Space & Astronomy/Space and Astronomy (October 1993).iso/pc/text/stskits/sts_39.pre

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PUBLIC AFFAIRS CONTACTS

NASA

Mark Hess/Jim Cast/Ed Campion
Office of Space Flight
NASA Headquarters, Washington, D.C.
(Phone:  [phone])

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

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

James Hartsfield
Johnson Space Center, Houston, Texas
(Phone:  [phone])

Delores Beasley
Goddard Space Flight Center, Greenbelt, Md.
(Phone:  [phone])

Myron Webb
Stennis Space Center, Miss.
(Phone:  60l/688-334l)

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

PUBLIC AFFAIRS CONTACTS

DOD

Capt. Marty Hauser
Secretary of the Air Force Public Affairs
The Pentagon
(Phone:  [phone])

Betty Ciotti
USAF Space Systems Division
Los Angeles AFB, Calif.
(Phone:  [phone])

Maj. Carolyn Channave
DOD/SDIO External Affairs
The Pentagon
(Phone:  [phone])

Robert McKinney
SDIO External Affairs
The Pentagon
(Phone:  [phone])

Lt. Col. Jim Jannette
Eastern Space and Missile Center, Fla.
(Phone:  [phone])


CONTENTS

GENERAL INFORMATION                                                  5
GENERAL RELEASE                                                      6
STS-39 QUICK LOOK                                                    9
SUMMARY OF MAJOR ACTIVITIES                                         10
SPACE SHUTTLE ABORT MODES                                           12
TRAJECTORY SEQUENCE OF EVENTS                                       13
VEHICLE AND PAYLOAD WEIGHTS                                         14
STS-39 PRELAUNCH PROCESSING                                         15
SHUTTLE ADVANCED GENERAL PURPOSE COMPUTER                           16
STS-39 MISSION OVERVIEW                                             17
AIR FORCE PAYLOAD-675 (AFP-675)                                     20
CIRRIS-1A                                                           20
AURORA DETAILS                                                      23
FAR UV                                                              24
URA                                                                 25
HUP                                                                 26
QINMS                                                               28
INFRARED BACKGROUND SIGNATURE SURVEY (IBSS)                         29
IBSS OVERVIEW                                                       29
SPAS-II                                                             29
CRO                                                                 29
CIV                                                                 33
IBSS OBJECTIVES                                                     35
IBSS PLUME OBSERVATIONS                                             37
EARTH BACKGROUND EXPERIMENTS                                        37
ORBITER ENVIRONMENT EXPERIMENT                                      38
IBSS PARTICIPANTS                                                   39
STS-39 SPAS/IBSS RENDEZVOUS & TRACKING OPERATIONS                   40
SECONDARY PAYLOADS:
STP-1                                                               44
OVERVIEW                                                            44
HITCHHIKER PROJECT                                                  44
ULTRAVIOLET LIMB IMAGING (UVLIM) EXPERIMENT                         46
ADVANCED LIQUID FEED EXPERIMENT (ALFE)                              46
SPACECRAFT KINETIC INFRARED TEST (SKIRT)                            48
ASCENT PARTICLE MONITOR (APM)                                       49
DATA SYSTEM EXPERIMENT (DSE)                                        50
STP-1 PARTICIPANTS                                                  51
MULTI-PURPOSE EXPERIMENT CANISTER (MPEC)                            52
CLOUDS 1A                                                           52
RADIATION MONITORING EQUIPMENT-III                                  53
STS-39 CREW BIOGRAPHIES                                             54
SPACE SHUTTLE MANAGEMENT                                            58
UPCOMING SPACE SHUTTLE MISSIONS                                     62
PREVIOUS SPACE SHUTTLE FLIGHTS                                      63



    GENERAL INFORMATION

    NASA Select Television Transmission

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

    The schedule for television transmissions from the orbiter and for 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 TV schedule will be updated daily
to reflect changes dictated by mission operations.

    Television schedules also may be obtained by calling COMSTOR,
713/483-5817.  COMSTOR is a computer data base service requiring the
use of a telephone modem.  A voice update of the TV schedule may be
obtained by dialing 202/755-1788.  This service is updated daily at
noon EST.

    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-39 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.



RELEASE:  91-25

STRATEGIC DEFENSE SYSTEM TESTS HIGHLIGHT STS-39 MISSION


Mission STS-39 is the first unclassified Department of Defense-
dedicated Space Shuttle mission, highlighted by around-the-clock
observations of the atmosphere, gas releases, Shuttle engine firings,
subsatellite gas releases and the Shuttle's orbital environment in
wavelengths ranging from infrared to the far ultraviolet.

Carried aboard Discovery on its 12th flight, the 39th Shuttle mission,
will be Air Force Program-675 (AFP-675); the Infrared Background
Signature Survey (IBSS) mounted on the Shuttle Pallet Satellite-II (SPAS-
II); the Critical Ionization Velocity (CIV) experiment; three Chemical
Release Observation (CRO) subsatellites; the Space Test Payload (STP-1)
and a classified payload in a Multi-Purpose Experiment Canister (MPEC).

Inside Discovery's crew cabin will be the Cloud Logic to Optimize the
Use of Defense Systems-1A (CLOUDS-1A) experiment and the Radiation
Monitoring Equipment-III (RME-III).

Work with these payloads during the flight will involve extensive
maneuvering, rendezvous and close proximity operations by Discovery.
STS-39 is currently working toward a 3:49 a.m. EST launch on March 9,
1991. Landing is set for Edwards Air Force Base, Calif., at 11:14 a.m. EST
on March 17, giving the flight a planned length of 8 days, 7 hours and 26
minutes.

AFP-675 is a collection of scientific instruments to observe targets
such as the atmosphere, the aurora and stars in infrared, far ultraviolet,
ultraviolet and X-ray wavelengths. AFP-675 instruments also will analyze
the spectrum of various targets and gases released from or around the
Shuttle. AFP-675 is sponsored by the U.S. Air Force's Space Systems
Division and may provide a better understanding of the difficulties in
identifying spacecraft with remote sensors and distinguishing those
spacecraft from naturally occurring phenomena. The AFP-675 instruments
also are to study several astronomical targets of interest.

The Strategic Defense Initiative Organization's IBSS experiment,
mounted on the SPAS-II platform, will be deployed and retrieved by
Discovery so that SPAS-II can observe the Shuttle's engine firings from
afar. IBSS will observe and record the infrared signature of these firings
and also will perform infrared observations of other targets, including
three CRO subsatellites to be released from Discovery. IBSS will observe
common rocket fuels nitrogen tetroxide, monomethyl hydrazine and
dimethyl hydrazine released from the three CRO subsatellites after they
are deployed by Discovery.

IBSS also will observe releases of the gases xenon, neon, carbon
dioxide and nitric oxide from canisters in Discovery's payload bay. These
gases are part of the CIV experiment, which, with instruments in the
payload bay, will observe the releases simultaneously with IBSS. IBSS is
sponsored by SDIO and information from its studies may assist in
developing remote sensors that can identify missiles.

The STP-1 experiment is a varied collection of scientific instruments,
including one that will observe the luminous "airglow" effect of atomic
oxygen on Discovery; one that will test a new method of flowing rocket
propellants in weightlessness to assist in the design of future engines;
and another to observe the fringes of Earth's atmosphere at various times,
including sunrise and sunset, in ultraviolet wavelengths. STP-1 is
sponsored by the Air Force's Space Systems Division.

Inside the crew cabin, the CLOUDS-1A experiment is a camera the crew
will use to photograph various cloud formations on the Earth to better
understand cloud movements and structures. The RME-III experiment is
designed to monitor radiation levels inside the cabin during the flight.

Commanding Discovery will be Navy Capt. Michael L. Coats. Air Force
Major L. Blaine Hammond will serve as pilot. Mission specialists include
Gregory J. Harbaugh; USAF Lt. Col. Don McMonagle; USAF Col. Guion Bluford;
C. Lacy Veach; and Richard J. Hieb.

The flight crew will operate in two teams to accommodate 24-hour a
day observations aboard Discovery, with each team working a 12-hour
shift. On the Red Team will be Hammond, Veach and Hieb. On the Blue Team
will be Harbaugh, McMonagle and Bluford. Coats will keep his own hours,
independent of any assigned shift.

(End of general release.  Background information follows.)


    STS-39 QUICK LOOK

    Launch Date and Site: Mar. 9, 1991
        Kennedy Space Center, Fla., Pad 39-A

    Launch Window:  3:49 a.m. - 6:51 a.m. EST

    Orbiter:  Discovery (OV-103)

    Orbit:  140 x 140 nautical miles, 57 degrees inclination

    Landing Date/Time:  Mar. 17, 1991, 11:14 a.m. EST

    Primary Landing Site:  Edwards Air Force Base, Calif.

    Abort Landing Sites:
        Return to Launch Site - Kennedy Space Center, Fla.
        Transoceanic Abort Landing - Zaragosa and Moron, Spain
        Abort Once Around - Northrup Strip, White Sands, N.M.

    Crew:
        Michael L. Coats, Commander
        Blaine Hammond, Jr., Pilot
        Gregory L. Harbaugh, Mission Specialist 1
        Donald R. McMonagle, Mission Specialist 2
        Guion S. Bluford, Mission Specialist 3
        C. Lacy Veach, Mission Specialist 4
        Richard J. Hieb, Mission Specialist 5

    Cargo Bay Payloads:
        IBSS/SPAS-II
        CIV
        CRO
        STP-1
        MPEC

    Middeck Payloads:
        Cloud Logic to Optimize the Use of Defense Systems (CLOUDS-1A)
        Radiation Monitoring Experiment (RME-III)


    SUMMARY OF MAJOR ACTIVITIES

    FLIGHT DAY ONE
    Ascent
    OMS 2
    IBSS on-orbit checkout
    AFP-675 activation
    RME-III activation
    DSO

    FLIGHT DAY TWO
    AFP-675 operations
    SPAS pre-deploy checkout
    IBSS/SPAS-II unberth; deploy
    IBSS/SPAS-II far-field observations

    FLIGHT DAY THREE
    IBSS/SPAS-II far-field observations
    IBSS/SPAS-II near-field observations
    CRO-C deploy

    FLIGHT DAY FOUR
    IBSS/SPAS-II near-field observations
    IBSS/SPAS-II rendezvous
    CRO-B deploy
    IBSS/SPAS-II retrieval; berthing
    DSO

    FLIGHT DAY FIVE
    AFP-675 operations
    CRO-A deploy

    FLIGHT DAY SIX
    SPAS-II pre-deploy checkout
    IBSS/SPAS-II unberthing; RMS operations

    FLIGHT DAY SEVEN
    IBSS/SPAS-II berthing
    AFP-675 operations

    FLIGHT DAY EIGHT
    AFP-675 operations
    STP-I operations
    Flight Control Systems checkout
    MPEC deploy
    Payload deactivation
    Cabin stow

    FLIGHT DAY NINE
    RME-III deactivation; stow
    Deorbit; landing


    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 either
Edwards Air Force Base, Calif.; White Sands Space Harbor (Northrup
Strip), NM; or the Shuttle Landing Facility (SLF) at Kennedy Space
Center, FL.

    * Trans-Atlantic Abort Landing (TAL) -- Loss of two main engines
midway through powered flight would force a landing at either
Zaragosa or Moron, Spain.

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

    STS-39 contingency landing sites are Edwards AFB, White Sands,
Kennedy Space Center, Zaragosa and Moron.



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         160            .14            600
End Roll
Maneuver                00/00:00:19         410            .37          3,500
Throttle Down to 70%    00/00:00:28         630            .56          7,170
Throttle Up to 104%     00/00:00:58       1,320           1.28         33,230
Max. Dynamic Pressure   00/00:01:03       1,460           1.45         38,540
SRB Staging             00/00:02:06       4,190           3.8         154,810
Main Engine Cutoff      00/00:08:30      24,900          21.94        375,830
Zero Thrust             00/00:08:40      24,974          21.68        375,830
ET Separation           00/00:08:50
OMS 2 Burn              00/00:38:00
IBSS/SPAS-II Deploy     01/21:10:00
IBSS/SPAS-II Retrieval  03/11:18:00
Deorbit Burn            08/06:31:00
Landing                 08/07:26:00


Apogee, Perigee at MECO: 136 x 23 nautical miles

Apogee, Perigee post-OMS 2: 140 x 140 nautical miles




    VEHICLE AND PAYLOAD WEIGHTS

        Pounds

    Orbiter (Discovery) empty, and 3 SSMEs    172,517

    Remote Manipulator System (payload bay)    1,258

    IBSS/SPAS-II (payload bay)    4,197

    AFP-675 (payload bay)    203

    Chemical Release Observation (CRO) (payload bay)    1,307

    Critical Ionization Velocity (CIV) (payload bay)    1,215

    Space Test Program (STP-I) (payload bay)    4,288

    Radiation Monitoring Experiment-III (RME-III)    8

    Cloud Logic to Optimize the Use of Defense Systems (CLOUDS)    8

    Total Vehicle at SRB Ignition    4,512,245

    Orbiter Landing Weight    211,300


STS-39 PRELAUNCH PROCESSING

     Kennedy Space Center workers began preparing Discovery for its 12th
flight into space when the vehicle was towed into the Orbiter Processing
Facility on Oct. 18 following its previous mission, STS-33.

     Discovery spent about 15 weeks in the processing facility undergoing
about 22 modifications and routine testing.  One of the significant changes
made was the installation of the five new general purpose computers.

     Space Shuttle main engine locations for this flight are as follows:
engine 2026 in the No. 1 position, engine 2030 in the No. 2 position, and
engine 2029 in the No. 3 position.

     Booster stacking operations on mobile launcher platform 2 began Nov. 7
and were completed Dec. 13.  The external tank was mated to the boosters
Dec. 18 and the Orbiter Discovery was bolted to the tank on Jan. 30.

     STS-39 primary payloads were installed in Discovery's payload bay in
the OPF and at the launch pad.  Payloads installed in the OPF include the
Critical Ionization Velocity payload and the Chemical Release Observatory.
The U.S. Air Force payload 675 and the Shuttle Pallet Satellite-II were
installed at the launch pad Feb. 5.  The vehicle was rolled out to Launch
Pad 39-A on Feb. 4. A dress rehearsal launch countdown was held Feb. 7-8
at KSC.

     The launch countdown will begin about 3 days prior to the launch.
During the countdown, the orbiter's onboard fuel and oxidizer storage
tanks will be loaded and all orbiter systems will be prepared for flight.
About 9 hours before launch, the external tank will be filled with its
flight load of a half a million gallons of liquid oxygen and liquid hydrogen
propellants.  About 2 1/2 hours before liftoff, the flight crew will begin
taking their assigned seats in the crew cabin.

     KSC's recovery teams will prepare the orbiter Discovery for the return
trip to Florida following the end-of-mission landing at Edwards AFB,
Calif.  Orbiter turnaround operations at Dryden Flight Research Facility
typically take about 5 days.


SHUTTLE  ADVANCED GENERAL PURPOSE COMPUTER

     On STS-39, Discovery's avionics system will feature the first set of
five upgraded general purpose computers (GPCs), plus a spare, to fly
aboard the Shuttle.

     The updated computers have more than twice the memory and three
times the processing speed of their predecessors. Officially designated
the IBM AP-101S, built by IBM, Inc., they are half the size, about half the
weight and require less electricity than the first-generation GPCs. The
central processor unit and input/output processor, previously installed as
two separate boxes, are now a single unit.

     The new GPCs use the existing Shuttle software with only subtle
changes.  However, the increases in memory and processing speed allow
for future innovations in the Shuttle's data processing system.

     Although there is no real difference in the way the crew will operate
with the new computers, the upgrade increases the reliability and
efficiency in commanding the Shuttle systems.  The predicted "mean time
between failures" (MTBF) for the advanced GPCs is 6,000 hours.  The MTBF
for the original GPCs is 5,200 hours.

Specifications

Dimensions:    19.55" x 7.62" x 10.2"
Weight:     64 lbs
Memory capacity:    262,000 words (32-bits each)
Processing rate:     1 million instructions per second
Power requirements:    550 watts


STS-39 MISSION OVERVIEW

The STS-39 mission is comprised of two primary payloads:  Air Force
Program 675 (AFP-675) and the Strategic Defense Initiative's (SDIO)
Infrared Background Signature Survey (IBSS).

There also are two secondary payloads; Space Test Payload (STP-1) and
a Multi-Purpose Experiment Canister (MPEC).  Two mid-deck experiments,
CLOUDS-1A and RME III, are included on the STS-39 mission.  IBSS and
AFP-675 have scheduled observing time throughout the mission with a
small amount of dedicated time for both STP-1 and MPEC on the last day
of the mission.

The AFP-675 payload is sponsored by SDIO and Air Force Systems
Command's Space Systems Division (SSD).  It contains three experiments
sponsored by the Phillips Laboratory's Geophysics Directorate, by the
Naval Research Laboratory, and by the Los Alamos National Laboratory,
respectively.  The prime integration contractor for the payload is
Lockheed Missiles and Space Company, Inc.  AFP-675 is a unique
demonstration of the ability to command, control and evaluate a system of
experiments without ground commands or telemetry data.  Voice (although
not necessary) will be included on this mission for communication
between the crew and the ground to discuss the experiments.

The AFP-675 payload will remain in the payload bay during the mission,
and commanding of the experiments will be accomplished by the crew
from a panel in the aft flight deck.  The experiments will be measuring
infrared, ultraviolet, visible and X-ray emissions.  One of the important
observations for the mission is the aurora.  The launch date and time were
chosen to assure visibility of the aurora.

SDIO's IBSS payload is composed of three separate systems, the Shuttle
Pallet Satellite (SPAS-II), the Critical Ionization Velocity (CIV) system
and the Chemical Release Observation (CRO) experiment.  SDIO has program
management responsibility.  The SPAS-II was developed by
Messerschmitt-Bolkow-Blohm (MBB).  The CIV portion is managed by the
Geophysics Directorate, and the CRO portion is managed by the Western
Space Technology Center.  Mission operations are managed by SSD.

The SPAS-II structure supports a cryogenically cooled infrared sensor, an
ultraviolet multispectral sensor and low light level television cameras.
The SPAS-II will be deployed and maneuvered to observe various targets
and can be commanded by the on-board crew or by the ground.

The CRO is composed of three separate subsatellite structures that
will be deployed and will release chemicals upon ground command to be
observed by the SPAS infrared sensors.  Each subsatellite is loaded with a
different chemical.  The CIV structure is composed of four separate gas
canisters which remain attached to the orbiter and will release gas upon
command to be observed by the SPAS sensors.  Each cylinder is loaded
with a different gas; xenon, neon, carbon dioxide and nitrous oxide.

SSD sponsors the STP-1 payload which is a standard Goddard Space
Flight Center (GSFC) Hitchhiker structure supporting five experiments.
Experiments are sponsored by the Naval Research Laboratory, the Rocket
Propulsion Directorate of the Phillips Laboratory, the Geophysics
Directorate, GSFC, and SSD.

STP-1 remains in the cargo bay and is commanded from a control center
at Goddard Space Flight Center.  The UVLIM experiment will collect
airglow measurements, ALFE will evaluate advanced propellant
management systems, and SKIRT will collect infrared, visible and
ultraviolet data on Shuttle glow.  DSE will test advanced data management
concepts, and APM will collect particles to study particulate
contamination in the Shuttle bay.

MPEC is a multipurpose experiment cannister sponsored by SSD.  The
MPEC will deploy a classified experiment on the last day of the mission.

There are two mid-deck experiments on the STS-39 mission.  The
CLOUDS-1A experiment will study cloud cover, and the RME-III experiment
will measure ionizing radiation exposure in the orbiter cabin.


AIR FORCE PAYLOAD-675

Cryogenic Infrared Radiance Instrumentation for Shuttle
(CIRRIS-1A)

     The CIRRIS instrument is sponsored by the Strategic Defense Initiative
Organization (SDIO), and program responsibility is under the Phillips
Laboratory's Geophysics Directorate at Hanscom Air Force Base, Md.  The
sensor prime contractor is Utah State University with major
subcontractors Space Data Corporation, Sensor System Group and Boston
College.

     CIRRIS-1A is the highest priority experiment being flown on the AFP-
675 space vehicle.  The experiment is designed to be operated by
Discovery's crew from a command panel in the aft flight deck.

     The experiment operates in the infrared portion of the electromagnetic
spectrum (wavelength between 2.5 to 25 micro-meters).  The experiment
will obtain simultaneous spectral and spatial measurements of airglow
and auroral emissions.

     The data obtained from the mission should help answer questions
regarding the optimum atmospheric windows for detecting cold body
targets, the background radiance levels in various regions, the spatial
structure (clutter) of the background, and the variability of Earth limb
emissions during day/night airglow and auroral events.  This information
will help DOD design surveillance systems.

     There is a low light level television co-aligned on the sensor telescope
which can be used by the crew to acquire and track the auroral displays
and celestial calibration targets.

     One primary mission objective is to measure the spectral and spatial
characteristics of auroral emissions.  The pre-midnight/midnight sector
of the Northern and Southern auroral oval is expected to exhibit the most
intense infrared emissions and therefore, is of particular interest.  An
auroral watch will be maintained by a network of ground personnel to
monitor the level of auroral activity.  In the event of an intense auroral
display, this team would alert Discovery's crew of the location and
intensity of the aurora.

     Earth limb emissions will be collected covering a range of altitudes,
latitudes, day/night and geomagnetic conditions.

     To provide a radiometric calibration of the infrared sensors, certain
known celestial sources will be measured during the mission.

     Discovery will be maneuvered to provide the proper attitude for
observations and to provide the required scanning and pointing capability.
The sensor is mounted on a two-axis gimbal.

     Gravity gradient is the primary attitude for CIRRIS-1A data collection.
It is the only attitude maintainable by the orbiter without the use of the
reaction control system which produces unacceptable contaminates.

Aurora Details

    Aurora are created by solar activity.  When a solar flare, sun spot or
coronal hole occurs within a particular area of the sun's disk, an increased
number of energetic particles is directed towards the Earth.  As the solar
wind accelerates with the Earth's magnetosphere, a generator effect is
produced which accelerates electrons down the Earth's magnetic field
lines.  As these electrons impinge upon the Earth's atmosphere, oxygen and
nitrogen are excited and ionized to produce aurorae.  The aurorae emit
visible, ultraviolet, infrared and radio frequencies.  Because the electrons
precipitate down the geomagnetic field lines, aurorae are produced in an
oval shaped zone roughly centered around the magnetic pole regions of the
North and South poles.

    The shape and size of the oval is dependent on the intensity of the
solar wind.  The intensity of the aurora within the oval is variable.  The
objective of the mission is to observe an extremely active aurora.  The
two primary indicators for predicting when an active aurora might appear
are solar activity and geomagnetic disturbance.  These events will both be
monitored during the mission.

    A ground station magnetometer network and Defense Meteorological
Satellite Program (DMSP) satellite coverage will be utilized to detect
whether an active aurora is in progress.  This network is located in the
Northern Hemisphere and will collect simultaneous scientific
measurements as well as provide a near realtime detection capability.
The southern aurora is a mirror image of the northern aurora.  If there is
an active northern aurora then the southern aurora also will be active.

FAR Ultraviolet Cameras (FAR UV)

    The FAR Ultraviolet Cameras experiment is sponsored by the Naval
Research Laboratory.  The hardware is a part of the AFP-675 payload.  The
instrumentation consists of two electrographic Schmidt cameras.  A
course-pointing two axis gimbal platform and a low light level TV camera
for finding the objects and guiding the instrument.  The instrument also
has a stabilization system for long exposures on celestial objects.  The
instrument weighs approximately 550 pounds and the dimensions are
approximately 60" x 32" x 20".

    The cameras will record naturally-occurring and man-made emission
phenomena in near-Earth space in the 1050-1600 angstroms (A) and 1230-
2000A wavelength ranges.  The phenomena of interest include day and
night airglow, diffuse aurorae and the orbiter environment.  Of particular
interest is the orbiter thruster and surface glow effects.

    The experiment also will make observations of interplanetary and
interstellar media, stars, extragalactic objects, effects of chemical
deposition and atmospheric density measurements by stellar occultation.

    Each camera has a film transport loaded with 150 feet of film yielding
up to 900 frames of data.  The gimbaled platform allows pointing of FAR
UV to be somewhat independent of orbiter attitude.  The outer gimbal can
travel between +/- 80 degrees and the inner gimbal can travel between
+/- 22 degrees.

    The experiment is commanded by a crew member who views the TV
monitor to determine where the camera is pointing as he moves the
camera into position.

    The sun sensor is an array of silicon solar cells which outputs a
voltage of 5 volts in full sunlight.  As the output from the sun sensor in
excess of 3 volts indicates the sun is shining into the payload bay and
hence, the FAR UV high voltage must be turned off and the doors closed.

    The terrestrial atmospheric observations include northern and southern
diffuse aurora, snapshot views of discrete aurora, night airglow with
attention to the tropical arcs and twilight airglow.  Stellar occultation
observations will occur concurrent with airglow observations.  Any unique
phenomena such as meteor showers should be noted if they occur in
airglow or aurora viewing periods.

    The celestial target observations include the diffuse nebulae, diffuse
galactic background, star fields at high and low galactic latitudes, and
also nearby external galaxies.

    The primary Shuttle environment events are the primary RCS
and OMS thruster firings (in daylight and dark) and Shuttle
glow.  Secondary interests are Shuttle contamination effects such
as fuel cell purges, flash evaporator events and water dumps.


Uniformly Redundant Array (URA)

    The URA experiment is sponsored by the Department of Energy and Los
Alamos National Laboratory.

    The URA is designed to conduct studies of astrophysical sources of
X-ray radiation.  The instrument, a part of the AFP-675 payload, is an
assembly consisting of a detector, a 35mm camera and an electronics
package.  The aperture plate of the detector contains over 26,000
hexagonal holes to collect the X-ray photons.  Objects will be selected to
test the capability of the URA to image point sources, complex collections
of point sources and extended objects.  The instrument will be operated
both in a staring and slow scan mode.  The URA experiment will be
controlled by a mission specialist via the CMP (Command and Monitor
Panel).

    The URA must not only detect X-rays of interest but must also suppress
detection of particles that are present as background.  The backgrounds of
concern are mainly cosmic rays (relativistic protons and alpha particles)
and charged particles (electrons above a 50 keV energy) trapped by the
Earth's magnetic field.  Because such particles penetrate the detector
walls or window, the backgrounds are rejected by anti-coincidence,
second moment and rise time discrimination techniques.

    The extended charge distribution from an energetic charged particle, as
opposed to an X-ray photon, produces a slower amplifier pulse because it
is collected over a finite period of time.  Rise time discrimination is thus
an independent means of background rejection.

    Despite the background rejection provisions, URA will not operate
usefully at high levels of background.  Cosmic ray background is less at
low latitude and altitude because of the shielding effect of the Earth's
magnetic field.  X-ray experiments are not successful in high background
regions, which are found at high altitude, and high magnetic latitude, and
in the South Atlantic Anomaly.  Low altitude, low latitude will increase
the success of the URA observations.


Horizon Ultraviolet Program (HUP)

    The HUP is an AF Geophysics Laboratory experiment to demonstrate a
capability to measure the spatial and spectral characteristics of the
Earth's horizon as observed in the ultraviolet wavelength region and to
analyze Shuttle contamination.

    The instrument weighs less than 40 pounds and is approximately 15" x
21" x 9".  The ultraviolet instrument is smaller and does not require
cooling like the infrared instruments.  The experiment runs continuously
during the mission.  The line of sight of the instrument is in the -Z
direction, vertically out of the Shuttle bay.

    The telescope assembly is pivoted about an axis which enables the field
of view to vary from local horizontal to a few degrees below the hard
Earth horizon.  Data will be collected using continuous angle scans at a
series of wavelengths in the range of 1100-1900 A, continuous
wavelength scans in a fixed direction and a fixed wavelength fixed
direction.

    To prevent damage from the sun, a solar protection sensor closes the
spectrometer shutter when the sun is within 3 degrees of the line of
sight.  The spectrometer then automatically starts a calibration cycle and
resumes data taking when the sun is no longer in the field of view.

    The HUP instrument will measure the atmospheric radiance as a
function of tangent altitude.  The horizon limb profiles are necessary to
develop attitude sensors for spacecraft and to obtain backgrounds for
above the horizon missile detection techniques.  The radiance is due to
solar scattering, airglow and auroral excitation.  Contamination of the
orbiter environment also will be measured.

    The experiment should yield data radiation backgrounds from the
airglow and aurora Earth limb measurements, and information on
variability and clutter in the atmosphere.


Quadrupole Ion-Neutral Mass Spectrometer (QINMS)

     The QINMS experiment is sponsored by the Phillips Laboratory's
Geophysics Directorate.  The mass spectrometer instrument weighs
approximately 28 pounds.  The hardware, part of the AFP-675 payload, is
mounted to the ESS and does not gimbal.

     The primary role of QINMS is to support CIRRIS by measuring the
amount and nature of orbiter bay contamination, particularly water
concentration.  CIRRIS will not be operated until contamination levels are
low.

     QINMS will collect data continuously throughout the flight with
operations controlled by a Mission Specialist via the CMP.

     Data also will be collected while passing through the auroral zone and
polar latitude.  Levels of hydrogen, oxygen, water vapor and other gases
will be measured.



INFRARED BACKGROUND SIGNATURE SURVEY (IBSS)

IBSS Overview

    Infrared Background Signature Survey is a Strategic Defense Initiative
Organization sponsored program for the purpose of obtaining scientific
data for use in the development of ballistic missile defense sensor
systems.

    IBSS is composed of three separate elements:  the Shuttle Pallet
Satellite II  (SPAS -II), the Critical Ionization Velocity (CIV) package, and
the Chemical Release Observation (CRO) experiment.  In addition to
sponsoring the program, SDIO also manages the overall program.
Supporting SDIO in program management are several systems engineering
and technical analysis firms, including: Stears, Kiya and Wright of
Arlington, Va; Orbital Systems Limited of Lanham, Md; Nichols Research
Corp. of Vienna, Va., and Hernandez Engineering Inc. of Houston, Tex.  The
SPAS-II hardware is developed and manufactured by Messerschmitt-
Bolkow-Blohm GmbH of Munich, Germany.  Mounted on the SPAS-II are two
sensor systems:  an infrared spectrometer/radiometer built by Kayser-
Threde of Germany housed in cryostat (cryogenically cooled instrument
chamber) built by Linde of Germany and a multispectral Arizona
Imager/Spectrograph (AIS) built by the University of Arizona at Tucson,
Ariz.


Shuttle Pallet Satellite II (SPAS-II)

     The SPAS-II element incorporates a liquid helium cooled infrared
sensor, the Arizona Imager/Spectrograph (AIS) multispectral sensor, two
low light level television cameras and various support subsystems on a
modular graphite-epoxy structure.  SPAS-II will be deployed from the
orbiter using the Remote Manipulator System (RMS) and will maneuver at
ranges of up to 20 km from the orbiter to gather spectral and spatial data
during several experiments.


Chemical Release Observation (CRO)

     The Chemical Release Observation (CRO) portion of the Infrared
Background Signature Survey (IBSS) mission is an experiment designed to
collect infrared, visible and ultraviolet time-resolved radiometric data
associated with the release of liquid rocket propellants in near Earth
orbit.  The experiment is composed of three separate subsatellites
containing chemicals and their launchers.

     Since the three chemical releases will produce short-lived clouds of
vapor and frozen particles in orbit near the Shuttle, it is possible that a
faint glow of visible light may occur due to the interaction of the vapor
cloud with oxygen atoms in the upper atmosphere.  It is not expected,
however, that the vapor glow from any of the releases will be bright
enough to be detected by the unaided eye on the ground.  The chances of
observers near Vandenberg seeing the first and only nighttime scheduled
release experiment are very remote.

     The cloud of frozen particles, however, can scatter sunlight producing
visible light with much greater intensity.  The sunlight scattered from the
particle cloud will not be as intense as the daytime sky, however, so it is
unlikely that either the second or third release can be viewed from the
ground for the scheduled launch and mission time line.  If the launch is
delayed a couple of hours, however, the first scheduled release could
occur under pre-dawn twilight conditions on the west coast.  This
situation would provide optimal viewing conditions as the release would
occur in sunlight while a west coast observer would be in darkness.  Under
these conditions, the release would initially appear as a disk of white
light approximately the size of the full moon (though somewhat dimmer).
The cloud will continue to grow and gradually dim after the flow of liquid
ends.  The remnants of the bright cloud will only persist for a few
minutes.

CRO Management

    The CRO element is managed by the Air Force Space Technology Center
from their West Coast (Los Angeles) office.  The CRO subsatellites and
launcher mechanisms are designed and manufactured by Defense Systems
Inc,. of McLean, Va, while the launcher cylinders and support beams are
provided by NASA/Goddard Space Flight Center at Greenbelt, Md.
Subsatellite ground control and telemetry is provided by USAF 6595th
Test & Evaluation Group and the Western Test Range at Vandenberg AFB,
Calif., supported by Federal Electric Corp.  Aircraft sensor platform
operations for collecting CRO data in the VAFB area are provided by the
HALO aircraft, operated by Phillips Laboratory's Weapons Directorate and
4950th Test Group at Kirtland AFB, N.M., supported by BDM Corp. of
Albuquerque, N.M.

    IBSS mission integration, launch site operations and payload flight
operations are managed by the Space Systems Division, Air Force Systems
Command, supported by The Aerospace Corporation and Rockwell
International Space Division.


Critical Ionization Velocity (CIV)

     The Critical Ionization Velocity experiment will investigate the
interaction of neutral gases with the ambient weakly-magnetized plasma.

    The CIV element includes four compressed gas canisters (xenon, neon,
carbon dioxide and nitrous oxide) which release plumes of the gas out of
the orbiter bay upon crew command.  The plumes are then observed by the
SPAS-II sensors at different orientations to the orbiter's direction of
travel and the local geomagnetic lines of force.  The CIV hardware weighs
about 500 lbs.

          Kinetic energy of the gas will exceed its ionization potential due to
its relative velocity with the ambient plasma.  The resulting plasma
instability is expected to enhance ionization.  Charge exchange between
the gases released and ambient ions (mainly oxygen) is expected to
produce other ions.

     Both mechanisms can lead to the release of radiation.  Therefore,
radiation in the infrared, visible and ultraviolet bands will be collected by
the sensors from the deployed SPAS-II.  The CIV experiment also has a
data acquisition package, its radiometers will measure both visible and
ultraviolet radiation from the payload bay.  The CIV experiment, in the
payload bay, has a Langmuir probe which will measure the ambient
electron density and temperature.

     Four different gases have been selected, and the release mechanism
was designed such that the critical ionization velocity should be reached
for three of the four gases when they are released in the RAM direction.
Because the orientation and strength of the local magnetic field is
expected to affect the intensity of the ionization phenomenon, the gas
releases will be observed both when the local magnetic field is
approximately parallel to RAM and when it is perpendicular to RAM.  The
effect of ambient electron density on the phenomenon will be observed by
repeating the observations in both the daylight and darkness.

     Four observations are planned with the SPAS-II deployed at a location
near the Orbiter.  Lighting and magnetic field orientation will be varied to
produce four unique observations.

CIV Management

    The CIV element is managed by Geophysics Laboratory/Space Physics
Division at Hanscom AFB, Mass.  Supporting contractors include:

Physical Sciences Inc., Andover, Mass.    Gas Release System & System
Integration

Northeastern University, Boston, Mass.    Payload Support System
Manufacturer

Wentworth Inst. of Tech, Boston, Mass.    General Mechanical Mfg.

John Hopkins University, Baltimore, Md.    Pressure Gauge Subsystems

Research Science Inc., Washington, D.C.    Radiometer Subsystem

University of Iowa, Iowa City, Iowa    Langmuir Probe


IBSS Objectives

    The Infrared Background Signature Survey is a Strategic Defense
Initiative Organization sponsored program for the purpose of obtaining
scientific data for use in the development of ballistic missile defense
sensor systems.  The IBSS mission will involve the collection of infrared,
ultraviolet and visible measurements of natural and induced geophysical
phenomena.

    Using the SPAS-II sensors at various ranges from the orbiter, spectral,
spatial and temporal radiometric observations will be made of the exhaust
plumes when the orbiter's orbital maneuvering systems (OMS) fires and
creates replications of ICBM booster and midcourse engine firings.
Interaction of the outer plume regions with the atmosphere will be
characterized, as well as the region near the exit nozzle.  The single
engine OMS firings for these observations represent the first time such
firings have been attempted in space by the orbiter.

    The Chemical Release Observations (CRO) will be carried out by
deploying each of the three CRO subsatellites from the cargo bay at about
3.5 feet per second, allowing them to separate until the subsatellite
trails the SPAS-II by 50 to 200 km in orbit.  Release will be timed such
that, at that range, the CRO subsatellite will pass over Vandenberg AFB
(VAFB) in Southern California.  A signal from VAFB will cause the
subsatellite to send telemetry measurements of its health and status.
Then another signal (moments later on the same pass or on the next pass)
will cause the subsatellite to expel a stream of chemical which will
quickly vaporize into a cloud, while being observed from SPAS-II sensors,
ground sensors at VAFB and airborne sensors on the ARGUS aircraft,
simultaneously.  Spectral information will permit characterization of the
chemical interactions with the atmosphere and solar energy, as well as
determine the aerosol distribution of the chemicals with respect to
particle size and expansion rate.  The chemicals released are 15 pounds of
nitrogen tetroxide, 52 pounds of unsymmetrical dimethyl hydrazine and 60
pounds of monomethyl hydrazine, released in that order.  These
observations will assist the SDIO in characterizing the signature from
liquid fuel clouds escaping from damaged ICBM boosters.

    The subsatellites will be tracked and commanded by personnel from the
USAF 659th Test and Evaluation Group, supported by Federal Electric
Corporation, using assets of the Western Test Range at VAFB.  Aircraft
sensor platform operations for collecting CRO data in the VAFB area are
provided by the Strategic Defense Initiative Organization's High Altitude
Observatory (HALO) aircraft operated by Aeromet Inc., Tulsa, Okla., with
instrument support by Automated Sciences Group, Inc., Huntsville, Ala. for
the U.S. Army Strategic Defense Command.

    The CIV experiment is intended to provide on-orbit spectral data to
examine a theory which holds that many gases (including rocket
combustion products) can be ionized if they are passed through a
magnetized plasma and their kinetic energy is caused to exceed their
ionization potential.  Ions so created would then flow along the local
magnetic lines of force and generate emissions which can be detected by
space-borne sensors, thereby permitting tracking of the vehicle releasing
the gases.  In the CIV experiment, gases under pressure will be ejected at
different angles to the orbiter velocity (such that collisions with the thin
orbital atmosphere will enhance ionization) and to the local magnetic
field lines.  The SPAS-II will be "parked" about 2 km away, taking spectral
data on the gas plumes, and other instruments in the CIV package
(radiometers and a Langmuir probe) will take data as well.  The gases used
will be xenon (low ionization potential - should definitely ionize), neon
(very high potential -  should not ionize), carbon dioxide and nitric oxide
(typical exhaust products form hypergolic fueled rockets).

    SPAS-II also will be used to take spatial and spectral measurements of
the Earth's atmosphere as viewed at the horizon (called the "Earth's limb"
at various altitudes above the surface.  Such data is necessary to
establish the background against which an approaching ICBM would be
viewed by a sensor system as the ICBM came over the horizon.  For the
same reason, measurements will be taken of the Earth's surface under
many conditions of light and darkness, hard earth and water, clouds and
cloudlessness.  Yet another geophysical type of data which will be
measured for the same reasons will be auroral emissions (Northern and
Southern Lights) as available.

    Finally, to characterize the effects of contaminating materials coming
from a sensor platform itself, the environment around the orbiter will be
measured by the SPAS-II "parked" nearby.  These measurements will be
taken with the orbiter in a "quiet" state, as well as during fuel cell
purges, water dumps, thruster firings and other contaminating events.
Measurements also will be taken of the "orbiter glow" phenomenon.  This
phenomenon occurs where the rarified atmosphere strikes orbiter
surfaces, especially the tail, causing visible and infrared radiance.
Theories on the mechanism, including reactions with atomic oxygen,
chemiluminescence and gas phase collisions, will be investigated and
hopefully better understood.  This phenomenon also may occur on orbiting
SDI sensor platforms or target ICBM vehicles.

IBSS Plume Observations

    The objective of the plume experiment is to gather data on the optical
signature of rocket plumes.  The experiment should permit the
characterization of the plumes through spectral, spatial and temporal
radiometric measurements in the infrared, ultraviolet and visible bands.

    Observations will be made of the plumes generated by the orbiter
engine firings.  The outer regions of the plumes will be examined to
determine the interaction with the atmosphere.  Observations also will be
made to measure the radiative properties near the exit nozzle.

Earth Background Experiments

    The Earth Background experiments will use the IBSS Infrared Sensor
and the AIS sensors to characterize the Earth background from the Earth's
limb to the hard earth and in areas around the solar specular point.
Measurements will consist of Earth's limb and Earth scan observations
with SPAS deployed, auroral observations with SPAS on the RMS, and AIS
Earth's limb observations from in the bay.

    The Earth's limb observations will include day, night and terminator
views.  The Earth scan observations are directed at the Earth rather than
the limb.  These include observations of spatial clutter in CO2 bands,
observations of areas around the solar specular point, the terminator and
limb to Earth scans.


Orbiter Environment Experiment

    The Orbiter Environment Experiment is an experiment to be performed
by the IBSS payload.  The orbiter environment observation will use the
IBSS infrared sensor and the AIS sensors to characterize the contaminant
environment in and around the orbiter payload bay.  Observations will be in
the infrared, visible, and ultraviolet regions of the spectrum.
Observations also will be made of the orbiter glow phenomenon.

    During orbital operations, water dumps are made and thrusters are
fired.  Gases are released when materials are exposed to the vacuum
environment of space.  This experiment will observe these and other
contaminants in the payload bay.

    A diffuse near-field glow phenomenon has been observed above
spacecraft surfaces subjected to the impact of atmospheric species as
the spacecraft travels through the low-Earth orbital atmosphere.  It is
thought that this phenomenon results from some type of interaction
between the ambient atmosphere and the spacecraft surface.  Sufficient
data does not exist to fully understand the process.  A number of
mechanisms have been proposed which could give rise to the glow.  These
include: (1) gas phase collisions, (2) surface-aided chemiluminescence
reactions with adsorbates on orbiter surfaces, and (3) surface reactions
with the atomic oxygen environment leading to material loss or
compositional changes.

    The spectrum of the glow is relatively diffuse and based primarily in
the red-infrared region.  The glow intensity is dependent upon the surface
orientation to the velocity vector.  The glow intensity seems to vary as a
function of the atomic oxygen density.  The glow intensity seems to vary
depending upon the type of material.

IBSS Participants

Program Management

Strategic Defense Initiative Organization.
Washington, D.C.

Integration of Payload and Operations with Shuttle

HQ Space Systems Division
Los Angeles Air Force Base, Calif.

The Aerospace Corporation
Los Angeles, Calif.

Federal Electric Corporation
Vandenberg Air Force Base, Calif.

Rockwell International
Downey, Calif.

6595th TEG/DTR and Western Test Range
Vandenberg Air Force Base, Calif.

Develop Payload

Strategic Defense Initiative Organization
Washington, D.C.

Messerschmidt-Bolkow-Blohm
Germany

Defense Systems, Inc.
McLean, Va.

Physical Sciences, Inc.
Andover, Mass.

Orbital Systems, Ltd.
Lanham, Md.

SKW Corporation
Arlington, Va.

Nichol Research Corp.
McLean, Va.

Geophysics Directorate of Phillips Laboratory
Hanscom Air Force Base, Mass.

Phillips Laboratory's West Coast Office
Los Angeles Air Force Base, Calif.

University of Arizona
Tucson, Ariz.

Training

Hernandez Engineering Corp.
Houston, Texas

STS-39 SPAS/IBSS RENDEZVOUS & TRACKING OPERATIONS

     Rendezvous and tracking maneuvers in support of IBSS operations
during STS-39 present many significant challenges to Space Shuttle
mission operations.  More than 60 orbiter maneuvers are planned to
support the various phases of SPAS/IBSS rendezvous, including IBSS
calibrations, deployment, separation, far-field observations, near-field
observations, CRO subsatellite deployments and observations, and SPAS
retrieval and berthing.

Separation to Far-field

     Following the deployment of the SPAS/IBSS imaging platform, the
crew will perform an acceleration, or posigrade burn, firing Discovery's
reaction control system (RCS) thrusters to raise Discovery's orbit about 1
statute mile above the SPAS. The effect of this maneuver will drift
Discovery to a point about 6 1/2 statute miles behind the SPAS, the
required distance for far-field observations. Arriving at that point one
orbit after the separation burn, the crew will fire the RCS to brake
Discovery and place it again in the same orbit with the SPAS.  Deployment
and separation are scheduled to occur while both crew shifts are awake.

Far-field Operations

     Following a crew shift handover at the far-field position, the Red Team
will maneuver Discovery to point its nose north, with the payload bay
pointed in the direction of orbital travel -- toward SPAS, 6 1/2 miles
ahead.

OMS Plume Observation

     From this position, the crew will remotely command the SPAS/IBSS to
point its imaging systems at Discovery for the first plume observation.
Once the experiments are properly trained on Discovery, one orbital
maneuvering system (OMS) engine will be fired for 20 seconds. The result
of the burn will be to propel Discovery north, off of its previous orbital
groundtrack, without changing the spacecraft's altitude. A burn with this
lateral effect is known as "out-of-plane." Immediately following the burn,
the crew will perform a "fast-flip" yaw maneuver, using RCS jets to turn
Discovery's nose around 180 degrees to the south. A single-engine OMS
braking burn then will be performed to stop Discovery's travel at a point
less than a mile north of its previous groundtrack. Using RCS jets, the
crew will return Discovery to its starting position, on its original
groundtrack behind the SPAS. As Discovery drifts back to the starting
point, a "fast-flip" reversal will turn the spacecrafts nose back to the
north. Throughout this sequence, the crew will point the SPAS/IBSS by
remote control to observe each burn.

     Far-field observations will continue following the Blue Team's sleep
shift.  Due to the complexities involved, all OMS burns will be conducted
only when both crew shifts are awake and able to participate.

     Discovery will remain at the far-field position during the Blue Team's
sleep, and the Red Team will continue SPAS/IBSS operations, conducting
Earth's limb observations by remote control.

     Following the Blue Team's sleep shift, while both teams are awake, the
same sequence of maneuvers will be repeated twice in support of two
additional plume observations.

PRCS Plume Observation

     The final IBSS objective at the far-field position will be an
observation of Discovery's primary RCS jets firing. In the same attitude
used for OMS plume observations, the crew again will align SPAS/IBSS to
train it's optics on the vehicle and then ignite one of the primary
thrusters for 25 seconds.

Far-field CRO Release

     After the far-field plume observations have been completed and while
the Red Team sleeps, the Blue Team will eject the first CRO canister from
the payload bay at a rate of 3.5 feet per second (fps) to an altitude just
above that of Discovery and SPAS.

     Just after it is ejected from the payload bay, antennae on the canister
will deploy, providing a remote command link to investigators at
Vandenberg Air Force Base (VAFB). The canister will drift during several
orbits to the desired distance for IBSS imaging, where VAFB investigators
will remotely command the canister to release its gaseous contents. CRO
gas releases and observations will begin after near-field operations have
been completed.

Transition to Near-field

     To reach the near-field observations position, the crew will perform a
slowing, or retrograde, RCS burn to slightly lower Discovery's orbit. The
effect of the burn, over the next orbit, will move Discovery to within 1 5
statute miles behind the SPAS. As Discovery approaches that point,
another RCS burn will brake the orbiter, placing it directly behind SPAS on
the same orbital path, less than 1.5 miles behind.

Near-field Operations: OMS Plume Observations

     At the near-field position with both crew teams awake, Discovery
again will be maneuvered to the "nose-north" start attitude which was
used for far-field observations. The same out-of-plane OMS burn sequence
will be repeated twice for near-field plume observations. The crew will
continue to point the SPAS/IBSS imaging systems by remote control to set
up and record each observation.

Near-field Operations: CIV Observations

     Before leaving the near-field position, the crew will train SPAS/IBSS
imaging systems on Discovery's payload bay to observe and document a
sequence of gas releases from CIV canisters mounted in the bay.

CRO Observations

     Following completion of near-field operations while the Blue Team
sleeps, the Red Team will conduct a series of maneuvers to set up IBSS
imaging and tracking of the CRO gas-release canisters ejected from
Discovery's payload bay.

     A combination burn, both posigrade and out-of-plane, will be made to
further separate Discovery from the SPAS and avoid obscuring it's view of
the already deployed canister. The posigrade component of the RCS burn
will provide for a slow separation from the SPAS, over 7.5 hours and five
orbits, to a distance of 9 miles behind SPAS for the start of retrieval
operations. The lateral component will move Discovery off of the direct
track between SPAS and the CRO canister so it will not block the line of
sight of the SPAS imaging experiments.

     During this five-orbit separation phase, the crew will remotely
command the SPAS/IBSS to track and observe the first CRO canister as
VAFB ground controllers remotely command the gas release.

     Following completion of the first CRO observation, the crew will
perform an RCS burn to move Discovery back into alignment with the
flight path of the SPAS, but continuing to separate.  The crew will then
eject a second canister and command the SPAS/IBSS to track and observe
another ground-commanded gas release.

SPAS/IBSS Retrieval

     After separating to more than 9 statute miles and with both crew
shifts awake again, a retrograde burn will slightly lower Discovery's orbit
to overtake the SPAS/IBSS. Several course adjustment burns may be
conducted as Discovery nears it's target, in order to arrive directly in
front of the SPAS on the same flight path. The crew then will manually
maneuver Discovery to within range of the remote manipulator system for
capture.



STP-1

Overview

     The STP-1 payload is sponsored by the USAF Space Systems Division.
It is a complex secondary payload with experiments that are monitored
and controlled by the Hitchhiker avionics.  The Hitchhiker equipment for
the payload consists of the support structure, the avionics and the
experiment containers.  This equipment is managed by NASA's Goddard
Space Flight Center (GSFC).  GSFC also provides a carrier, power and
communications to the various experiments aboard.  The experiments are
contained in Get Away Special (GAS) canisters which are already certified
for space.  GSFC also completes the integration and testing for the
experiments.

     STP-1 is composed of five separate experiments:  the Ultraviolet Limb
Imaging (UVLIM) experiment, the Advanced Liquid Feed Experiment (ALFE),
the Spacecraft Kinetic Infrared Test (SKIRT), the Data System Experiment
(DSE) and the Ascent Particle Monitor (APM).

     STP-1 is considered a secondary payload which means it may not
interfere with the two primary payloads.  Only a short portion of
dedicated time is allocated to the payload, and at other times the
experiments are conducted on a non-interference basis.

     After the Shuttle is in orbit and the payload bay doors are open, the
crew will power on the payload.  The payload then will be commanded from
the ground by a control center located at GSFC.  The control center will be
operated 24 hours a day to coincide with the 24-hour operations of the
Shuttle crew.  The control centers for the two primary payloads are
located at NASA's Johnson Space Center.  There will be constant
coordination between the control centers during the flight to execute the
mission and to replan should the need arise.

Hitchhiker Project

     The Hitchhiker Project, operated by Goddard Space Flight Center (GSFC)
in Greenbelt, Md., provides for accommodation of small payloads in the
Shuttle payload bay. The Hitchhiker payload for STS-39 is called Space
Test Payload-1 (STP-1) and consists of a Hitchhiker cross-bay carrier
with five experiments. The carrier hardware includes the cross-bay
structure, carrier avionics unit, mounting plates, canisters and a
motorized canister door. STP-1 is sponsored by the U.S. Air Force Space
Systems Division.

     Hitchhiker was designed and built at Goddard and will be operated from
a control center at GSFC during the mission. The five experiments on STP-
1 are:

     The Hitchhiker Project is operated by GSFC for the NASA Office of
Space Flight. Payloads are provided thermally controlled mounting
surfaces or sealed pressurizable canisters, orbiter power, command and
data interfaces.

     The last Hitchhiker mission was in 1986, and the next after STS-39
will be in August 1992, followed by another in October of that year.

     GSFC Project Manager and Deputy Project Manager are Theodore
Goldsmith and Steven Dunker. Chuck Chidekel, also of Goddard, is
Integration Manager. The USAF STP-1 Program Manager is Capt. Hau Tran,
and NASA Headquarters Program Manager is Edward James.

Ultraviolet Limb Imaging (UVLIM) Experiment

     The objective of the Ultraviolet Limb Imaging experiment, sponsored by
the Naval Research Laboratory in Washington D .C., is to measure the
vertical and geographic distribution of the ultraviolet airglow in the
wavelength region from 575 angstroms to 1900 angstroms.

     These measurements will be used to determine the daily and seasonal
variation of the composition of the ionosphere and neutral atmosphere
between the altitudes of 100 and 500 kilometers.  The UVLIM experiment
requires a 5 cubic foot canister with a motorized door and a mounting
plate to house a 35mm aspect camera.  The camera will be aligned with
the experiment aperture plate to provide simultaneous data which will be
correlated with post flight data in determining point location.

     The experiment uses an extreme ultraviolet imaging spectrometer with
a two dimensional detector to make images of the horizon from the
airglow emissions which characterize the composition of the ionosphere.
The far ultraviolet spectrometer measures emissions indicative of the
temperature and composition of the neutral atmosphere.


Advanced Liquid Feed Experiment (ALFE)

     The next generation of spacecraft and space tugs may be one step
closer to autonomous operation and longer life due to the technology to be
demonstrated in space by the Advanced Liquid Feed Experiment (ALFE).
The space flight experiment is designed to evaluate the performance of
key components of an advanced spacecraft propulsion system designed and
built by the McDonnell Douglas Astronautics Company (MDAC) under
contract to the Phillips Laboratory's Astronautics Directorate.

     ALFE will provide the first space flight demonstration of an electronic
pressure regulator and a series of ultrasonic propellant level and flow
sensing systems.  These components will provide the capability to
remotely and electronically control the pressurization schedule of
spacecraft propellant tanks to accurately gauge the available on-board
propellants and to reliably track the propellant usage throughout the
mission.  The experiment also will demonstrate the capability to integrate
all storable propellant on-board the spacecraft by transferring attitude
control system propellants into the main engine tanks and vice versa.

     The experiment is designed to use commercially available components
to build two hardware modules weighing approximately 250 pounds each.
The first module is an electronic package which will function as the
remote test conductor aboard the Shuttle.  It contains an on-board
computer and associated electronics necessary for performing the
experiment and recording the data.  The module will provide the command
and control for the experiment.  It also will provide the communication
link to transfer experiment telemetry and video signals to the ground
based operator located at NASA's Goddard Space Flight Center (GSFC).

     The second module is the fluid system module.  It contains two test
tanks, an electronic pressure regulator, an ultrasonic liquid gauging
system and the associated instrumentation, pumps and valves.  The items
of interest are the test tanks, the electronic pressure regulator and the
ultrasonic liquid gauging system.

     The test tanks are made of Plexiglas and are scaled to represent a 1/4
scale of the actual system.  Internally, each of these tanks is fitted with
a liquid acquisition device for liquid positioning in the low gravity
environment of space, and a screen device to preclude the ingestion of gas
bubble into the lines.  During the experiment, various quantities of fluid
will be transferred between two tanks to simulate a hypothetical resupply
scenario in space.

     The electronic pressure regulator, built by Parker Hannifin of Irvine,
Calif., will control the pressure of the test tank during flight.  It has a
unique capability to provide a smooth ramp-up of tank pressure when
commanded in contrast with the typical burst disk system.  The regulator
also has the capability to control the downstream pressure to different
pressure settings.  This will enable better management of the limited
quantity of the precious pressurized gas carried by the spacecraft.

     The ultrasonic liquid gauging system, supplied by Panametrics in
Waltham, Mass., will provide an advanced approach to measure and track
the liquid propellant usage.  The system consists of a group of six
ultrasonic point sensors and an ultrasonic flow cell.  The point sensors,
using the pulse-echo effect, measure the time delays for the ultrasonic
pulses and their echoes to transit through the fluid to the gas-liquid
interface.  From these time measurements, the amount of the liquid
contained within the tank can be calculated.  Using a similar approach, the
ultrasonic flow cell measures the time delay between two simultaneous
ultrasonic pulses along a fluid line to calculate the propellant flow.

     When flown, the ALFE on-board computer will accept commands from
the ground based operator located at NASA's GSFC and will configure the
payload for the desired test sequence.  An internal wide angle television
camera will record the fluid settling characteristics under various
acceleration loads.  Experiment data will be both stored on-board in the
electronic module and transmitted to the ground based operator.  The
results will be used in further updating the design of the advanced
spacecraft feed system.

Spacecraft Kinetic Infrared Test (SKIRT)

     The Spacecraft Kinetic Infrared Test (SKIRT), sponsored by Phillips
Laboratory's Geophysics Directorate, consists of two separate and
independent components.

     The Gaseous Luminosity of Optical Surface (GLOS) consists of infrared,
visible and ultraviolet radiometers combined into one package weighing
50 pounds.  The Circular Variable Filter (CVF) is a solid nitrogen cooled
infrared spectrometer/radiometer mounted in a sealed canister with an
aperture in the top plate.  A motor driven cover is commanded open and
closed on-orbit to cover the aperture as needed.  A "glow plate" attached
to the top plate provides a surface for impingement of the residual
atmosphere to produce the glow which is then observed by the
spectrometer.  CVF weighs approximately 150 pounds with cryogen.

     The experiment objective is to obtain infrared spectral measurements
of the Shuttle glow at resolutions and sensitivity that will allow
identification of the chemical species associated with this phenomenon.
Since the Shuttle glow effect is thought to be caused by the impact of
atomic oxygen on the orbiter surfaces, it is only necessary that surfaces
near the SKIRT field-of-view be exposed to ram (direction) at various
times during the mission.


Ascent Particle Monitor (APM)

     The Ascent Particle Monitor (APM), sponsored by USAF Space Systems
Division's Operating Location detachment in Houston Texas, consists of a
small box with a fixed door and a movable door mounted in a clamshell
arrangement atop an aluminum housing.  Each door contains six coupon
holders into which selected passive witness samples are installed.  The
door is closed preflight to protect the coupons from the environment.  It is
opened after ground operations are completed and the payload bay doors
are about to be closed in preparation for launch.  A motor/gearbox
assembly, two battery packs, launch detection circuitry and door opening
circuitry are contained within the aluminum housing of the unit.  The
electric motor is used to open and close the door so that particles can be
collected at specific times during Shuttle ascent.  An internal timing
circuit set prior to installation of the APM into the orbiter payload bay to
control the door movement.  The timer circuit is acoustically actuated by
orbiter main engine start.

     The concept of the APM experiment evolved as a direct response to
concerns by the spacecraft community about the fallout of particles in the
Shuttle orbiter payload bay during the ascent portion of the missions.
Particulate contaminants on Shuttle bay surfaces and on surfaces of
payloads in the cargo bay may be released during launch and ascent by
vibroacoustic, gravitational and aerodynamic forces.  These particles can
be deposited on surfaces from which they were released or on other
surfaces depending on location acceleration and velocity vectors with
respect to such surfaces.

     Many analytical models of particle redistribution have been made using
assumed ascent forces during launch, but most models are based on
uniform redistribution of particles.  Insufficient experiment data exist on
particle fallout and deposition during Shuttle ascent to verify current
models.  The understanding of particle redistribution on surfaces and
releases of particles into the field of view of instruments incorporating
critical sensors is important in view of the influence the particles may
have on the properties of the surfaces on which they are deposited and on
the optical degradation of the environment into which they may escape.
Some of the effects of particles on surfaces and in the environment are
physical obscuration of the surface, scattering of radiation which changes
the transmitting or reflecting properties, increased diffuse reflection of
the surface, and emission of radiation by the particles which may be
detrimental to certain sensors.

     The first APM flew on the STS-28 mission and the flight coupons were
analyzed in the Materials Science Laboratory of the Aerospace Corporation
in Los Angeles, Calif.  Various analytical techniques were used to evaluate
the contaminants, including optical and scanning electron microscopy,
infrared spectroscopy and energy dispersive X-ray spectroscopy.  The
coupons also were examined at NASA's Goddard Space Flight Center at
Greenbelt, Md., using bidirectional reflectance distribution function
scatter measurements.  The APM also flew on STS-31 (Hubble Space
Telescope), and is manifested on STS-37 (Gamma Ray Observatory
payload).


Data System Experiment (DSE)

     The Data System Experiment (DSE), sponsored by NASA's Goddard Space
Flight Center in Greenbelt, Md., consists of a MILVAX computer, Erasable
Optical Disk, and associated simulators and interfaces.  The simulators
would generate data to be used to exercise the computer and the optical
disk.

     The objective of the DSE is to evaluate the performance of the
computer and disk in a micro gravity environment.  The optical disk
system stem consists of an erasable optical disk drive unit and a
removable cartridge media.  Both are designed for reliable use under a
variety of environmental conditions.


STP-1 PARTICIPANTS

Overall Project Management
    Space Systems Division, Los Angeles AFB, Calif.

Responsible for integration of flight hardware, production
of flight and ground safety packages, and performance of all
integrated systems testing:
    NASA's Goddard Space Flight Center, Greenbelt, Md.


Organizations Responsible for the Experiments
    Naval Research Laboratory
    Washington, D.C.
    Ultraviolet Limb Imaging Experiment (UVLIM)

    Phillips Laboratory's Astronautics Directorate
    Edwards Air Force Base, Calif.
    Advanced Liquid Feed Experiment (ALFE)

    Hanscom Air Force Base, Mass.
    Spacecraft Kinetic Infrared Test (SKIRT)

    USAF Space Systems Division
    Detachment OL-AW, Houston, Tex.
    Ascent Particle Monitor (APM)

    NASA's Goddard Space Flight Center
    Greenbelt, Md.
    Data System Experiment (DSE)



MULTI-PURPOSE EXPERIMENT CANISTER (MPEC)

     The Multi-Purpose Experiment Canister (MPEC) carries a classified
experiment sponsored by the USAF Space Systems Division (SSD).  The
canister, a modified Get Away Special (GAS) container, is mounted on a
beam attached to the starboard sidewall of orbiter cargo bay 6.  The
modified canister includes a 9-inch extension containing an ejection kit,
electronics and a full diameter motorized door assembly.

     The experiment is scheduled to be deployed from the cargo bay on the
last day of the mission.  However, deployment can occur earlier on a
contingency basis.  The crew provides power to the MPEC via the standard
switch panel located in the crew compartment.  The crew will send a
command to open the canister door and, after verifying that the door is
open, will arm the ejection mechanism and send the deployment command.
The experiment is ejected with a relative velocity of about 2.7 ft/sec by a
spring mechanism.  After ejection, the canister door will be closed and
power removed from the canister.

CLOUDS 1A

     The overall objective of the CLOUDS-1A program is to quantify the
variation in apparent cloud cover as a function of the angle at which
clouds of various types are viewed.

     The CLOUDS-1A experiment is stowed in a middeck locker and consists
of a Nikon F3/T camera assembly and film.  On-orbit, a crew member will
take a series of high resolution photographs of individual cloud scenes,
preferably high "wispy" cirrus clouds, over a wide range of viewing angles.


RADIATION MONITORING EQUIPMENT-III

     Radiation Monitoring Equipment-III (RME-III) measures the rate and
dosage of ionizing radiation to the crew at different locations throughout
the orbiter cabin. The hand-held instrument measures gamma ray,
electron, neutron and proton radiation and calculates the amount of
exposure. The information is stored in memory modules for post-flight
analysis.

     RME-III will be stored in a middeck locker during flight except for
when it is turned on and when memory modules are replaced every 2 days.
It will be activated as soon as possible after achieving orbit and will
operate throughout the flight. To activate the instrument, a crew member
will enter the correct mission elapsed time.

     The instrument contains a liquid crystal display for real-time data
readings and a keyboard for function control. It has four zinc-air batteries
and five AA batteries in each replaceable memory module and two zinc-air
batteries in the main module.

     RME-III, which has flown on STS-31 and STS-41, is the current
configuration, replacing the earlier RME-I and RME-II units.

     The Department of Defense, in cooperation with NASA, sponsors the
data gathering instrument.

STS-39 CREW BIOGRAPHIES

     Michael L. Coats, 45, Capt., USN, will serve as commander. Selected
as an astronaut in 1978, he considers Riverside, Calif., his hometown.
STS-39 will be Coats' third space flight.

     Coats was pilot on STS-41D, launched Aug. 30, 1984, the maiden flight
of Discovery. Coats next commanded mission STS-29 aboard Discovery,
launched March 13, 1989, to deploy a Tracking and Data Relay Satellite.

     Coats graduated from Ramona High School, Riverside, in 1964, received
a bachelor of science from the U.S. Naval Academy in 1968; a master of
science in the administration of science and technology from George
Washington University in 1977; and a master of science in aeronautical
engineering from the U.S. Naval Postgraduate School in 1979.

     He was designated a naval aviator upon graduation from Annapolis in
1969 and was assigned to Attack Squadron 192 aboard the USS Kitty Hawk
for 2 years, flying 315 combat missions in Southeast Asia. He then served
as a flight instructor with the A-7E Readiness Training Squadron at the
Naval Air Station in Lenmoore, Calif., for a year before attending the Naval
Test Pilot School. Afterward, he was project officer and test pilot for the
A-7 and A-4 aircraft for 2 years before becoming a flight instructor at
the Test Pilot School in 1976.

     Coats has logged more than 5,000 hours of flying time in more than 28
different aircraft and 264 hours in space.

     L. Blaine Hammond, Jr., 38, Major, USAF, will serve as Pilot.
Selected as an astronaut in 1984, Hammond was born in Savannah, Ga., and
will make his first space flight.

     Hammond graduated from Kirkwood High School, Kirkwood, Mo., in 1969;
received a bachelor of science in engineering science and mechanics from
the U.S. Air Force Academy in 1973; and received a master of science in
engineering science and mechanics from the Georgia Institute of
Technology in 1974.

     Hammond earned his wings at Reese Air Force Base, Texas, in 1975 and
was assigned to the 496th Tactical Fighter Squadron, Hahn Air Base,
Germany, flying the F-4E. In 1979, he spent a year at Williams Air Force
Base, Ariz., flying the F-5B/E/F and training foreign students. Hammond
then attended the Empire Test Pilot School at A&AEE Boscombe Down,
England. He returned to Edwards Air Force Base in 1982 and was assigned
as an instructor at the Air Force Test Pilot School, a position he held at
the time of his selection by NASA.

     Hammond has logged more than 3,100 hours flying 15 different
American and 10 different English aircraft.

     Gregory J. Harbaugh, 34, will serve as Mission Specialist 1 (MS1).
Harbaugh, selected as an astronaut in 1987, considers Willoughby, Ohio, to
be his hometown and will make his first space flight.

     Harbaugh graduated from Willoughby South High School in 1974;
received a bachelor of science in aeronautical engineering from Purdue
University in 1978; and received a master of science in physical sciences
from the University of Houston-Clear Lake in 1986.

     Harbaugh came to NASA upon his graduation from Purdue and served in
engineering and management positions at JSC until his selection as an
astronaut. Harbaugh supported Shuttle operations in Mission Control for
most flights from STS-1 through STS-51L, working as a Data Processing
Systems (DPS) flight controller and later as a Shuttle Planning and
Analysis Manager, the senior flight controller interface with the
engineering community. He also has a commercial pilot's license and has
logged more than 1,000 hours flying time.

     Donald R. McMonagle, 38, Lt. Col., USAF, will serve as Mission
Specialist 2 (MS2). Selected as an astronaut in 1987, he was born in Flint,
Mich., and will make his first space flight.

     McMonagle graduated from Hamady High School, Flint, Mich., in 1970;
received a bachelor of science in astronautical engineering from the Air
Force Academy in 1974; and a master of science in mechanical engineering
from California State University-Fresno in 1985.

     He completed pilot training on the F-4 in 1975 and was assigned a
year-long tour of duty at Kunsan Air Base, South Korea. He returned to
Holloman AFB, N.M., in 1977 for training on the F-15, and, in 1979, was
assigned as an F-15 instructor at Luke AFB, Ariz. In 1981, he attended the
Air Force Test Pilot School and graduated as the outstanding pilot of his
class. From 1982-1985, he was the operations officer and test pilot for
the Advanced Fighter Technology Integration (AFTI) F-16. He then attended
the Air Command and Staff College at Maxwell AFB, Ala., for 1 year before
being assigned as operations officer for the 6513th Test Squadron at
Edwards AFB, Calif., where he was stationed at the time of his selection
by NASA.

     McMonagle has logged more than 3,400 hours flying time in a variety of
aircraft.

     Guion S. Bluford, 48, Col., USAF, will serve as Mission Specialist 3
(MS3). Selected as an astronaut in 1979, Bluford was born in Philadelphia,
Pa., and will make his third space flight.

     Bluford graduated from Overbrook High School, Philadelphia, in 1960;
received a bachelor of science in aerospace engineering from Pennsylvania
State University in 1964; received a master of science in the same
subject from the Air Force Institute of Technology in 1974; received a
doctorate in aerospace engineering with a minor in laser physics from the
Air Force Institute of Technology in 1978; and received a master of
business administration from the University of Houston-Clear Lake in
1987.

     He served as a mission specialist on STS-8, launched Aug. 30, 1983,
the third flight of Challenger and first mission with a night launch and
landing. During the flight, the crew deployed the Indian National Satellite
(INSAT-1B) and operated the remote manipulator system with a test
article. His next flight was as a mission specialist aboard Challenger on
STS 61-A, launched Oct. 30, 1985, with the German D-1 Spacelab.

     Bluford has logged more than 314 hours in space.

     C. Lacy Veach, 46, will serve as Mission Specialist 4 (MS4). Selected
as an astronaut in 1984, Veach considers Honolulu his hometown and will
make his first space flight.

     Veach graduated from Punahou School in 1962 and received a bachelor
of science in engineering management from the Air Force Academy in
1966.

     Veach was commissioned in the Air Force upon graduation from the
Academy and received his pilot wings in 1967. For 14 years, he served as a
fighter pilot with a variety of assignments in the United States and
overseas, including a 275-mission combat tour in Southeast Asia and 2
years with the Air Force Demonstration Squadron, the Thunderbirds. Veach
left active duty in 1981, but continues to fly with the Texas Air National
Guard.

     He began work at NASA in 1982 as an engineer and research pilot,
serving as an instructor pilot in the Shuttle Training Aircraft until his
selection as an astronaut.

     He has logged more than 4,500 flying hours.

     Richard J. Hieb, 35, will serve as Mission Specialist 5 (MS5).
Selected as an astronaut in 1986, he considers Jamestown, N.D., his
hometown and will make his first space flight.

     Hieb graduated from Jamestown High School in 1973; received a
bachelor of arts in math and physics from Northwest Nazarene College in
1977; and received a master of science in aerospace engineering from the
University of Colorado in 1979.

     Hieb began work for NASA after graduating from the University of
Colorado, serving in the crew procedures development and crew activity
planning areas. He worked in Mission Control for ascent during STS-1 and
specialized in rendezvous and proximity operations for numerous
subsequent flights.


NASA SPACE SHUTTLE MANAGEMENT


NASA Headquarters
Office of Space Flight
Washington, D.C.

Dr. William B. Lenoir - Associate Administrator
Robert L. Crippen - Director, Space Shuttle
Leonard S. Nicholson - Deputy Director, Space Shuttle (Program)
Brewster Shaw - Deputy Director, Space Shuttle (Operations)


Kennedy Space Center
Kennedy Space Center, Fla.

Forrest S. McCartney - Director
Jay Honeycutt - Director, Shuttle Management & Operations
Robert B. Sieck - Launch Director
John T. Conway - Director, Payload Management & Operations
Joanne H. Morgan - Director, Payload Project Management
Roelf Schuiling - STS-39 Payload Manager


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 and Mission Assurance
Victor Keith Henson - Manager, Solid Rocket Motor Project
Cary H. Rutland - Manager, Solid Rocket Booster Project
Jerry W. Smelser - Manager, Space Shuttle Main Engine Project
Gerald C. Ladner - Manager, External Tank Project



Johnson Space Center
Houston, TEXAS

Aaron Cohen - Director
Eugene F. Kranz - Director, Mission Operations
Franklin Brizzolara - Payload Integration Manger

Stennis Space Center
Bay St. Louis, Miss.

John S. Estess - Director
Gerald W. Smith - Deputy Director
J. Harry Guin - Director, Propulsion Test Operations

Ames-Dryden Flight Research Facility
Edwards, Calif.

Kenneth J. Szalai, Director
T.G. Ayers, Deputy Director
James R. Phelps, Chief, Shuttle Support Office


Department of Defense Payload Management


Key Management Participants

Martin C. Faga - Assistant Secretary of the Air Force for Space

Mission Directors

Lt. Gen. Donald L. Cromer - Commander, Space Systems Division
Col. John E. Armstrong - Program Manager, Space Test and Transportation
System Office

CARGO Operations Officers

Maj. Robert Crombie - SSD/CLPC
Capt. Linda Wolters - SSD/CLPC

IBSS Program Directors

Mike Harrison - SDIO/TNS
Howard Stears - SKW Corp.

AFP-675 Program Directors

Capt. Lindley Johnson - SSD/CLPC
Capt. Lloyd Johnson - SSD/CLPC

STP-1 Program Directors

Ted Goldsmith - GSFC
Capt. Hau Tran - SSD/CLPC


Key Operations Participants

IBSS Operations Directors

Capt. Al Locker - GL
1Lt. Ross Balestreri - SSD/CLPC

IBSS Test Conductors

Jim Covington - Aerospace
Scott Bartell - SKW Corp.

IBSS Replanners

Howard R. Pedolsky - Orbital Systems, Ltd.
Larry Sharp - Aerospace

AFP-675 Operations Directors

Capt. Mike Spencer - SSD/CLPC
Capt. Pete Clarke - SSD/CLPC

STP-1 Operations Directors

Debbie Knapp - GSFC
Vic Gehr - GSFC