yee@trident.arc.nasa.gov (Peter E. Yee) (02/19/91)
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