slam into Jupiter's atmosphere at 115,000
mph, fast enough to jet from Los Angeles to New York in 90 seconds.
Deceleration to about Mach 1 -- the speed of sound -- should take just a few
minutes.  At maximum deceleration as the craft slows from 115,000 mph to 100
mph, it will be hurtling against a force 350 times Earth's gravity.  The
incandescent shock wave ahead of the probe will be as bright as the sun and
reach searing temperatures of up to 28,000 degrees Fahrenheit.    After the
aerodynamic braking has slowed the probe, it will drop its heat shields and
deploy its parachute.  This will allow the probe to float down about 125 miles
through the clouds, passing from a pressure of 1/10th that on Earth's surface
to about 25 Earth atmospheres.

    About 4 minutes after probe entry into Jupiter's atmosphere, a pilot chute
deploys and explosive nuts shoot off the top section of the probe's protective
shell.    As the cover whips away, it pulls out and opens the main parachute
attached to the inner capsule.    What remains of the probe's outer shell, with
its massive heat shield, falls away as the parachute slows the instrument
module.

    From there on, suspended from the main parachute, the probe's capsule with
its activated instruments floats downward toward the bright clouds below.

    The probe will pass through the white cirrus clouds of ammonia crystals -
the highest cloud deck.  Beneath this ammonia layer probably lie reddish-brown


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              SPACE SHUTTLE MISSION STS-34


clouds of ammonium hydrosulfides.  Once past this layer, the probe is expected
to reach thick water clouds.  This lowest cloud layer may act as a buffer
between the uniformly mixed regions below and the turbulent swirl of gases
above.

    Jupiter's atmosphere is primarily hydrogen and helium.  For most of its
descent through Jupiter's three main cloud layers, the probe will be immersed
in gases at or below room temperature.    However, it may encounter hurricane
winds up to 200 mph and lightning and heavy rain at the base of the water
clouds believed to exist on the planet.  Eventually, the probe will sink below
these clouds, where rising pressure and temperature will destroy it.  The
probe's active life in Jupiter's atmosphere is expected to be about 75 minutes
in length.  The probe batteries are not expected to last beyond this point, and
the relaying orbiter will move out of reach.

    To understand this huge gas planet, scientists must find out about its
chemical components and the dynamics of its atmosphere.  So far, scientific
data are limited to a two-dimensional view (pictures of the planet's cloud
tops) of a three-dimensional process (Jupiter's weather).  But to explore such
phenomena as the planet's incredible coloring, the Great Red Spot and the
swirling shapes and high-speed motion of its topmost clouds, scientists must
penetrate Jupiter's visible surface and investigate the atmosphere concealed in
the deep-lying layers below.

    A set of six scientific instruments on the probe will measure, among other
things, the radiation field near Jupiter, the temperature, pressure, density
and composition of the planet's atmosphere from its first faint outer traces to
the hot, murky hydrogen atmosphere 100 miles below the cloud tops.  All of the
information will be gathered during the probe's descent on an 8-foot parachute.
Probe data will be sent to the Galileo Orbiter 133,000 miles overhead then
relayed across the half billion miles to Deep Space Network stations on Earth.

    To return its science, the probe relay radio aboard the orbiter must
automatically acquire the probe signal below within 50 seconds, with a success
probability of 99.5 percent.  It must reacquire the signal immediately should
it become lost.

    To survive the heat and pressure of entry, the probe spacecraft is composed
of two separate units:    an inner capsule containing the scientific instruments,
encased in a virtually impenetrable outer shell.  The probe weighs 750 pounds.
The outer shell is almost all heat shield material.



--The Orbiter at Jupiter


     After releasing the probe, the orbiter will use its main engine to go into
orbit around Jupiter.  This orbit, the first of 10 planned, will have a period
of about 8 months.  A close flyby of Ganymede in July 1996 will shorten the
orbit, and each time the Galileo orbiter returns to the inner zone of
satellites, it will make a gravity-assist close pass over one or another of the
satellites, changing Galileo's orbit while making close observations.  These
satellite encounters will be at altitudes as close as 125 miles above their
surfaces.  Throughout the 22-month orbital phase, Galileo will continue
observing the planet and the satellites and continue gathering data on the
magnetospheric environment.



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              SPACE SHUTTLE MISSION STS-34


--SCIENTIFIC ACTIVITIES


    Galileo's scientific experiments will be carried out by more than 100
scientists from six nations.  Except for the radio science investigation, these
are supported by dedicated instruments on the Galileo orbiter and probe.  NASA
has appointed 15 interdisciplinary scientists whose studies include data from
more than one Galileo instrument.

    The instruments aboard the probe will measure the temperatures and pressure
of Jupiter's atmosphere at varying altitudes and determine its chemical
composition including major and minor constituents (such as hydrogen, helium,
ammonia, methane, and water) and the ratio of hydrogen to helium.  Jupiter is
thought to have a bulk composition similar to that of the primitive solar
nebula from which it was formed.  Precise determination of the ratio of
hydrogen to helium would provide an important factual check of the Big Bang
theory of the genesis of the universe.

    Other probe experiments will determine the location and structure of
Jupiter's clouds, the existence and nature of its lightning, and the amount of
heat radiating from the planet compared to the heat absorbed from sunlight.

    In addition, measurements will be made of Jupiter's numerous radio
emissions and of the high-energy particles trapped in the planet's innermost
magnetic field.  These measurements for Galileo will be made within a distance
of 26,000 miles from Jupiter's cloud tops, far closer than the previous closest
approach to Jupiter by Pioneer 11.  The probe also will determine vertical wind
shears using Doppler radio measurements made of probe motions from the radio
receiver aboard the orbiter.

    Jupiter appears to radiate about twice as much energy as it receives from
the sun and the resulting convection currents from Jupiter's internal heat
source towards its cooler polar regions could explain some of the planet's
unusual weather patterns.

    Jupiter is over 11 times the diameter of Earth and spins about two and
one-half times faster -- a jovian day is only 10 hours long.  A point on the
equator of Jupiter's visible surface races along at 28,000 mph.  This rapid
spin may account for many of the bizarre circulation patterns observed on the
planet.



--Spacecraft Scientific Activities


    The Galileo mission and systems were designed to investigate three broad
aspects of the Jupiter system: the planet's atmosphere, the satellites and the
magnetosphere.    The spacecraft is in three segments to focus on these areas:
the atmospheric probe; a non-spinning section of the orbiter carrying cameras
and other remote sensors; and the spinning main section of the orbiter
spacecraft which includes the propulsion module, the communications antennas,
main computers and most support systems as well as the fields and particles
instruments, which sense and measure the environment directly as the spacecraft
flies through it.





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              SPACE SHUTTLE MISSION STS-34


--Probe Scientific Activities


    The probe will enter the atmosphere about 6 degrees north of the equator.
The probe weighs just under 750 pounds and includes a deceleration module to
slow and protect the descent module, which carries out the scientific mission.

    The deceleration module consists of an aeroshell and an aft cover designed
to block the heat generated by slowing from the probe's arrival speed of about
115,000 miles per hour to subsonic speed in less than 2 minutes.  After the
covers are released, the descent module deploys its 8-foot  parachute and its
instruments, the control and data system, and the radio-relay transmitter go to
work.

    Operating at 128 bits per second, the dual L-band transmitters send nearly
identical streams of scientific data to the orbiter.  The probe's relay radio
aboard the orbiter will have two redundant receivers that process probe science
data, plus radio science and engineering data for transmission to the orbiter
communications system.    Minimum received signal strength is 31 dBm.  The
receivers also measure signal strength and Doppler shift as part of the
experiments for measuring wind speeds and atmospheric absorption of radio
signals.

    Probe electronics are powered by long-life, high-discharge-rate 34-volt
lithium batteries, which remain dormant for more than 5 years during the
journey to Jupiter.  The batteries have an estimated capacity of about 18
amp-hours on arrival at Jupiter.



--Orbiter Scientific Activities


    The orbiter, in addition to delivering the probe to Jupiter and relaying
probe data to Earth, will support all the scientific investigations of Venus,
the Earth and moon, asteroids and the interplanetary medium, Jupiter's
satellites and magnetosphere, and observation of the giant planet itself.

    The orbiter weighs about 5,200 pounds including about 2,400 pounds of
rocket propellant to be expended in some 30 relatively small maneuvers during
the long gravity-assisted flight to Jupiter, the large thrust maneuver which
puts the craft into its Jupiter orbit, and the 30 or so trim maneuvers planned
for the satellite tour phase.

    The retropropulsion module consists of 12 10-newton thrusters, a single
400-newton engine, and the fuel, oxidizer, and pressurizing-gas tanks, tubing,
valves and control equipment.  (A thrust of 10 newtons would support a weight
of about 2.2 pounds at Earth's surface).  The propulsion system was developed
and built by Messerschmitt-Bolkow-Blohm and provided by the Federal Republic of
Germany.

    The orbiter's maximum communications rate is 134 kilobits per second (the
equivalent of about one black-and-white image per minute); there are other data
rates, down to 10 bits per second, for transmitting engineering data under poor
conditions.  The spacecraft transmitters operate at S-band and X-band (2295 and
8415 megahertz) frequencies between Earth and on L-band between the probe.




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              SPACE SHUTTLE MISSION STS-34


    The high-gain antenna is a 16-foot umbrella-like reflector unfurled after
the first Earth flyby.    Two low-gain antennas (one pointed forward and one aft,
both mounted on the spinning section) are provided to support communications
during the Earth-Venus-Earth leg of the flight and whenever the main antenna is
not deployed and pointed at Earth.  The despun section of the orbiter carries a
radio relay antenna for receiving the probe's data transmissions.

    Electrical power is provided to Galileo's equipment by two radioisotope
thermoelectric generators.  Heat produced by natural radioactive decay of
plutonium 238 dioxide is converted to approximately 500 watts of electricity
(570 watts at launch, 480 at the end of the mission) to operate the orbiter
equipment for its 8-year active period.  This is the same type of power source
used by the Voyager and Pioneer Jupiter spacecraft in their long outer-planet
missions, by the Viking lander spacecraft on Mars and the lunar scientific
packages left on the Moon.

    Most spacecraft are stabilized in flight either by spinning around a major
axis or by maintaining a fixed orientation in space, referenced to the sun and
another star.  Galileo represents a hybrid of these techniques, with a spinning
section rotating ordinarily at 3 rpm and a "despun" section which is
counter-rotated to provide a fixed orientation for cameras and other remote
sensors.

    Instruments that measure fields and particles, together with the main
antenna, the power supply, the propulsion module, most of the computers and
control electronics, are mounted on the spinning section.  The instruments
include magnetometer sensors mounted on a 36-foot boom to escape interference
from the spacecraft; a plasma instrument detecting low-energy charged particles
and a plasma-wave detector to study waves generated in planetary magnetospheres
and by lightning discharges; a high-energy particle detector; and a detector of
cosmic and Jovian dust.

    The despun section carries instruments and other equipment whose operation
depends on a fixed orientation in space.  The instruments include the camera
system; the near-infrared mapping spectrometer to make multispectral images for
atmosphere and surface chemical analysis; the ultraviolet spectrometer to study
gases and ionized gases; and the photopolarimeter radiometer to measure radiant
and reflected energy.  The camera system is expected to obtain images of
Jupiter's satellites at resolutions from 20 to 1,000 times better than
Voyager's best.

    This section also carries a dish antenna to track the probe in Jupiter's
atmosphere and pick up its signals for relay to Earth.    The probe is carried on
the despun section, and before it is released, the whole spacecraft is spun up
briefly to 10 rpm in order to spin-stabilize the probe.

    The Galileo spacecraft will carry out its complex operations, including
maneuvers, scientific observations and communications, in response to stored
sequences which are interpreted and executed by various on-board computers.
These sequences are sent up to the orbiter periodically through the Deep Space
Network in the form of command loads.









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              SPACE SHUTTLE MISSION STS-34


--GROUND SYSTEMS


    Galileo communicates with Earth via NASA's Deep Space Network (DSN), which
has a complex of large antennas with receivers and transmitters located in the
California desert, another in Australia and a third in Spain, linked to a
network control center at NASAUs Jet Propulsion Laboratory in Pasadena, Calif.
The spacecraft receives commands, sends science and engineering data, and is
tracked by Doppler and ranging measurements through this network.

    At JPL, about 275 scientists, engineers and technicians, will be supporting
the mission at launch, increasing to nearly 400 for Jupiter operations
including support from the German retropropulsion team at their control center
in the FGR.  Their responsibilities include spacecraft command, interpreting
engineering and scientific data from Galileo to understand its performance, and
analyzing navigation data from the DSN.  The controllers use a set of complex
computer programs to help them control the spacecraft and interpret the data.

    Because the time delay in radio signals from Earth to Jupiter and back is
more than an hour, the Galileo spacecraft was designed to operate from programs
sent to it in advance and stored in spacecraft memory.    A single master
sequence program can cover 4 weeks of quiet operations between planetary and
satellite encounters.  During busy Jupiter operations, one program covers only
a few days.  Actual spacecraft tasks are carried out by several subsystems and
scientific instruments, many of which work from their own computers controlled
by the main sequence.

    Designing these sequences is a complex process balancing the desire to make
certain scientific observations with the need to safeguard the spacecraft and
mission.  The sequence design process itself is supported by software programs,
for example, which display to the scientist maps of the instrument coverage on
the surface of an approaching satellite for a given spacecraft orientation and
trajectory.  Notwithstanding these aids, a typical 3-day satellite encounter
may take efforts spread over many months to design, check and recheck.    The
controllers also use software designed to check the command sequence further
against flight rules and constraints.

    The spacecraft regularly reports its status and health through an extensive
set of engineering measurements.  Interpreting these data into trends and
averting or working around equipment failures is a major task for the mission
operations team.  Conclusions from this activity become an important input,
along with scientific plans, to the sequence design process.  This too is
supported by computer programs written and used in the mission support area.

    Navigation is the process of estimating, from radio range and Doppler
measurements, the position and velocity of the spacecraft to predict its flight
path and design course-correcting maneuvers.  These calculations must be done
with computer support.    The Galileo mission, with its complex gravity-assist
flight to Jupiter and 10 gravity-assist satellite encounters in the Jovian
system, is extremely dependent on consistently accurate navigation.

    In addition to the programs that directly operate the spacecraft and are
periodically transmitted to it, the mission operations team uses software
amounting to 650,000 lines of programming code in the sequence design process;
1,615,000 lines in the telemetry interpretation; and 550,000 lines of code in
navigation.  These must all be written, checked, tested, used in mission
simulations and, in many cases, revised before the mission can begin.



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              SPACE SHUTTLE MISSION STS-34


    Science investigators are located at JPL or other university laboratories
and linked by computers.  From any of these locations, the scientists can be
involved in developing the sequences affecting their experiments and, in some
cases, in helping to change preplanned sequences to follow up on unexpected
discoveries with second looks and confirming observations.





--JUPITER'S SYSTEM


    Jupiter is the largest and fastest-spinning planet in the solar system.
Its radius is more than 11 times Earth's, and its mass is 318 times that of our
planet.  Named for the chief of the Roman gods, Jupiter contains more mass than
all the other planets combined.  It is made mostly of light elements,
principally hydrogen and helium.  Its atmosphere and clouds are deep and dense,
and a significant amount of energy is emitted from its interior.

    The earliest Earth-based telescopic observations showed bands and spots in
Jupiter's atmosphere.  One storm system, the Red Spot, has been seen to persist
over three centuries.

    Atmospheric forms and dynamics were observed in increasing detail with the
Pioneer and Voyager flyby spacecraft, and Earth-based infrared astronomers have
recently studied the nature and vertical dynamics of deeper clouds.

    Sixteen satellites are known.  The four largest, discovered by the Italian
scientist Galileo Galilei in 1610, are the size of small planets.  The
innermost of these, Io, has active sulfurous volcanoes, discovered by Voyager 1
and further observed by Voyager 2 and Earth-based infrared astronomy.  Io and
Europa are about the size and density of Earth's moon (3 to 4 times the density
of water) and probably rocky inside.  Ganymede and Callisto, further out from
Jupiter, are the size of Mercury but less than twice as dense as water.  Their
cratered surfaces look icy in Voyager images, and they may be composed partly
of ice or water.

    Of the other satellites, eight (probably captured asteroids) orbit
irregularly far from the planet, and four (three discovered by the Voyager
mission in 1979) are close to the planet.  Voyager also discovered a thin ring
system at Jupiter in 1979.

    Jupiter has the strongest planetary magnetic field known.  The resulting
magnetosphere is a huge teardrop-shaped, plasma-filled cavity in the solar wind
pointing away from the sun.  JupiterUs magnetosphere is the largest single
entity in our solar system, measuring more than 14 times the diameter of the
sun.  The inner part of the magnetic field is doughnut-shaped, but farther out
it flattens into a disk.  The magnetic poles are offset and tilted relative to
Jupiter's axis of rotation, so the field appears to wobble with Jupiter's
rotation (just under 10 hours), sweeping up and down across the inner
satellites and making waves throughout the magnetosphere.








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              SPACE SHUTTLE MISSION STS-34


--WHY JUPITER INVESTIGATIONS ARE IMPORTANT


    With a thin skin of turbulent winds and brilliant, swift-moving clouds, the
huge sphere of Jupiter is a vast sea of liquid hydrogen and helium.  Jupiter's
composition (about 88 percent hydrogen and 11 percent helium with small amounts
of methane, ammonia and water) is thought to resemble the makeup of the solar
nebula, the cloud of gas and dust from which the sun and planets formed.
Scientists believe Jupiter holds important clues to conditions in the early
solar system and the process of planet formation.

    Jupiter may also provide insights into the formation of the universe
itself.  Since it resembles the interstellar gas and dust  that are thought to
have been created in the "Big Bang," studies of Jupiter may help scientists
calibrate models of the beginning of the universe.

    Though starlike in composition, Jupiter is too small to generate
temperatures high enough to ignite nuclear fusion, the process that powers the
stars.    Some scientists believe that the sun and Jupiter began as unequal
partners in a binary star system.  (If a double star system had developed, it
is unlikely life could have arisen in the solar system.)  While in a sense a
"failed star," Jupiter is almost as large as a planet can be.  If it contained
more mass, it would not have grown larger, but would have shrunk from
compression by its own gravity.  If it were 100 times more massive,
thermonuclear reactions would ignite, and Jupiter would be a star.

    For a brief period after its formation, Jupiter was much hotter, more
luminous, and about 10 times larger than it is now, scientists believe.  Soon
after accretion (the condensation of a gas and dust cloud into a planet), its
brightness dropped from about one percent of the Sun's to about one billionth
-- a decline of ten million times.

    In its present state Jupiter emits about twice as much heat as it receives
from the Sun.  The loss of this heat -- residual energy left over from the
compressive heat of accretion -- means that Jupiter is cooling and losing
energy at a tremendously rapid rate.  Temperatures in Jupiter's core, which
were about 90,000 degrees Fahrenheit in the planet's hot, early phase, are now
about 54,000 degrees Fahrenheit, 100 times hotter than any terrestrial surface,
but 500 times cooler than the temperature at the center of the sun.
Temperatures on Jupiter now range from 54,000 degrees Fahrenheit at the core to
minus 248 degrees Fahrenheit at the top of the cloud banks.

    Mainly uniform in composition, Jupiter's structure is determined by
gradations in temperature and pressure.  Deep in Jupiter's interior there is
thought to be a small rocky core, comprising about four percent of the planet's
mass.  This "small" core (about the size of 10 Earths) is surrounded by a
25,000-mile-thick layer of liquid metallic hydrogen.  (Metallic hydrogen is
liquid, but sufficiently compressed to behave as metal.)  Motions of this
liquid "metal" are the source of the planet's enormous magnetic field.    This
field is created by the same dynamo effect found in the metallic cores of Earth
and other planets.

    At the outer limit of the metallic hydrogen layer, pressures equal three
million times that of Earth's atmosphere and the temperature has cooled to
19,000 degrees Fahrenheit.

    Surrounding the central metallic hydrogen region is an outer shell of
"liquid" molecular hydrogen.  Huge pressures compress Jupiter's gaseous


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              SPACE SHUTTLE MISSION STS-34


hydrogen until, at this level, it behaves like a liquid.  The liquid hydrogen
layer extends upward for about 15,000 miles.  Then it gradually becomes
gaseous.  This transition region between liquid and gas marks, in a sense,
where the solid and liquid planet ends and its atmosphere begins.

    From here, Jupiter's atmosphere extends up for 600 more miles, but only in
the top 50 miles are found the brilliant bands of clouds for which Jupiter is
known.    The tops of these bands are colored bright yellow, red and orange from
traces of phosphorous and sulfur.  Five or six of these bands, counterflowing
east and west, encircle the planet in each hemisphere.    At one point near
Jupiter's equator, east winds of 220 mph blow right next to west winds of 110
mph.  At boundaries of these bands, rapid changes in wind speed and direction
create large areas of turbulence and shear.  These are the same forces that
create tornados here on Earth.    On Jupiter, these "baroclinic instabilities"
are major phenomena, creating chaotic, swirling winds and spiral features such
as White Ovals.

    The brightest cloud banks, known as zones, are believed to be higher,
cooler areas where gases are ascending.  The darker bands, called belts, are
thought to be warmer, cloudier regions of descent.

    The top cloud layer consists of white cirrus clouds of ammonia crystals, at
a pressure six-tenths that of Earth's atmosphere at sea level (.6 bar).
Beneath this layer, at a pressure of about two Earth atmospheres (2 bars) and a
temperature of near minus 160 degrees Fahrenheit, a reddish-brown cloud of
ammonium hydrosulfide is predicted.

    At a pressure of about 6 bars, there are believed to be clouds of water and
ice.  However, recent Earth-based spectroscopic studies suggest that there may
be less water on Jupiter than expected.  While scientists previously believed
Jupiter and the sun would have similar proportions of water, recent work
indicates there may be 100 times less water on Jupiter than if it had a solar
mixture of elements.  If this is the case, there may be only a thin layer of
water-ice at the 6 bar level.

    However, Jupiter's cloud structure, except for the highest layer of ammonia
crystals, remains uncertain.  The height of the lower clouds is still
theoretical -- clouds are predicted to lie at the temperature levels where
their assumed constituents are expected to condense.  The Galileo probe will
make the first direct observations of Jupiter's lower atmosphere and clouds,
providing crucial information.

    The forces driving Jupiter's fast-moving winds are not well understood yet.
The classical explanation holds that strong currents are created by convection
of heat from Jupiter's hot interior to the cooler polar regions, much as winds
and ocean currents are driven on Earth, from equator to poles.    But temperature
differences do not fully explain wind velocities that can reach 265 mph.  An
alternative theory is that pressure differences, due to changes in the
thermodynamic state of hydrogen at high and low temperatures, set up the wind
jets.

    Jupiter's rapid rotation rate is thought to have effects on wind velocity
and to produce some of Jupiter's bizarre circulation patterns, including many
spiral features.  These rotational effects are known as manifestations of the
Coriolis force.  Coriolis force is what determines the spin direction of
weather systems.  It basically means that on the surface of a sphere (a
planet), a parcel of gas farther from the poles has a higher rotational
velocity around the planet than a parcel closer to the poles.  As gases then


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              SPACE SHUTTLE MISSION STS-34


move north or south, interacting parcels with different velocities produce
vortices (whirlpools).    This may account for some of Jupiter's circular surface
features.

    Jupiter spins faster than any planet in the solar system.  Though 11 times
Earth's diameter, Jupiter spins more than twice as fast (once in 10 hours),
giving gases on the surface extremely high rates of travel -- 22,000 mph at the
equator, compared with 1000 mph for air at Earth's equator.  Jupiter's rapid
spin also causes this gas and liquid planet to flatten markedly at the poles
and bulge at the equator.

    Visible at the top of Jupiter's atmosphere are eye-catching features such
as the famous Great Red Spot and the exotic White Ovals, Brown Barges and White
Plumes.  The Great Red Spot, which is 25,000 miles wide and large enough to
swallow three Earths, is an enormous oval eddy of swirling gases.  It is driven
by two counter-flowing jet streams, which pass, one on each side of it, moving
in opposite directions, each with speeds of 100-200 mph.  The Great Red Spot
was first discovered in 1664, by the British scientist Roger Hook, using
Galileo's telescope.  In the three centuries since, the  huge vortex has
remained constant in latitude in Jupiter's southern equatorial belt.  Because
of its stable position, astronomers once thought it might be a volcano.

    Another past theory compared the Great Red Spot to a gigantic hurricane.
However, the GRS rotates anti-cyclonically while hurricanes are cyclonic
features (counterclockwise in the northern hemisphere, clockwise in the
southern) -- and the dynamics of the Great Red Spot appear unrelated to
moisture.

    The Great Red Spot most closely resembles an enormous tornado, a huge
vortex that sucks in smaller vortices.    The Coriolis effect created by
Jupiter's fast spin, appears to be the key to the dynamics that drive the
spot.

    The source of the Great Red Spot's color remains a mystery.  Many
scientists now believe it to be caused by phosphorus, but its spectral line
does not quite match that of phosphorus.  The GRS may be the largest in a whole
array of spiral phenomena with similar dynamics.  About a dozen white ovals,
circulation patterns resembling the GRS, exist in the southern latitudes of
Jupiter and appear to be driven by the same forces.  Scientists do not know why
these ovals are white.

    Scientists believe the brown barges, which appear like dark patches on the
planet, are holes in the upper clouds, through which the reddish-brown lower
cloud layer may be glimpsed.  The equatorial plumes, or white plumes, may be a
type of wispy cirrus anvil cloud.















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              SPACE SHUTTLE MISSION STS-34


--GALILEO MANAGEMENT


    The Galileo Project is managed for NASA's Office of Space Science and
Applications by the NASA Jet Propulsion Laboratory, Pasadena, Calif.  This
responsibility includes designing, building, testing, operating and tracking
Galileo.  NASA's Ames Research Center, Moffett Field, Calif. is responsible for
the atmosphere probe, which was built by Hughes Aircraft Company, El Segundo,
Calif.

    The probe project and science teams will be stationed at Ames during
pre-mission, mission operations, and data reduction periods.  Team members will
be at Jet Propulsion Laboratory for probe entry.

    The Federal Republic of Germany has furnished the orbiter's retro-
propulsion module and is participating in the scientific investigations.  The
radioisotope thermoelectric generators were designed and built for the U.S.
Department of Energy by the General Electric Company.




--STS-34 INERTIAL UPPER STAGE (IUS-19)


    The Inertial Upper Stage (IUS) will again be used with the Space Shuttle,
this time to transport NASA's Galileo spacecraft out of Earth's orbit to
Jupiter, a 2.5-billion-mile journey.

    The IUS has been used previously to place three Tracking and Data Relay
Satellites in geostationary orbit as well as to inject the Magellan spacecraft
into its interplanetary trajectory to Venus.  In addition, the IUS has been
selected by the agency for the Ulysses solar polar orbit mission.

    After 2 1/2 years of competition, Boeing Aerospace Co., Seattle, was
selected in August 1976 to begin preliminary design of the IUS.  The IUS was
developed and built under contract to the Air Force Systems Command's Space
Systems Division.  The Space Systems Division is executive agent for all
Department of Defense activities pertaining to the Space Shuttle system.  NASA,
through the Marshall Space Flight Center, Huntsville, Ala., purchases the IUS
through the Air Force and manages the integration activities of the upper stage
to NASA spacecraft.



--Specifications


    IUS-19, to be used on mission STS-34, is a two-stage vehicle weighing
approximately 32,500 lbs.  Each stage has a solid rocket motor (SRM), preferred
over liquid-fueled engines because of SRM's relative simplicity, high
reliability, low cost and safety.

    The IUS is 17 ft. long and 9.25 ft. in diameter.  It consists of an aft
skirt, an aft stage SRM generating approximately 42,000 lbs. of thrust, an
interstage, a forward-stage SRM generating approximately 18,000 lbs. of thrust,
and an equipment support section.



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              SPACE SHUTTLE MISSION STS-34


Airborne Support Equipment

    The IUS Airborne Support Equipment (ASE) is the mechanical, avionics and
structural equipment located in the orbiter.  The ASE supports the IUS and the
Galileo in the orbiter payload bay and elevates the combination for final
checkout and deployment from the orbiter.

    The IUS ASE consists of the structure, electromechanical mechanisms,
batteries, electronics and cabling to support the Galileo/IUS.    These ASE
subsystems enable the deployment of the combined vehicle; provide, distribute
and/or control electrical power to the IUS and spacecraft; provide plumbing to
cool the radioisotope thermoelectric generator (RTG) aboard Galileo; and serve
as communication paths between the IUS and/or spacecraft and the orbiter.



--IUS Structure


    The IUS structure is capable of supporting loads generated internally and
also by the cantilevered spacecraft during orbiter operations and the IUS free
flight.  It is made of aluminum skin-stringer construction, with longerons and
ring frames.



--Equipment Support Section


    The top of the equipment support section contains the spacecraft interface
mounting ring and electrical interface connector segment for mating and
integrating the spacecraft with the IUS.  Thermal isolation is provided by a
multilayer insulation blanket across the interface between the IUS and
Galileo.

    The equipment support section also contains the avionics which provide
guidance, navigation, control, telemetry, command and data management, reaction
control and electrical power.  All mission-critical components of the avionics
system, along with thrust vector actuators, reaction control thrusters, motor
igniter and pyrotechnic stage separation equipment are redundant to assure
reliability of better than 98 percent.



--IUS Avionics Subsystems


    The avionics subsystems consist of the telemetry, tracking and command
subsystems; guidance and navigation subsystem; data management; thrust vector
control; and electrical power subsystems.  These subsystems include all the
electronic and electrical hardware used to perform all computations, signal
conditioning, data processing and formatting associated with navigation,
guidance, control, data and redundancy management.  The IUS avionics subsystems
also provide the equipment for communications between the orbiter and ground
stations as well as electrical power distribution.

    Attitude control in response to guidance commands is provided by thrust
vectoring during powered flight and by reaction control thrusters while


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              SPACE SHUTTLE MISSION STS-34


coasting.  Attitude is compared with guidance commands to generate error
signals.  During solid motor firing, these commands gimble the IUS's movable
nozzle to provide the desired pitch and yaw control.  The IUS's roll axis
thrusters maintain roll control.  While coasting, the error signals are
processed in the computer to generate thruster commands to maintain the
vehicle's altitude or to maneuver the vehicle.

    The IUS electrical power subsystem consists of avionics batteries, IUS
power distribution units, a power transfer unit, utility batteries, a
pyrotechnic switching unit, an IUS wiring harness and umbilical and staging
connectors.  The IUS avionics system provides 5-volt electrical power to the
Galileo/IUS interface connector for use by the spacecraft telemetry system.



--IUS Solid Rocket Motors


    The IUS two-stage vehicle uses a large solid rocket motor and a small solid
rocket motor.  These motors employ movable nozzles for thrust vector control.
The nozzles provide up to 4 degrees of steering on the large motor and 7
degrees on the small motor.  The large motor is the longest-thrusting duration
SRM ever developed for space, with the capability to thrust as long as 150
seconds.  Mission requirements and constraints (such as weight) can be met by
tailoring the amount of propellant carried.  The IUS-19 first-stage motor will
carry 21,488 lb. of propellant; the second stage 6,067 lb.



--Reaction Control System


    The reaction control system controls the Galileo/IUS spacecraft attitude
during coasting, roll control during SRM thrustings, velocity impulses for
accurate orbit injection and the final collision-avoidance maneuver after
separation from the Galileo spacecraft.

    As a minimum, the IUS includes one reaction control fuel tank with a
capacity of 120 lb. of hydrazine.  Production options are available to add a
second or third tank.  However, IUS-19 will require only one tank.



--IUS To Spacecraft Interfaces


    Galileo is physically attached to the IUS at eight attachment points,
providing substantial load-carrying capability while minimizing the transfer of
heat across the connecting points.   Power, command and data transmission
between the two are provided by several IUS interface connectors.  In
addition, the IUS provides a multilayer insulation blanket of aluminized Kapton
with polyester net spacers across the Galileo/IUS interface, along with an
aluminized Beta cloth outer layer.  All IUS thermal blankets are vented toward
and into the IUS cavity, which in turn is vented to the orbiter payload bay.
There is no gas flow between the spacecraft and the IUS.  The thermal blankets
are grounded to the IUS structure to prevent electrostatic charge buildup.




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              SPACE SHUTTLE MISSION STS-34


--Flight Sequence

    After the orbiter payload bay doors are opened in orbit, the orbiter will
maintain a preselected attitude to keep the payload within thermal requirements
and constraints.

    On-orbit predeployment checkout begins, followed by an IUS command link
check and spacecraft communications command check.  Orbiter trim maneuvers are
normally performed at this time.

    Forward payload restraints will be released and the aft frame of the
airborne-support equipment will tilt the Galileo/IUS to 29 degrees.  This will
extend the payload into space just outside the orbiter payload bay, allowing
direct communication with Earth during systems checkout.  The orbiter then will
be maneuvered to the deployment attitude.  If a problem has developed within
the spacecraft or IUS, the IUS and its payload can be restowed.

    Prior to deployment, the spacecraft electrical power source will be
switched from orbiter power to IUS internal power by the orbiter flight crew.
After verifying that the spacecraft is on IUS internal power and that all
Galileo/IUS predeployment operations have been successfully completed, a
GO/NO-GO decision for deployment will be sent to the crew from ground support.

    When the orbiter flight crew is given a "Go" decision, they will activate
the ordnance that separates the spacecraft's umbilical cables.    The crew then
will command the electromechanical tilt actuator to raise the tilt table to a
58-degree deployment position.    The orbiter's RCS thrusters will be inhibited
and an ordnance-separation device initiated to physically separate the
IUS/spacecraft combination from the tilt table.

    Six hours, 20 minutes into the mission, compressed springs provide the
force to jettison the IUS/Galileo from the orbiter payload bay at approximately
6 inches per second.  The deployment is normally performed in the shadow of the
orbiter or in Earth eclipse.

    The tilt table then will be lowered to minus 6 degrees after IUS and its
spacecraft are deployed.  A small orbiter maneuver is made to back away from
IUS/Galileo.  Approximately 15 minutes after deployment, the orbiter's OMS
engines will be ignited to move the orbiter away from its released payload.

    After deployment, the IUS/Galileo is controlled by the IUS onboard
computers.  Approximately 10 minutes after IUS/Galileo deployment from the
orbiter, the IUS onboard computer will send out signals used by the IUS and/or
Galileo to begin mission sequence events.  This signal will also enable the IUS
reaction control system.  All subsequent operations will be sequenced by the
IUS computer, from transfer orbit injection through spacecraft separation and
IUS deactivation.

    After the RCS has been activated, the IUS will maneuver to the required
thermal attitude and perform any required spacecraft thermal control
maneuvers.

    At approximately 45 minutes after deployment from the orbiter, the ordnance
inhibits for the first SRM will be removed.  The belly of the orbiter already
will have been oriented towards the IUS/Galileo to protect orbiter windows from
the IUS's plume.  The IUS will recompute the first ignition time and maneuvers
necessary to attain the proper attitude for the first thrusting period.  When
the proper transfer orbit opportunity is reached, the IUS computer will send


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              SPACE SHUTTLE MISSION STS-34


the signal to ignite the first stage motor 60 minutes after deployment.  After
firing approximately 150 seconds, the IUS first stage will have expended its
propellant and will be separated from the IUS second stage.

    Approximately 140 seconds after first-stage burnout, the second- stage
motor will be ignited, thrusting about 108 seconds.   The IUS second stage then
will separate and perform a final collision/contamination avoidance maneuver
before deactivating.





--SHUTTLE SOLAR BACKSCATTER ULTRAVIOLET INSTRUMENT


    The Shuttle Solar Backscatter Ultraviolet (SSBUV) instrument was developed
by NASA to calibrate similar ozone measuring space-based instruments on the
National Oceanic and Atmospheric Administration's TIROS satellites (NOAA-9 and
-11).

    The SSBUV will help scientists solve the problem of data reliability caused
by calibration drift of solar backscatter ultraviolet (SBUV) instruments on
orbiting spacecraft.  The SSBUV uses the Space Shuttle's orbital flight path to
assess instrument performance by directly comparing data from identical
instruments aboard the TIROS spacecraft, as the Shuttle and the satellite pass
over the same Earth location within a 1-hour window.  These orbital
coincidences can occur 17 times per day.

    The SBUV measures the amount and height distribution of ozone in the upper
atmosphere.  It does this by measuring incident solar ultraviolet radiation and
ultraviolet radiation backscattered from the Earth's atmosphere.  The SBUV
measures these parameters in 12 discrete wavelength channels in the
ultraviolet.  Because ozone absorbs in the ultraviolet, an ozone measurement
can be derived from the ratio of backscatter radiation at different
wavelengths, providing an index of the vertical distribution of ozone in the
atmosphere.

    Global concern over the depletion of the ozone layer has sparked increased
emphasis on developing and improving ozone measurement methods and instruments.
Accurate, reliable measurements from space are critical to the detection of
ozone trends and for assessing the potential effects and development of
corrective measures.

    The SSBUV missions are so important to the support of Earth science that
six additional missions have been added to the Shuttle manifest for calibrating
ozone instruments on future TIROS satellites.  In addition, the dates of the
four previously manifested SSBUV flights have been accelerated.

    The SSBUV instrument and its dedicated electronics, power, data and command
systems are mounted in the Shuttle's payload bay in two Get Away Special
canisters, an instrument canister and a support canister.  Together, they weigh
approximately 1200 lb.     The instrument canister holds the SSBUV, its specially
designed aspect sensors and in-flight calibration system.  A motorized door
assembly opens the canister to allow the SSBUV to view the sun and Earth and
closes during the in-flight calibration sequence.




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              SPACE SHUTTLE MISSION STS-34


    The support canister contains the power system, data storage and command
decoders.  The dedicated power system can operate the SSBUV for a total of
approximately 40 hours.

    The SSBUV is managed by NASA's Goddard Space Flight Center, Greenbelt, Md.
Ernest Hilsenrath is the principal investigator.





--GROWTH HORMONE CONCENTRATIONS AND DISTRIBUTION IN PLANTS


    The Growth Hormone Concentration and Distribution in Plants (GHCD)
experiment is designed to determine the effects of microgravity on the
concentration, turnover properties, and behavior of the plant growth hormone,
Auxin, in corn shoot tissue (Zea Mays).

    Mounted in foam blocks inside two standard middeck lockers, the equipment
consists of four plant cannisters, two gaseous nitrogen freezers and two
temperature recorders.    Equipment for the experiment, excluding the lockers,
weighs 97.5 pounds.

    A total of 228 specimens (Zea Mays seeds) are "planted" in special filter,
paper-Teflon tube holders no more than 56 hours prior to flight.  The seeds
remain in total darkness throughout the mission.

    The GHCD experiment equipment and specimens will be prepared in a Payload
Processing Facility at KSC and placed in the middeck lockers.  The GHCD lockers
will be installed in the orbiter middeck within the last 14 hours before
launch.

    No sooner than 72 hours after launch, mission specialist Ellen Baker will
place two of the plant cannisters into the gaseous nitrogen freezers to arrest
the plant growth and preserve the specimens.  The payload will be restowed in
the lockers for the remainder of the mission.

    After landing, the payload must be removed from the orbiter within 2 hours
and will be returned to customer representatives at the landing site.  The
specimens will be examined post flight for microgravity effects.

     The GHCD experiment is sponsored by NASA Headquarters, the Johnson Space
Center and Michigan State University.





--POLYMER MORPHOLOGY


    The Polymer Morphology (PM) experiment is a 3M-developed organic materials
processing experiment designed to explore the effects of microgravity on
polymeric materials as they are processed in space.

    Since melt processing is one of the more industrially significant methods
for making products from polymers, it has been chosen for study in the PM


                  - Page 32 -


              SPACE SHUTTLE MISSION STS-34


experiment.  Key aspects of melt processing include polymerization,
crystallization and phase separation.  Each aspect will be examined in the
experiment.  The polymeric systems for the first flight of PM include
polyethelyne, nylon-6 and polymer blends.

    The apparatus for the experiment includes a Fournier transform infrared
(FTIR) spectrometer, an automatic sample manipulating system and a process
control and data acquisition computer known as the Generic Electronics Module
(GEM).    The experiment is contained in two separate, hermetically sealed
containers that are mounted in the middeck of the orbiter.  Each container
includes an integral heat exchanger that transfers heat from the interior of
the containers to the orbiter's environment.  All sample materials are kept in
triple containers for the safety of the astronauts.

    The PM experiment weighs approximately 200 lb., occupies three standard
middeck locker spaces (6 cubic ft., total) in the orbiter and requires 240
watts to operate.

    Mission specialists Franklin R. Chang-Diaz and Shannon W. Lucid are
responsible for the operation of the PM experiment on orbit.  Their interface
with the PM experiment is through a small, NASA-supplied laptop computer that
is used as an input and output device for the main PM computer.  This interface
has been programmed by 3M engineers to manage and display the large quantity of
data that is available to the crew.  The astronauts will have an active role in
the operation of the experiment.

    In the PM experiment, infrared spectra (400 to 5000 cm-1) will be acquired
from the FTIR by the GEM computer once every 3.2 seconds as the materials are
processed on orbit.  During the 100 hours of processing time, approximately 2
gigabytes of data will be collected.  Post flight, 3M scientists will process
the data to reveal the effects of microgravity on the samples processed in
space.

    The PM experiment is unique among material processing experiments in that
measurements characterizing the effects of microgravity will be made in real
time, as the materials are processed in space.

    In most materials processing space experiments, the materials have been
processed in space with little or no measurements made during on-orbit
processing and the effects of microgravity determined post facto.

    The samples of polymeric materials being studied in the PM experiment are
thin films (25 microns or less) approximately 25 mm in diameter.  The samples
are mounted between two infrared transparent windows in a specially designed
infrared cell that provides the capability of  thermally processing the samples
to 200 degrees Celsius with a high degree of thermal control.  The samples are
mounted on a carousel that allows them to be positioned, one at a time, in the
infrared beam where spectra may be acquired.  The GEM provides all carousel and
sample cell control.  The first flight of PM will contain 17 samples.

    The PM experiment is being conducted by 3M's Space Research and
Applications Laboratory.  Dr. Earl L. Cook is 3M's Payload Representative and
Mission Coordinator.  Dr. Debra L. Wilfong is  PM's Science Coordinator, and
James E. Steffen is the Hardware Coordinator.

    The PM experiment, a commercial development payload, is sponsored by NASA's
Office of Commercial Programs.    The PM experiment will be 3M's fifth space
experiment and the first under the company's 10-year Joint Endeavor Agreement


                  - Page 33 -


              SPACE SHUTTLE MISSION STS-34


with NASA for 62 flight experiment opportunities.  Previous 3M space
experiments have studied organic crystal growth from solution (DMOS/1 on
mission STS 51-A and DMOS/2 on STS 61-B) and organic thin film growth by
physical vapor treatment (PVTOS/1 on STS 51-I and PVTOS/2 on mission STS-26).







--STUDENT EXPERIMENT


    Zero Gravity Growth of Ice Crystals From Supercooled Water With Relation To
Temperature (SE82-15)

    This experiment, proposed by Tracy L. Peters, formerly of Ygnacio High
School, Concord, Calif., will observe the geometric ice crystal shapes formed
at supercooled temperatures, below 0 degrees Celsius, without the influence of
gravity.

    Liquid water has been discovered at temperatures far below water's freezing
point.    This phonomenon occurs because liquid water does not have a nucleus, or
core, around which to form the crystal.  When the ice freezes at supercold
temperatures, the ice takes on many geometric shapes based on the hexagon.  The
shape of the crystal primarily depends on the supercooled temperature and
saturation of water vapor.  The shapes of crystals vary from simple plates to
complex prismatic crystals.

    Many scientists have tried to determine the relation between temperature
and geometry, but gravity has deformed crystals, caused convection currents in
temperature-controlled apparatus, and caused faults in the crystalline
structure.  These all affect crystal growth by either rapid fluctuations of
temperature or gravitational influence of the crystal geometry.

    The results of this experiment could aid in the design of radiator cooling
and cryogenic systems and in the understanding of high-altitude meteorology and
planetary ring structure theories.

    Peters is now studying physics at the University of California at Berkeley.
His teacher advisor is James R. Cobb, Ygnacio High School; his sponsor is
Boeing Aerospace Corp., Seattle.

    Peters also was honored as the first four-time NASA award winner at the
International Science and Engineering Fair (ISEF), which recognizes student's
creative scientific endeavors in aerospace research.  At the 1982 ISEF, Peters
was one of two recipients of the Glen T. Seaborg Nobel Prize Visit Award, an
all-expense-paid visit to Stockholm to attend the Nobel Prize ceremonies, for
his project "Penetration and Diffusion of Supersonic Fluid."










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              SPACE SHUTTLE MISSION STS-34


--MESOSCALE LIGHTNING EXPERIMENT


    The Space Shuttle will again carry the Mesoscale Lightning Experiment
(MLE), designed to obtain nighttime images of lightning in order to better
understand the global distribution of lightning, the interrelationships between
lightning events in nearby storms, and relationships between lightning,
convective storms and precipitation.

    A better understanding of the relationships between lightning and
thunderstorm characteristics can lead to the development of applications in
severe storm warning and forecasting, and early warning systems for lightning
threats to life and property.

    In recent years, NASA has used both Space Shuttle missions and
high-altitude U-2 aircraft to observe lightning from above convective storms.
The objectives of these observations have been to determine some of the
baseline design requirements for a satellite-borne optical lightning mapper
sensor; study the overall optical and electrical characteristics of lightning
as viewed from above the cloudtop; and investigate the relationship between
storm electrical development and the structure, dynamics and evolution of
thunderstorms and thunderstorm systems.

    The MLE began as an experiment to demonstrate that meaningful, qualitative
observations of lightning could be made from the Shuttle.  Having accomplished
this, the experiment is now focusing on quantitative measurements of lightning
characteristics and observation simulations for future space-based lightning
sensors.

    Data from the MLE will provide information for the development of
observation simulations for an upcoming polar platform and Space Station
instrument, the Lightning Imaging Sensor (LIS).  The lightning experiment also
will be helpful for designing procedures for using the Lightning Mapper Sensor
(LMS), planned for several geostationary platforms.

    In this experiment, Atlantis'  payload bay camera will be pointed directly
below the orbiter to observe nighttime lightning in large, or mesoscale, storm
systems to gather global estimates of lightning as observed from Shuttle
altitudes.  Scientists on the ground will analyze the imagery for the frequency
of lightning flashes in active storm clouds within the camera's field of view,
the length of lightning discharges, and cloud brightness when illuminated by
the lightning discharge within the cloud.

    If time permits during missions, astronauts also will use a handheld 35mm
camera to photograph lightning activity in storm systems not directly below the
Shuttle's orbital track.

    Data from the MLE will be associated with ongoing observations of lightning
made at several locations on the ground, including observations made at
facilities at the Marshall Space Flight Center, Huntsville, Ala.; Kennedy Space
Center, Fla.; and the NOAA Severe Storms Laboratory, Norman, Okla.  Other
ground-based lightning detection systems in Australia, South America and Africa
will be intergrated when possible.

    The MLE is managed by the Marshall Space Flight Center.  Otha H. Vaughan
Jr., is coordinating the experiment.  Dr. Hugh Christian is the project
scientist, and Dr. James Arnold is the project manager.



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              SPACE SHUTTLE MISSION STS-34


--IMAX


    The IMAX project is a collaboration between NASA and the Smithsonian
Institution's National Air and Space Museum to document significant space
activities using the IMAX film medium.    This system, developed by the IMAX
Systems Corp., Toronto, Canada, uses specially designed 70mm film cameras and
projectors to record and display very high definition large-screen color motion
pictures.

    IMAX cameras previously have flown on Space Shuttle missions 41-C, 41-D and
41-G to document crew operations in the payload bay and the orbiter's middeck
and flight deck along with spectacular views of space and Earth.

    Film from those missions form the basis for the IMAX production, "The Dream
is Alive."  On STS 61-B, an IMAX camera mounted in the payload bay recorded
extravehicular activities in the EAS/ACCESS space construction demonstrations.

    The IMAX camera, most recently carried aboard STS-29, will be used on this
mission to cover the deployment of the Galileo spacecraft and to gather
material on the use of observations of the Earth from space for future IMAX
films.





--AIR FORCE MAUI OPTICAL SITE CALIBRATION TEST


    The Air Force Maui Optical Site (AMOS) tests allow ground-based
electro-optical sensors located on Mt. Haleakala, Maui, Hawaii, to collect
imagery and signature data of the orbiter during cooperative overflights.
Scientific observations made of the orbiter while performing Reaction Control
System thruster firings, water dumps or payload bay light activation are used
to support the calibration of the AMOS sensors and the validation of spacecraft
contamination models.  AMOS tests have no payload-unique flight hardware and
only require that the orbiter be in predefined attitude operations and lighting
conditions.

    The AMOS facility was developed by Air Force Systems Command (AFSC) through
its Rome Air Development Center, Griffiss Air Force Base, N.Y., and is
administered and operated by the AVCO Everett Research Laboratory, Maui.  The
principal investigator for the AMOS tests on the Space Shuttle is from AFSC's
Air Force Geophysics Laboratory, Hanscom Air Force Base, Mass.    A co-principal
investigator is from AVCO.

    Flight planning and mission support activities for the AMOS test
opportunities are provided by a detachment of AFSC's Space Systems Division at
Johnson Space Center, Houston.    Flight operations are conducted at JSC Mission
Control Center in coordination with the AMOS facilities located in Hawaii.









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              SPACE SHUTTLE MISSION STS-34


--SENSOR TECHNOLOGY EXPERIMENT


    The Sensor Technology Experiment (STEX) is a radiation detection experiment
designed to measure the natural radiation background.  The STEX is a
self-contained experiment with its own power, sensor, computer control and data
storage.  A calibration pack, composed of a small number of passive threshold
reaction monitors, is attached to the outside of the STEX package.

    Sponsored by the Strategic Defense Initiative Organization, the STEX
package weighs approximately 50 pounds and is stowed in a standard middeck
locker throughout the flight.





--PAYLOAD AND VEHICLE WEIGHTS


    Vehicle/Payload           Weight (Pounds)
    ----------------          ---------------

    Orbiter (Atlantis) Empty          172,018
    Galileo/IUS (payload bay)           43,980
    Galileo support hardware  (middeck)           59
    SSBUV (payload bay)                  637
    SSBUV support                      578
    DSO                           49
    DTO                          170
    GHCD                          130
    IMAX                          269
    MLE                           15
    PM                          219
    SSIP                           70
    STEX                           52
    Orbiter and Cargo at SRB Ignition      264,775
    Total Vehicle at SRB Ignition        4,523,810
    Orbiter Landing Weight              195,283





--SPACEFLIGHT TRACKING AND DATA NETWORK


    Primary communications for most activities on STS-34 will be conducted
through the orbiting Tracking and Data Relay Satellite System (TDRSS), a
constellation of three communications satellites in geosynchronous orbit 22,300
miles above the Earth.    In addition, three NASA Spaceflight Tracking and Data
Network (STDN) ground stations and the NASA Communications Network (NASCOM),
both managed by Goddard Space Flight Center, Greenbelt, Md., will play key
roles in the mission.

    Three stations -- Merritt Island and Ponce de Leon, Florida and the Bermuda
-- serve as the primary communications during the launch and ascent phases of
the mission.  For the first 80 seconds, all voice, telemetry and other


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              SPACE SHUTTLE MISSION STS-34


communications from the Space Shuttle are relayed to the mission managers at
Kennedy and Johnson Space Centers by way of the Merritt Island facility.

    At 80 seconds, the communications are picked up from the Shuttle and
relayed to the two NASA centers from the Ponce de Leon facility, 30 miles north
of the launch pad.  This facility provides the communications between the
Shuttle and the centers for 70 seconds, or until 150 seconds into the mission.
This is during a critical period when exhaust from the solid rocket motors
"blocks out" the Merritt Island antennas.

    The Merritt Island facility resumes communications to and from the Shuttle
after those 70 seconds and maintains them until 6 minutes, 30 seconds after
launch when communications are "switched over" to Bermuda.  Bermuda then
provides the communications until 11 minutes after liftoff when the TDRS-East
satellite acquires the Shuttle.  TDRS-West acquires the orbiter at launch plus
50 minutes.

    The TDRS-East and -West satellites will provide communications with the
Shuttle during 85 percent or better of each orbit.  The TDRS-West satellite
will handle communications with the Shuttle during its descent and landing
phases.





--CREW BIOGRAPHIES



    Donald E. Williams, 47, Capt., USN, will serve as commander.  Selected as
an astronaut in January 1978, he was born in Lafayette, Ind.

    Williams was pilot for STS-51D, the fourth flight of Discovery, launched
April 12, 1985.  During the mission, the seven-member crew deployed the Anik-C
communications satellite for Telesat of Canada and the    Syncom IV-3 satellite
for the U.S. Navy.  A malfunction in the Syncom spacecraft resulted in the
first unscheduled extravehicular, rendezvous and proximity operation for the
Space Shuttle in an attempt to activate the satellite.

    He graduated from Otterbein High School, Otterbein, Ind., in 1960 and
received his B.S. degree in mechanical engineering from Purdue University in
1964.  Williams completed his flight training at Pensacola, Fla., Meridian,
Miss., and Kingsville, Texas, and earned his wings in 1966.

    During the Vietnam Conflict, Williams completed 330 combat missions.  He
has logged more than 5,400 hours flying time, including 5,100 in jets, and 745
aircraft carrier landings.



    Michael J. McCulley, 46, Cdr., USN, will be pilot on this flight. Born in
San Diego, McCulley considers Livingston, Tenn., his hometown.    He was selected
as a NASA astronaut in 1984.  He is making his first Space Shuttle flight.

    McCulley graduated from Livingston Academy in 1961.  He received B.S. and
M.S. degrees in metallurgical engineering from Purdue University in 1970.



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              SPACE SHUTTLE MISSION STS-34


    After graduating from high school, McCulley enlisted in the U.S. Navy and
subsequently served on one diesel-powered and two nuclear-powered submarines.
Following flight training, he served tours of duty in A-4 and A-65 aircraft and
was selected to attend the Empire Test Pilots School in Great Britain.    He
served in a variety of test pilot billets at the Naval Air Test Center,
Patuxent River, Md., before returning to sea duty on the USS Saratoga and USS
Nimitz.

    He has flown more than 50 types of aircraft, logging more than 4,760 hours,
and has almost 400 carrier landings on six aircraft carriers.



    Shannon W. Lucid, 46, will serve as mission specialist (MS-1) on this, her
second Shuttle flight.    Born in Shanghai, China, she considers Bethany, Okla.,
her hometown.  Lucid is a member of the astronaut class of 1978.

    Lucid's first Shuttle mission was during STS 51-G, launched from the
Kennedy Space Center on June 17, 1985.    During that flight, the crew deployed
communications satellites for Mexico, the Arab League and the United States.

    Lucid graduated from Bethany High School in 1960.  She then attended the
University of Oklahoma where she received a B.S. degree in chemistry in 1963,
an M.S. degree in biochemistry in 1970 and a Ph.D. in biochemistry in 1973.

    Before joining NASA, Lucid held a variety of academic assignments such as
teaching assistant at the University of Oklahoma's department of chemistry;
senior laboratory technician at the Oklahoma Medical Research Foundation;
chemist at Kerr-McGee in Oklahoma City; graduate assistant in the University of
Oklahoma Health Science Center's department of biochemistry; and molecular
biology and research associate with the Oklahoma Medical Research Foundation in
Oklahoma City.    Lucid also is a commercial, instrument and multi-engine rated
pilot.



    Franklin Chang-Diaz, 39, will serve as MS-2.  Born in San Jose, Costa Rica,
Chang-Diaz also will be making his second flight since being selected as an
astronaut in 1980.

    Chang-Diaz made his first flight aboard Columbia on mission STS 61-C,
launched from KSC Jan. 12, 1986.  During the 6-day flight he participated in
the deployment of the SATCOM KU satellite, conducted experiments in
astrophysics and operated the materials science laboratory, MSL-2.

    Chang-Diaz graduated from Colegio De La Salle, San Jose, Costa Rica, in
1967, and from Hartford High School, Hartford, Conn., in 1969.    He received a
B.S. degree in mechanical engineering from the University of Connecticut in
1973 and a Ph.D. in applied plasma physics from the Massachusetts Institute of
Technology in 1977.

    While attending the University of Connecticut, Chang-Diaz also worked as a
research assistant in the physics department and participated in the design and
construction of high-energy atomic collision experiments.  Upon entering
graduate school at MIT, he became heavily involved in the United State's
controlled fusion program and conducted intensive research in the design and
operation of fusion reactors.  In 1979, he developed a novel concept to guide
and target fuel pellets in an inertial fusion reactor chamber.    In 1983, he was


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              SPACE SHUTTLE MISSION STS-34


appointed as visiting scientist with the MIT Plasma Fusion Center which he
visits periodically to continue his research on advanced plasma rockets.

    Chang-Diaz has logged more than 1,500 hours of flight time, including 1,300
hours in jet aircraft.



    Ellen S. Baker, 36, will serve as MS-3.  She will be making her first
Shuttle flight.  Baker was born in Fayetteville, N.C., and was selected as an
astronaut in 1984.

    Baker graduated from Bayside High School, New York, N.Y., in 1970.    She
received a B.A. degree in geology from the State University of New York at
Buffalo in 1974, and an M.D. from Cornell University in 1978.

    After medical school, Baker trained in internal medicine at the University
of Texas Health Science Center in San Antonio, Texas.  In 1981, she was
certified by the American Board of Internal Medicine.

    Baker joined NASA as a medical officer at the Johnson Space Center in 1981
after completing her residency.  That same year, she graduated with honors from
the Air Force Aerospace Medicine Primary Course at Brooks Air Force Base in San
Antonio.  Prior to her selection as an astronaut, she served as a physician in
the Flight Medicine Clinic at JSC.



































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              SPACE SHUTTLE MISSION STS-34


--NASA PROGRAM MANAGEMENT


NASA Headquarters
Washington, D.C.

Richard H. Truly
NASA Administrator

James R. Thompson Jr.
NASA Deputy Administrator

William B. Lenoir
Acting Associate Administrator for Space Flight

George W.S. Abbey
Deputy Associate Administrator for Space Flight

Arnold D. Aldrich
Director, National Space Transportation Program

Leonard S. Nicholson
Deputy Director, NSTS Program (located at Johnson Space Center)

Robert L. Crippen
Deputy Director, NSTS Operations (located at Kennedy Space Center)

David L. Winterhalter
Director, Systems Engineering and Analyses

Gary E. Krier
Director, Operations Utilization

Joseph B. Mahon
Deputy Associate Administrator for Space Flight (Flight Systems)

Charles R. Gunn
Director, Unmanned Launch Vehicles and Upper Stages

George A. Rodney
Associate Administrator for Safety, Reliability,
Maintainability and Quality Assurance

Charles T. Force
Associate Administrator for Operations

Dr. Lennard A. Fisk
Associate Administrator for Space Science and Applications

Samuel Keller
Assistant Deputy Associate Administrator
NASA Headquarters

Al Diaz
Deputy Associate Administrator for Space Science and Applications

Dr. Geoffrey A. Briggs
Director, Solar System Exploration Division


                  - Page 41 -


              SPACE SHUTTLE MISSION STS-34


Robert F. Murray
Manager, Galileo Program

Dr. Joseph Boyce
Galileo Program Scientist



Johnson Space Center
Houston, Texas

Aaron Cohen
Director

Paul J. Weitz
Deputy Director

Richard A. Colonna
Manager, Orbiter and GFE Projects

Donald R. Puddy
Director, Flight Crew Operations

Eugene F. Kranz
Director, Mission Operations

Henry O. Pohl
Director, Engineering

Charles S. Harlan
Director, Safety, Reliability and Quality Assurance



Kennedy Space Center
Florida

Forrest S. McCartney
Director

Thomas E. Utsman
Deputy Director

Jay F. Honeycutt
Director, Shuttle Management and Operations

Robert B. Sieck
Launch Director

George T. Sasseen
Shuttle Engineering Director

Conrad G. Nagel
Atlantis Flow Director

James A. Thomas
Director, Safety, Reliability and Quality Assurance



                  - Page 42 -


              SPACE SHUTTLE MISSION STS-34


John T. Conway
Director, Payload Managerment and Operations



Marshall Space Flight Center
Huntsville, Ala.

Thomas J. Lee
Director

Dr. J. Wayne Littles
Deputy Director

G. Porter Bridwell
Manager, Shuttle Projects Office

Dr. George F. McDonough
Director, Science and Engineering

Alexander A. McCool
Director, Safety, Reliability and Quality Assurance

Royce E. Mitchell
Manager, Solid Rocket Motor Project

Cary H. Rutland
Manager, Solid Rocket Booster Project

Jerry W. Smelser
Manager, Space Shuttle Main Engine Project

G. Porter Bridwell
Acting Manager, External Tank Project

Sidney P. Saucier
Manager, Space Systems Projects Office [for IUS]



Stennis Space Center
Bay St. Louis, Miss.

Roy S. Estess
Director

Gerald W. Smith
Deputy Director

William F. Taylor
Associate Director

J. Harry Guin
Director,  Propulsion Test Operations

Edward L. Tilton III
Director, Science and Technology Laboratory



                  - Page 43 -


              SPACE SHUTTLE MISSION STS-34


John L. Gasery Jr.
Chief, Safety/Quality Assurance and Occupational Health



Jet Propulsion Laboratory

Dr. Lew Allen
Director

Dr. Peter T. Lyman
Deputy Director

Gene Giberson
Laboratory Director for Flight Projects

John Casani
Assistant Laboratory Director for Flight Projects

Richard J. Spehalski
Manager, Galileo Project

William J. O'Neil
Manager, Science and Mission Design, Galileo Project

Dr. Clayne M. Yeates
Deputy Manager, Science and Mission Design, Galileo Project

Dr. Torrence V Johnson
Galileo Project Scientist

Neal E. Ausman Jr.
Mission Operations and Engineering Manager, Galileo Project

A. Earl Cherniack
Orbiter Spacecraft Manager, Galileo Project

Matthew R. Landano
Deputy Orbiter Spacecraft Manager, Galileo Project

William G. Fawcett
Orbiter Science Payload Manager, Galileo Project



Ames Research Center
Mountain View, Calif.

Dr. Dale L. Compton
Acting Director

Dr. David Morrison
Director, Science Projects Directorate

Benny Chin
Probe Manager, Galileo Project




                  - Page 44 -


              SPACE SHUTTLE MISSION STS-34


Lawrence Colin
Probe Scientist, Galileo Project

Richard E. Young
Probe Scientist, Galileo Project



Ames-Dryden Flight Research Facility
Edwards, Calif.

Martin A. Knutson
Site Manager

Theodore G. Ayers
Deputy Site Manager

Thomas C. McMurtry
Chief, Research Aircraft Operations Division

Larry C. Barnett
Chief, Shuttle Support Office



Goddard Space Flight Center
Greenbelt, Md

Dr. John W. Townsend
Director

Peter Burr
Director, Flight Projects

Dale L. Fahnestock
Director, Mission Operations and Data Systems

Daniel A. Spintman
Chief, Networks Division

Gary A. Morse
Network Director

Dr. Robert D. Hudson
Head, Atmospheric Chemistry and Dynamics

Ernest Hilsenrath
SSBUV Principal Investigator

Jon R. Busse
Director, Engineering Directorate

Robert C. Weaver Jr.
Chief, Special Payloads Division

Neal F. Barthelme
SSBUV Mission Manager



                  - Page 45 -