Suzy B Software 2/Suzy B Software CD-ROM 2 (1994).iso/nasa/sts_44pk/sts_44pk.txt

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STS-44 SPACE SHUTTLE MISSION PRESS KIT

NOVEMBER 1991





CONTENTS

GENERAL RELEASE ...............................................    1

STS-44 QUICK LOOK FACTS ........................................3

SUMMARY OF MAJOR ACTIVITIES ....................................4

SPACE SHUTTLE ABORT MODES ......................................5

TRAJECTORY SEQUENCE OF EVENTS ..................................6

VEHICLE & PAYLOAD WEIGHTS ......................................7

STS-44 PRELAUNCH PROCESSING ....................................8

DSP MISSION OVERVIEW ...........................................9

DOD PAYLOAD ...................................................10

DEPLOYMENT AND FLIGHT SEQUENCE ................................15

TERRA SCOUT AND M88-1 EXPERIMENTS .............................17

ULTRAVIOLET PLUME INSTRUMENT ..................................17

EXTENDED DURATION MEDICAL PROJECT .............................19

RADIATION MONITORING EQUIPMENT ................................20

SHUTTLE ACTIVATION MONITOR ....................................20

COSMIC RADIATION EFFECTS AND ACTIVATION MONITOR ...............20

AMOS AND VFT-1 ................................................21

BIOREACTOR EXPERIMENT .........................................21

STS-44 CREW BIOGRAPHIES .......................................22

SPACE SHUTTLE MANAGEMENT ......................................24

UPCOMING SPACE SHUTTLE MISSIONS ...............................27

PREVIOUS SPACE SHUTTLE FLIGHTS ................................28


RELEASE:  91-176

DEFENSE SATELLITE DEPLOY, OBSERVATIONS HIGHLIGHT STS-44

     Space Shuttle mission STS-44, the ninth Department of
Defense-dedicated Shuttle flight, will deploy the Defense Support
Program (DSP) satellite designed to detect nuclear detonations,
missile launches and space launches from a geosynchronous orbit.

     Atlantis is scheduled to launch at 6:51 p.m. EST on Nov. 19
for the 10-day flight, Atlantis' tenth flight and the 44th Shuttle
mission.  With an on-time launch, landing would be at 2:27 p.m.
EST on Nov. 29 at Kennedy Space Center, Fla., the primary landing
site.

     Commanding Atlantis will be Fred Gregory.  Tom Henricks will
serve as Pilot.  Mission specialists will be Jim Voss, Story
Musgrave and Mario Runco, Jr.  Tom Hennen will serve as Payload
Specialist.

     After deploying DSP on the first day of the flight, the crew
will work with a variety of secondary payloads aboard Atlantis.
The Terra Scout experiment will include onboard analysis and an
evaluation of using the Shuttle to observe various sites on Earth
by Hennen, a trained analyst who has intensively studied the sites
to be observed.  The Military Man in Space experiment will
evaluate the ability of a spaceborne observer to gather
information about ground troops, equipment and facilities.

     Other experiments aboard Atlantis include the Shuttle
Activation Monitor, that will measure the radiation environment
onboard and its effect on gamma ray detectors; the Cosmic
Radiation Effects and Activation Monitor, that will gather
information on cosmic rays and radioactivity onboard; and the
Radiation Monitoring Equipment, a third-generation instrument used
to measure the ionizing radiation aboard and crew's exposure to
it.

     Although no onboard equipment is carried for them, two
experiments will use remote sensors to study the Shuttle in orbit.
The Air Force Maui Optical System experiment uses and Air Force
electrical-optical system located on the Hawaiian island of Maui
to look at Shuttle jet firings, water dumps and encounters with
atomic oxygen.  The Ultraviolet Plume Instrument, a sensor located
on a DOD satellite in geosynchronous orbit, also will attempt to
observe Atlantis as a method of fine tuning the sensor.

      Also aboard will be the Visual Function Tester, an
experiment to study changes in vision that may be experienced in
weightlessness and the Interim Operational Contamination Monitor,
located in the cargo bay will measure contamination in the bay
during launch.

     In addition, the crew will take part in a variety of
continuing medical investigations of the effect of weightlessness
on the human body and methods of counteracting those effects.
Among the medical studies will be use of the Lower Body Negative
Pressure unit, an often-flown device that uses low pressure to
pull body fluids back to the lower extremities, counteracting the
tendency for such fluids to rise to the upper body in
weightlessness.  Other investigations and the 10-day length of the
flight are in preparation for a gradual increase in the duration
of Shuttle missions, including the first 13-day flight planned in
1992.

                            - end general release -



STS-44 QUICK LOOK

Launch Date and Site:
November 19, 1991
Kennedy Space Center, Fla., Pad 39A

Launch Window:
6:51 p.m.- 9:30 p.m. EST

Orbiter:
Atlantis (OV-104)

Orbit & Inclination:
195 x 195 nautical miles, 28.5 degrees

Landing Date/Time:
2:27 p.m. EST, Nov. 29, 1991

Primary Landing Site:
Kennedy Space Center, Fla.

Abort Landing Sites:
Return to Launch Site - Kennedy Space Center, Fla.
Transoceanic Abort Landing - Banjul, The Gambia
Alternates - Moron, Spain; Ben Guerir, Morocco
Abort Once Around - White Sands Space Harbor, N.M.

Crew:
Frederick D. Gregory, Commander
Terence T. Henricks, Pilot
James S. Voss, Mission Specialist 1
F. Story Musgrave, Mission Specialist 2
Mario Runco, Jr., Mission Specialist 3
Tom Hennen, Payload Specialist

Cargo Bay Payloads:
DSP/IUS (Defense Support Program)
IOCM (Interim Operational Contamination Monitor)

Middeck Payloads:
Terra Scout
M88-1  (Military Man in Space)
AMOS  (Air Force Maui Optical System)
CREAM  (Cosmic Radiation Effects and Activation Monitor)
SAM  (Shuttle Activation Monitor)
RME-III  (Radiation Monitoring Experiment-III)
VFT-1  (Visual Function Tester-1)
UVPI  (Ultraviolet Plume Instrument)

SUMMARY OF MAJOR ACTIVITIES

FLIGHT DAY ONE
Ascent
OMS 2
DSP/IUS deploy
RME activation
AMOS RCS test
VFT-1


FLIGHT DAY TWO
Terra Scout observations
VFT-1
SAM, CREAM, RME set up


FLIGHT DAY THREE
M88-1 set up, observations
Terra Scout observations
AMOS RCS test
RME, SAM, CREAM
VFT-1


FLIGHT DAY FOUR
VFT-1VFT-1
M88-1:  Battle view, MosesM88-1:  Battle view, Moses
Terra Scout observationsTerra Scout observations
AMOS FEST testAMOS FEST test
RME, SAM, CREAMRME, SAM, CREAM


FLIGHT DAY FIVE
Terra Scout observations
M88-1: Battle view
VFT-1
AMOS
SAM, RME, CREAM


FLIGHT DAY SIX
RME, SAM, CREAM
M88-1:  Battle view, Moses
Terra Scout observations
VFT-1


FLIGHT DAY SEVEN
M88-1: Battle view, Moses
Terra Scout observations
VFT-1
RME, SAM, CREAM


FLIGHT DAY EIGHT
Terra Scout observations
M88-1:  Battle view
VFT-1
SAM


FLIGHT DAY NINE
M88-1: Battle view, Moses
Terra Scout observations
RME, SAM, CREAM


FLIGHT DAY TEN
SAM, CREAM deactivation
Terra Scout observations
VFT-1
M88-1:  Battle view, Moses, stow
FCS checkout
RCS hot-fire
Cabin stow


FLIGHT DAY ELEVEN
Deorbit preparation
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.; the Shuttle Landing
Facility (SLF) at Kennedy Space Center, Fla.; or White Sands Space
Harbor (Northrup Strip), N.M.

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

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

     STS-44 contingency landing sites are Edwards AFB, Kennedy
Space Center, White Sands, Banjul, Moron and Ben Guerir.


STS-44 TRAJECTORY SEQUENCE OF EVENTS

EVENT                        MET          REL. VELOCITY   MACH   ALTITUDE
                           (d:h:m:s)            (fps)            (ft)

Launch                     00/00:00:00

Begin Roll Maneuver        00/00:00:10           187      .17         791

End Roll Maneuver          00/00:00:15           322      .29        2238

SSME Throttle Down to 70%  00/00:00:30           713      .64        9131

SSME Throttle Up to 104%   00/00:01:00          1384     1.35       34981

Max. Dyn. Pressure (Max Q) 00/00:01:02          1477     1.46       38259

SRB Staging                00/00:02:05          4182     3.72      154862

Main Engine Cutoff (MECO)  00/00:08:29         24571    22.74      364029

Zero Thrust                00/00:08:35         24570      N/A      363385

ET Separation              00/00:08:47

OMS-2 Burn                 00/00:40:47

Landing (orbit 81)         09/19:26:00



    Apogee, Perigee at MECO:      192 x  34 nautical miles

    Apogee, Perigee post-OMS 2:   196 x 195 nautical miles




STS-44 VEHICLE AND PAYLOAD WEIGHTS


                                                           Pounds

Orbiter (Atlantis) empty, and 3 SSMEs                      172,308

Defense Support Program/Inertial Upper Stage                37,618

DSP Airborne Support Equipment                               5,569

IUS Airborne Support Equipment                                 192

Interim Operational Contamination Monitor                      190

Cosmic Radiation Effects and Activation Monitor                 48

Radiation Monitoring Experiment-III                             23

Military Man in Space (M88-1)                                  130

Shuttle Activation Monitor                                      90

Terra Scout                                                    473

Visual Function Tester-1                                         7

Detailed Supplementary Objectives (DSOs)                       281

Total Vehicle at SRB Ignition                            4,526,272

Orbiter Landing Weight                                     193,825



STS-44 PRELAUNCH PROCESSING

     Flight preparations on Atlantis for the STS-44 mission began
on Aug. 12 following its last mission, STS-43 which ended with a
landing at KSC's Shuttle Landing Facility.  Atlantis was towed
from the runway to the Orbiter Processing Facility (OPF) to start
operations for its 10th flight.

     Space Shuttle main engine locations for this flight are as
follows:  engine 2015 in the No.1 position, engine 2030 in the No.
2 position and engine 2029 in the No. 3 position.  These engines
were installed in mid September.

     Booster stacking operations on the mobile launch platform
began Aug. 26.  Stacking of all booster segments was completed by
Sept. 19.  The external tank was mated to the boosters on Sept. 26
and the orbiter Atlantis was mated to the external tank and solid
rocket boosters Oct. 19.

     The STS-44 vehicle was rolled out to Launch Pad 39-A on Oct.
23.  A standard 43-hour launch countdown is scheduled to begin 3
days prior to 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 million gallons of liquid oxygen
and liquid hydrogen propellants.  About 2 and one-half hours
before liftoff, the flight crew will begin taking their assigned
seats in the crew cabin.




DSP MISSION

OVERVIEW

     The Defense Support Program (DSP) is a survivable and
reliable satellite-borne system that detects and reports on real-
time missile launches, space launches and nuclear detonations.

     Under contract to Air Force Systems Command's Space System
Division,  Los Angeles AFB, Calif., in support of the Air Force
Program Executive Officer for Space, TRW in Redondo Beach, Calif.,
builds the satellites and integrates the sensor payload built by
Aerojet Electronics Systems Division, Azusa, Calif.

     DSP satellites have been the spaceborne segment of NORAD's
Tactical Warning and Attack Assessment System since 1970.  The
satellites weigh approximately 5,200 pounds and use infrared
detectors to sense heat from missile plumes against the earth
background.

     Over the past 20 years, DSP has repeatedly proven its
reliability and potential for growth.  DSP satellites have
exceeded their specified design life by some 30 percent through
five upgrade programs.  These upgrades have allowed DSP to provide
accurate, reliable data in the face of changing requirements --
greater numbers, smaller targets, advanced countermeasures -- with
no interruption in service.  Planned evolutionary growth has
improved satellite capability, survivability and life expectancy
without major redesign.

     On-station sensor reliability has provided uninterrupted
service well past their design lifetime.  Recent technological
improvements in sensor design includes above-the-horizon
capability for full hemispheric coverage and improved resolution.
Increased on-board signal-processing capability improves clutter
rejection enhancing reliability and survivability.

     The original DSP weighed 2,100 pounds, had 400 watts of
power, 2,000 detectors and a design life of 3 years.  In the
1970's, the satellite was upgraded to meet new mission
requirements.  As a result, the weight grew to 3,960 pounds, the
power to 680 watts, the number of detectors increased by threefold
to 6,000, and the design life was 3 years with a goal of 5 years.
Today's DSP satellite weighs 5,200 pounds and requires 1250 watts
of power.

     STS-44 will launch the DSP spacecraft into low earth orbit
where the Inertial Upper Stage (IUS) will propel the spacecraft to
a geosynchronous-equatorial orbit.  Upon separation from the IUS,
the DSP satellite will initiate various on-board programs that
will allow the spacecraft to complete its mission.



THE SATELLITE

     The satellite is approximately 33 feet long, 14 feet in
diameter and weighs 5,200 pounds.  To provide a scanning motion
for the infrared (IR) sensor, the satellite is spun about its
Earth-pointing axis.  Satellite-spin momentum is reduced to a
nominal value of zero by introducing an equal and opposite
momentum achieved throughout operation of a Reaction Wheel.  The
resulting "zero momentum" satellite is attitude controlled by gas
thrusters.

SENSOR EVOLUTIONARY DEVELOPMENT (SED) SENSOR

     The sensor's purpose is to detect, locate, and identify
targets of interest that are intense sources of IR radiation.  The
sensor and the spacecraft, which together comprise the satellite,
are placed in geosynchrounous-equatorial orbit so that the
telescope is pointed toward the Earth and rotated at six
revolutions per minute.

     The axis of the satellite's rotation is normal to the Earth's
surface.  A prime requirement of the spacecraft is to provide
attitude control to maintain the pointing direction accurately.

     The major elements of the sensor are:

-IR Telescope Subsystem (IR)
-Star Sensor Subsystem (SS)
-Status Monitor Subsystem (SMS)
-Signal Electronics Subsystem (SES)
-Thermal Control Subsystem (TCS)
-Advance RADEC I (ARI)

     Detection of IR sources is accomplished with the telescope
and Photo-Electric Cell (PEC) array portions of the IR telescope
subsystem.  The PEC detector array, mounted in the telescope
center line to coincide with the image surface of the telescope
optics, scans the Earth's surface through rotation of the
satellite.  As a detector passes across an IR source it will
develop an electronic signal.  The many signals are relayed to
processing units where they are grouped and sent to the ground for
mission usage.


SPACECRAFT

     The basic functions of the spacecraft are to:
-  Provide a spin-controlled, stable, Earth pointing vehicle for
the mission data
sensing and processing equipment.

-  Furnish the on-board functions required to position control,
and maintain the
satellite in its proper Earth orbit.

-  Furnish, condition, and control the electrical power for all
satellite
requirements.

-  Provide secure downlink capabilities to transmit mission data,
State-of-Health
(SOH), and other relevant information to the ground for final
processing.

-  Provide a secure uplink command receiving, processing, and
distribution
capability for both spacecraft and sensor ground-generated
commands.

     The spacecraft consists of the following principal systems:

-  Structure
-  Communication and Command and Mission Data Message
-  Electrical Power and Distribution
-  Propulsion
-  Attitude Control
-  Thermal


INERTIAL UPPER STAGE (IUS)

Background

     The IUS was developed and built under contract to the Air
Force Systems Command's Space Systems Division.  Space Systems
Division is executive agent for all Department of Defense
activities pertaining to the Space Shuttle system and provides the
IUS to NASA for Space Shuttle use.  After 2-1/2 years of
competition, Boeing Aerospace Company, Seattle, was selected in
August 1976 to begin preliminary design of the IUS.

Specifications

     IUS 14, the vehicle to be used on mission STS-44, is a two-
stage rocket weighing approximately 32,500 pounds.  Each stage has
a solid rocket motor, preferred over liquid-fueled engines for
their relative simplicity, high reliability, low cost and safety.

     The IUS is 17 feet long and 9.25 feet in diameter.  It
consists of an aft skirt; an aft stage solid rocket motor
containing 21,400 pounds of propellant generating approximately
42,000 pounds of thrust; an interstage; a forward stage solid
rocket motor with 6,000 pounds of propellant generating
approximately 18,000 pounds of thrust; and an equipment support
section.

     The equipment support section 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.

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 DSP in the orbiter payload bay and
elevates the IUS/DSP for final checkout and deployment from the
orbiter.

     The IUS ASE consists of the structure, aft tilt frame
actuator, batteries, electronics and cabling to support the
IUS/DSP combination.  These ASE subsystems enable the deployment
of the combined vehicle; provide, distribute and/or control
electrical power to the IUS and satellite; and serve as
communication conduits between the IUS and/or satellite and the
orbiter.

IUS Structure

     The IUS structure is capable of supporting all the loads
generated internally and also by the cantilevered spacecraft
during orbiter operations and the IUS free flight.  In addition,
the structure physically supports all the equipment and solid
rocket motors within the IUS and provides the mechanisms for the
IUS stage separation.  The major structural assemblies of the two-
stage IUS are the equipment support section, interstage and aft
skirt.  It is made by aluminum skin-stringer construction, with
longerons and ring frames.

Equipment Support Section

     The Equipment Support Section houses the majority of the
avionics of the IUS.  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 DSP.

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 coasting.

     Attitude is compared with guidance commands to generate error
signals.  During solid motor firing, these commands gimbal the
IUS's movable nozzle to provide the desired attitude 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, power transfer unit,
utility batteries, pyrotechnic switching unit, IUS wiring harness
and umbilical and staging connectors.  The IUS avionics system
distributes electrical power to the IUS/DSP interface connector
for all mission phases from prelaunch to spacecraft separation.

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 solid rocket motor
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 fuel carried.  The
IUS-14 first stage motor will carry 21,400 pounds of propellant;
the second stage over 6,000 pounds.

Reaction Control System

     The reaction control system controls the IUS/DSP's attitude
during coasting; roll control during SRM thrustings; and velocity
impulses for accurate orbit injection.

     As a minimum, the IUS includes one reaction control fuel tank
with a capacity of 120 pounds of hydrazine.  Production options
are available to add a second or third tank.  IUS-14 will carry
two tanks, each with 120 pounds of fuel.

     To avoid spacecraft contamination, the IUS has no forward
facing thrusters.  The reaction control system is also used to
provide the velocities for spacing between several spacecraft
deployments and for avoiding collision or contamination after the
spacecraft separates.

IUS-to-Spacecraft Interfaces

     The DSP spacecraft 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 an insulation blanket comprised of multiple layers of
double-aluminized Kapton and polyester net spacers across the
IUS/DSP interface.  The outer layer of the blanket, facing the DSP
spacecraft, is a special Teflon-coated fabric called Beta cloth.
The 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.



IUS/DSP DEPLOYMENT AND 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 requirement constraints.

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

     Forward payload restraints are released and the aft frame of
the airborne support equipment tilts the IUS/DSP to 29 degrees.
This extends the DSP into space just outside the orbiter payload
bay, allowing direct communication with Earth during systems
checkout.  The orbiter is then maneuvered to the deployment
attitude.  If a problem develops within the spacecraft or IUS, the
IUS and its payload can be restowed.

     Prior to deployment, the spacecraft electrical power source
is 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 IUS/DSP predeployment operations
have been successfully completed, a GO/NO-GO decision for IUS/DSP
deployment is sent to the crew.

     When the orbiter flight crew is given a GO decision, they
activate the pyrotechnics that separate the IUS/DSP umbilical
cables.  The crew then commands the electromechanical tilt
actuator to raise the tilt table to a 58-degree deployment
position.  The orbiter's RCS thrusters are inhibited and a
pyrotechnic separation device is initiated to physically separate
the IUS/spacecraft combination from the tilt table.  Compressed
springs provide the force to jettison the IUS/DSP from the orbiter
payload bay at approximately 4.2 inches per second.  The
deployment normally is performed in the shadow of the orbiter or
in Earth eclipse.

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

     At this point, the IUS/DSP is controlled by the IUS onboard
computers.  Approximately 10 minutes after the IUS/DSP is ejected
from the orbiter, the IUS onboard computer sends signals used by
the IUS to begin mission sequence events.  This signal also
enables the reaction control system.  All subsequent operations
are sequenced by the IUS computer, from transfer orbit injection
through spacecraft separation and IUS deactivation.

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

     At approximately 45 minutes after ejection from the orbiter,
the pyrotechnic inhibits for the first solid rocket motor are
removed.  The belly of the orbiter has been oriented towards the
IUS/DSP combination to protect the orbiter windows from the IUS's
plume.  The IUS recomputes 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 sends the signal to ignite the first stage motor.
This is expected at approximately 60 minutes after deployment (L+7
hours, 207 minutes).  After firing approximately 146 seconds and
prior to reaching the apogee point of its trajectory, the IUS
first stage expends its fuel.  While coasting, the IUS performs
maneuvers needed by the DSP for thermal protection or
communications.  When this is completed, the IUS first stage and
interstage separate from the IUS second stage.

     Approximately 6 hours, 20 minutes after deployment (at
approximately L+12:39) the second stage motor ignites, thrusting
about 108 seconds.  After burn is complete, the IUS stabilizes the
DSP while the solar arrays and two antennas are deployed.  The IUS
second stage separates and performs a final collision/contamination
avoidance maneuver before deactivating.



TERRA SCOUT

     TERRA SCOUT is an Earth observation experiment, which will
utilize the skills of a trained analyst to perform the
observations.  The analyst is a payload specialist (PS) who has
intensively studied the sites of interest.  The PS is experienced
in imagery analysis, terrain and aerial observation, and has some
formal geology training.  The PS will use the Spaceborne Direct-
View Optical System (SpaDVOS) to assist him in the site analysis.
Each site will have a prepared site packet which includes selected
maps and photographs.  A number of selected sites have large
resolution panels laid out in a grid pattern.  The use of these
grids will facilitate quantifying the resolution limit from the
Shuttle cabin.  The primary objective of the TERRA SCOUT
experiment is to explore the man/machine interface between skilled
technicians and current and advanced sensors.

M88-1

     M88-1 is an ongoing series of tri-service experiments
designed to asses man's visual and communication capabilities from
space.  Areas of investigation include dynamic Shuttle tasking,
near real-time information relay, and quantification of the
astronaut's visual resolution limits.

     The STS-44 mission will incorporate small aperture, long
focal-length optics, and a charge-coupled device (CCD) camera to
produce a high-resolution digital image that can be stored,
manipulated, and evaluated on-orbit.  Pertinent findings will then
be communicated via UHF voice to tactical field users seconds
after the observation pass is complete.

     Observation and communication sites include various Army,
Navy and Air Force units.  Site may be fixed (air fields, port
facilities, etc.) or mobile (ships at sea and ground
participants).  Emphasis is on coordinating observations with
ongoing DoD exercises to fully assess the military benefits of a
spaceborne observer.

ULTRAVIOLET PLUME INSTRUMENT (UVPI)

     The Strategic Defense Initiative's Ultraviolet Plume
Instrument (UVPI) is a sensor package which collects images of the
UV emission from rocket plumes in space and measures the UV
backgrounds seen from a space platform.

     The UVPI is mounted in a satellite currently in low earth
orbit called the Low-Power Atmospheric Compensation Experiment
(LACE), developed by the Naval Research Laboratory (NRL) and
launched February 14, 1990.  The Shuttle crew will perform
different types of engine burns when within view and range of the
LACE satellite.  UVPI will collect plume data on orbital
maneuvering system (OMS) and primary reaction control system
(PRCS) engine burns.

     The UVPI is mounted to look through an aperture in the Earth-
facing end of the LACE satellite.  A gimballed mirror allows the
UVPI to look at objects within a 50 degree half-angle cone about
nadir.  Another mirror mounted on the instrument's door allows
observation of stars and the Earth's horizon when the door is
partially open.  The UVPI has two cameras.  The tracker camera has
a 1.9 degree by 2.5 degree field of view and is used to acquire
and track a target so that the electronic tracker can lock on and
bring the target into the smaller field-of-view (0.11 x 0.15
degree) of the plume camera.  The tracker camera has a 245 to 450
nanometer passband.  The plume camera has four filters which can
be selected.  The four passbands for the plume camera are:

260 to 280 nanometers
300 to 320 nanometers
220 to 260 nanometers
250 to 345 nanometers

     Images can be transmitted from the UVPI and the LACE
satellite at either 5 or 30 images per second, depending on the
selected size of the image.

     Emissions observed by the UVPI in wavelengths between 220 and
320 nanometers cannot pass through the Earth's ozone layer, which
is found at altitudes between 40 and 80 kilometers.  Therefore the
220 to 320 nanometer emission from a rocket firing above 80
kilometers can only by observed by a space-based instrument such
as UVPI.  Since the Shuttle will be orbiting above the atmosphere,
UVPI will have an unencumbered view of the Shuttle plumes.


EXTENDED DURATION ORBITER MEDICAL PROJECT

     A series of medical investigations are included in the STS-44
flight plan to assist in the continuing development of
countermeasures to combat adverse effects of space flight.

     The headward shift of body fluids and slight muscle atrophy
that occurs in space causes no problems while astronauts are in
space.  Researchers are investigating the readaptive processes
that occur immediately upon return to Earth's gravity during
landing and egress operations.

     The Extended Duration Orbiter Medical Project, sponsored by
the Johnson Space Center's Medical Science Division, will validate
countermeasures for longer duration flights.  Nine of the 13
Detailed Supplementary Objectives flying on STS-44 support the
project. The crew's activities will include electrocardiograph
monitoring; measurement of inner eye pressure; assessing
orthostatic function, the ability to stand upright upon return to
Earth; treadmill exercise; checking gaze stability; and examining
endocrine system regulation.  Many of the on-orbit findings will
be compared with tests done before and after the flight.

     A large segment of the crew's time will be devoted to the
Lower Body Negative Pressure investigation (LBNP).  This is the
validation of a countermeasure combining rehydration and
orthostatic stress for use on longer space flights.  Operationally
it will be a single application, 4-hour treatment scheduled for
the day before landing.  The validation process, however, uses a
more extensive schedule of LBNP testing.

     The LBNP unit is a sleeping bag-like device that seals at the
waist. Once the crew member is situated in the device, the
pressure is gradually decreased, drawing fluids to the lower body
much like gravity does when one stands upright on Earth.  Crew
members also will ingest salt tablets and water during the LBNP
treatment. The result of the procedure is expected to be an
increased tolerance of standing upright upon return to Earth's
gravity.

     During STS-44, crew members will employ "ramp" and "soak"
procedures.  The ramp, which lasts 36 minutes, gradually lowers
the pressure in the unit by 10 millimeters of mercury, or mmHg,
increments to -50 mmHg before recovery.  The soak procedure,
performed once late in the mission, holds the negative pressure in
the unit to -30 mmHg for three hours and 45 minutes.  A ramp
procedure is performed 24 hours later to determine if the soak
improved the subject's orthostatic tolerance.  Heart rate and
blood pressure measurements are taken during both procedures.

     LBNP has been used a number of times in the United States
space program, first during the Skylab missions.  STS-44 will be
the second flight of an improved, collapsible, locker-stowed unit.
Researchers are refining the LBNP protocol which may be used
operationally on future 13- through 16-day missions.




RADIATION MONITORING EQUIPMENT

     The Radiation Monitoring Equipment-III measures ionizing
radiation exposure to the crew within the orbiter cabin.  RME-III
measures gamma ray, electron, neutron and proton radiation and
calculates in real time exposure in RADS-tissue equivalent.  The
information is stored in memory modules for post-flight  analysis.

     The hand-held instrument will be stored in a middeck locker
during flight except for activation and memory module replacement,
done every two days.  RME-III will be activated by the crew as
soon as possible after reaching orbit and operated throughout the
mission.  A crew member will enter the correct mission elapsed
time upon activation.

     RME-III is the current configuration, replacing the earlier
RME-I and RME-II units. RME-III last flew on STS-31.  The
experiment has four zinc-air batteries and five AA batteries in
each replaceable memory module.  RME-III is sponsored by the
Department of Defense in cooperation with NASA.

SHUTTLE ACTIVATION MONITOR

     The Shuttle Activation Monitor (SAM) is designed to measure
gamma ray data within the orbiter as a function of time and
location.

     Located in the middeck, the crew will install a foil packet
at four locations onboard. A tape recorder and two detector
assemblies will then record the information. Each activation of
the experiment will last about 12 hours and will record
information from a different location of the cabin.  SAM is
sponsored by the Air Force Space Systems Division, Los Angeles.

COSMIC RADIATION EFFECTS AND ACTIVATION MONITOR

     The Cosmic Radiation Effects and Activation Monitor (CREAM)
experiment is designed to collect data on cosmic ray energy loss
spectra, neutron fluxes and induced radioactivity.  The data will
be collected by active and passive monitors placed at specific
locations throughout the orbiter's cabin.  CREAM data will be
obtained from the same locations that will be used to gather data
for the Shuttle Activation Monitor (SAM) experiment in an attempt
to correlate data between the two.

     The active monitor will be used to obtain real-time spectral
data, while the passive monitors will obtain data during the
entire mission to be analyzed after the flight.  The flight
hardware has the active cosmic ray monitor, a passive sodium
iodide detector, and up to five passive detector packages.  All
hardware fits in one locker on Discovery's middeck.

     Once in orbit the payload will be unstowed and operated by
the crew.  A crewmember will be available at regular intervals to
monitor the payload/experiment.  CREAM is sponsored by the
Department of Defense.


AIR FORCE MAUI OPTICAL SYSTEM

     The Air Force Maui Optical System (AMOS) is an electrical-
optical facility located on the Hawaiian Island of Maui.  The
facility tracks the orbiter as it flies over the area and records
signatures from thruster firings, water dumps or the phenomena of
Shuttleflow, a well-documented glowing effect around the Shuttle
caused by the interaction of atomic oxygen with the spacecraft.
The information obtained is used to calibrate the infrared and
optical sensors at the facility.  No hardware onboard the Shuttle
is needed for the system.

VFT-1

     The objective of the VFT-1 experiment is to measure changes
in a number of vision parameters in the vision of subjects exposed
to microgravity.  The VFT-1 consists of hand-held battery-powered
testing device which incorporates a binocular eyepiece and uses
controlled illumination to present a variety of visual targets for
subject testing.  The device measures a number of basic vision
performance parameters.  Test results data are read on a display
and recorded on data sheets.

BIOREACTOR FLOW AND PARTICLE TRAJECTORY:

     Bioreactor Flow and Particle Trajectory in Microgravity is a
fluid dynamics experiment aboard STS-44 to validate Earth-based
predictions for the action of cell cultures in the NASA-developed
Slow-Turning Lateral Vessel (STLV) bioreactor.

     Ground research efforts in cell culturing are limited because
of the inability to suspend cultures in the presence of gravity.
Cultures grown by standard methods often are damaged by the
suspension processes or, in effect, smother their own development
when nutrients are blocked from some cells by others developing
around them.  Researchers are interested in the benefits of flying
a bioreactor in space because of the expected increased
capabilities for cell culturing.

     The STLV bioreactor, developed as a tool for Space Station
Freedom, grows cell cultures in a horizontal cylindrical container
that slowly rotates, emulating microgravity and keeping the cells
continuously suspended while bathing them in nutrients and oxygen.
On STS-44, components from the NASA bioreactor will occupy two
middeck lockers.  Inside the system, beads of varying sizes
simulating cell cultures of varying sizes will be rotated in a
solution of water and nutrients.  The action of the beads will be
used to validate the predicted action of cell cultures in
microgravity.  The results of DSO 316 will be used to refine the
system for future flight experiments.

     Though no cell cultures are currently manifested, plans are
for researchers to fly growth experiments on future Shuttle
flights.  Previous ground-based research has resulted in promising
findings in kidney, brain tumor, lung, small intestine and
cartilage tissue growth.  Such tissue growth could be used in
disease or replacement research.

     The STLV bioreactor is a project of the Johnson Space
Center's Medical Sciences Division Biotechnology Program, managed
by Dr. Glenn Spaulding.

STS-44 CREW BIOGRAPHIES

     Frederick D. Gregory, 50, Col., USAF, will serve as commander
of STS-44 and will be making his third flight.  Gregory, from
Washington, D.C., was selected as an astronaut in January 1978.
Gregory's first space flight was as pilot on STS-51B in April
1985. He next flew as commander of STS-33, a Department of
Defense-dedicated shuttle mission in November 1989.

     Gregory graduated from Anacostia High School, Washington,
D.C., in 1958, received a bachelor's degree from the United States
Air Force Academy in 1964 and a master's degree in information
systems from George Washington University
in 1977.

     He has logged more than 288 hours in space and more than
6,500 hours of
flying time in more than 50 types of aircraft, including 550
combat missions in Vietnam.

     Terence T. Henricks, 39, Col., USAF, will serve as pilot.
Selected as an astronaut in July 1986, Henricks considers
Woodville, Ohio, his hometown and will be making his first space
flight.

     He graduated from Woodmore High School in Woodville in 1970;
received a bachelor's degree in civil engineering from the U.S.
Air Force Academy in 1974, and received a master's degree in
public administration from Golden Gate
University in 1982.

     Henricks flew the F-4 in fighter squadrons in England and
Iceland. In 1980, he was reassigned to Nellis Air Force Base, Las
Vegas.  After attending the USAF Test Pilot School in 1983, he
remained at Edwards Air Force Base, Calif., as an F-16C test pilot
and chief of the 57th Fighter Weapons Wing Operating Location
until his selection as an astronaut.

     Henricks has logged more than 3,300 hours flying time in more
than 30 different types of aircraft.

     James S. Voss, 42, Lt. Col, USA, will serve as mission
specialist 1 (MS1).  Selected as an astronaut in June 1987, Voss
will be making his first space flight and considers Opelika, Ala.,
his hometown.

     Voss graduated from Opelika High School; received a
bachelor's degree in aerospace engineering from Auburn University
in 1972; and received a master's degree in aerospace engineering
sciences from the University of Colorado in 1974.

     Voss taught for three years in the Department of Mechanics at
the U.S.  Military Academy and  attended the U.S. Naval Test Pilot
School. He was involved in four major flight test projects before
being detailed to the Johnson Space Center in November 1984 as a
vehicle integration test engineer.

     At JSC, he supported shuttle and payload testing at the
Kennedy Space Center for STS 51-D, 51-F, 61-C and 51-L, and
participated in the STS 51-L accident investigation until his
selection as an astronaut.

     Story Musgrave, 56, will be mission specialist 2 (MS2).
Selected as an astronaut in August 1967, Musgrave considers
Lexington, Ky., his hometown and will be making his fourth space
flight.

     Musgrave graduated from St. Mark's School, Southborough,
Mass., in 1953; received a bachelor's degree in mathematics and
statistics from Syracuse University in 1958; received a master's
degree in operations analysis and computer programming from the
University of California at Los Angeles in 1959; received a
bachelor's degree in chemistry from Marietta College in 1960;
received a doctorate in medicine from Columbia University in 1964;
received a master's degree in physiology and biophysics from the
University of Kentucky in 1966; and received a master's degree in
literature from the University of Houston in 1987.

     Musgrave flew as a mission specialist on STS-6 in April 1983,
on Spacelab-2 in August 1985 and on STS-33 in November 1989. He
has logged more than 431 hours in space.

     Mario Runco, Jr., 39, Lt. Comdr., USN, will be mission
specialist 3 (MS3).  Selected as an astronaut in June 1987, Runco
considers Yonkers, N.Y., his hometown and will be making his first
space flight.

     Runco graduated from Cardinal Hayes High School, Bronx, NY,
in 1970; received a bachelor's degree in meteorology and physical
oceanography from the City College of New York in 1974; and
received a master's degree in meteorology from Rutgers University,
New Brunswick, N.J., in 1976.

     Runco worked as a research hydrologist for the U.S.
Geological Survey in New York, and, in 1977, he became a New
Jersey State Trooper until entering the Navy in June 1978.  He was
assigned to the Naval Environmental Prediction Research Facility
in Monterey, Calif., as a research meteorologist.  He later
commanded or served on several meteorological and oceanographic
surveys and research assignments aboard various Naval vessels.

     Thomas J. Hennen, 39, CWO-3, USA, will serve as payload
specialist (PS).  Hennen considers Columbus, Ohio, his hometown
and will be making his first space flight.  He graduated from
Groveport-Madison High School in Groveport, Ohio, in 1970;
attended Urbana College in Urbana, Ohio, from 1970-1972; and
completed numerous military courses of instruction.

     Hennen has more than 18 years of Army experience in
acquisitions management  and as an operational imagery analyst.
He has been assigned to the 163rd Military Intelligence Battalion,
the 203rd Military Intelligence Detachment and the 2nd Military
Intelligence Battalion.  From 1981-1986, Hennen was stationed in
Fort  Huachuca, Ariz., and was involved in the development of U.S.
Army imagery interpretation training and applications courses.

STS-44 MISSION MANAGEMENT - NASA


NASA HEADQUARTERS
WASHINGTON, D.C.

Richard H. Truly - NASA Administrator
J. R. Thompson - Deputy Administrator
Dr. William Lenoir - Associate Administrator, Office of Space Flight
Robert L. Crippen - Director, Space Shuttle
Leonard S. Nicholson - Deputy Director, Space Shuttle (Program)
Brewster H. Shaw - Deputy Director, Space Shuttle (Operations)
George A. Rodney - Associate Administrator for Safety and Mission Quality
James H. Ehl - Deputy Associate Administrator for Safety and Mission Quality
Richard U. Perry - Director, Programs Assurance Division


KENNEDY SPACE CENTER
KENNEDY SPACE CENTER, FLA.

Forrest S. McCartney - Director
James A. Thomas  - Deputy Director
Robert B. Sieck - Launch Director
George T. Sasseen - Shuttle Engineering Director
John T. Conway - Director, Payload Management and Operations
Joanne H. Morgan - Director, Payload Project Management
Conrad Nagel - Atlantis Flow Director


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
James N. Strickland - Acting Manager, Space Shuttle Main Engine Project
Victor Keith Henson - Manager, Solid Rocket Motor Project
Cary H. Rutland - Manager, Solid Rocket Booster Project
Gerald C. Ladner - Manager, External Tank Project



JOHNSON SPACE CENTER
HOUSTON, TEX.

Aaron Cohen - Director
Paul J. Weitz - Deputy Director
Daniel Germany - Manager, Orbiter and GFE Projects
Richard Covey - Acting Director, Flight Crew Operations
Eugene F. Kranz - Director, Mission Operations
Henry O. Pohl - Director, Engineering
Charles S. Harlan - Director, Safety, Reliability and Quality Assurance


STENNIS SPACE CENTER
BAY ST. LOUIS, MISS.

Roy S. Estess, Director
Gerald 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

STS-44 MISSION MANAGEMENT - DOD

Mission Director
Col. John R. Kidd - Program Director, Defense Support Program

Deputy Mission Director
Col. John E. Armstrong - Program Manager, Space Test and Transportation
                         System    Program Office

IUS Program Management
Col. Norman H. Buchanan - Program Director, Upper Stages Program Office

Mission Director Representatives
Col. Edward R. Dietz - Deputy Program Director, Defense Support Program
Major Michael W. Booen - Director, Space Systems

Mission Director Support Team
Capt. Linda R. Cole, Mission Manager, SSD/MJSO
Capt. Gregory D. Moxley, DSP Integration Manager, SSD/MJSO
Capt. Samuel J. Domino, MD Action Officer, JSC/OL-AW
Lt. Anthony F. Papatyi, IUS Integration Manager, SSD/CLUI

Air Force Test Director
Maj. John Traxler, 6555 ASTG

CSTC Flight Directors
Capt. Rick Kellogg - Ascent, CSTC/VOS
Capt. Frank Alexa (Lead) - Deploy Phase, CSTC/VOS
Capt. Bill Moriarity - Transfer Orbit, CSTC/VOS

Spacecraft Flight Directors
Capt. Rich Edmonds (Lead) - Deploy Phase, SSD/MJSO
Capt. Kathy Hays - Transfer Orbit, SSD/MJSO

Secondary Payload Operations Manager
Capt. Rick L. Shimon, JSC/OL-AW

 -END-