yee@trident.arc.nasa.gov (Peter E. Yee) (02/19/91)
PUBLIC AFFAIRS CONTACTS
NASA
Mark Hess/Jim Cast/Ed Campion
Office of Space Flight
NASA Headquarters, Washington, D.C.
(Phone: 202/453-8536)
Lisa Malone
Kennedy Space Center, Fla.
(Phone: 407/867-2468)
Jerry Berg
Marshall Space Flight Center, Huntsville, Ala.
(Phone: 205/544-0034)
James Hartsfield
Johnson Space Center, Houston, Texas
(Phone: 713/483-5111)
Delores Beasley
Goddard Space Flight Center, Greenbelt, Md.
(Phone: 301/286-2806)
Myron Webb
Stennis Space Center, Miss.
(Phone: 60l/688-334l)
Nancy Lovato
Ames-Dryden Flight Research Facility, Edwards, Calif.
(Phone: 805/258-3448)
PUBLIC AFFAIRS CONTACTS
DOD
Capt. Marty Hauser
Secretary of the Air Force Public Affairs
The Pentagon
(Phone: 703/695-5766)
Betty Ciotti
USAF Space Systems Division
Los Angeles AFB, Calif.
(Phone: 213/363-6836)
Maj. Carolyn Channave
DOD/SDIO External Affairs
The Pentagon
(Phone: 703/693-1777)
Robert McKinney
SDIO External Affairs
The Pentagon
(Phone: 703/693-1778)
Lt. Col. Jim Jannette
Eastern Space and Missile Center, Fla.
(Phone: 407/494-7731)
CONTENTS
GENERAL INFORMATION 5
GENERAL RELEASE 6
STS-39 QUICK LOOK 9
SUMMARY OF MAJOR ACTIVITIES 10
SPACE SHUTTLE ABORT MODES 12
TRAJECTORY SEQUENCE OF EVENTS 13
VEHICLE AND PAYLOAD WEIGHTS 14
STS-39 PRELAUNCH PROCESSING 15
SHUTTLE ADVANCED GENERAL PURPOSE COMPUTER 16
STS-39 MISSION OVERVIEW 17
AIR FORCE PAYLOAD-675 (AFP-675) 20
CIRRIS-1A 20
AURORA DETAILS 23
FAR UV 24
URA 25
HUP 26
QINMS 28
INFRARED BACKGROUND SIGNATURE SURVEY (IBSS) 29
IBSS OVERVIEW 29
SPAS-II 29
CRO 29
CIV 33
IBSS OBJECTIVES 35
IBSS PLUME OBSERVATIONS 37
EARTH BACKGROUND EXPERIMENTS 37
ORBITER ENVIRONMENT EXPERIMENT 38
IBSS PARTICIPANTS 39
STS-39 SPAS/IBSS RENDEZVOUS & TRACKING OPERATIONS 40
SECONDARY PAYLOADS:
STP-1 44
OVERVIEW 44
HITCHHIKER PROJECT 44
ULTRAVIOLET LIMB IMAGING (UVLIM) EXPERIMENT 46
ADVANCED LIQUID FEED EXPERIMENT (ALFE) 46
SPACECRAFT KINETIC INFRARED TEST (SKIRT) 48
ASCENT PARTICLE MONITOR (APM) 49
DATA SYSTEM EXPERIMENT (DSE) 50
STP-1 PARTICIPANTS 51
MULTI-PURPOSE EXPERIMENT CANISTER (MPEC) 52
CLOUDS 1A 52
RADIATION MONITORING EQUIPMENT-III 53
STS-39 CREW BIOGRAPHIES 54
SPACE SHUTTLE MANAGEMENT 58
UPCOMING SPACE SHUTTLE MISSIONS 62
PREVIOUS SPACE SHUTTLE FLIGHTS 63
GENERAL INFORMATION
NASA Select Television Transmission
NASA Select television is available on Satcom F-2R, Transponder 13,
located at 72 degrees west longitude; frequency 3960.0 MHz, audio 6.8
MHz.
The schedule for television transmissions from the orbiter and for the
change-of-shift briefings from Johnson Space Center, Houston, will be
available during the mission at Kennedy Space Center, Fla.; Marshall
Space Flight Center, Huntsville, Ala.; Johnson Space Center; and NASA
Headquarters, Washington, D.C. The TV schedule will be updated daily
to reflect changes dictated by mission operations.
Television schedules also may be obtained by calling COMSTOR,
713/483-5817. COMSTOR is a computer data base service requiring the
use of a telephone modem. A voice update of the TV schedule may be
obtained by dialing 202/755-1788. This service is updated daily at
noon EST.
Status Reports
Status reports on countdown and mission progress, on-orbit activities
and landing operations will be produced by the appropriate NASA news
center.
Briefings
An STS-39 mission press briefing schedule will be issued prior to
launch. During the mission, flight control personnel will be on 8-hour
shifts. Change-of-shift briefings by the off-going flight director will
occur at approximately 8-hour intervals.
RELEASE: 91-25
STRATEGIC DEFENSE SYSTEM TESTS HIGHLIGHT STS-39 MISSION
Mission STS-39 is the first unclassified Department of Defense-
dedicated Space Shuttle mission, highlighted by around-the-clock
observations of the atmosphere, gas releases, Shuttle engine firings,
subsatellite gas releases and the Shuttle's orbital environment in
wavelengths ranging from infrared to the far ultraviolet.
Carried aboard Discovery on its 12th flight, the 39th Shuttle mission,
will be Air Force Program-675 (AFP-675); the Infrared Background
Signature Survey (IBSS) mounted on the Shuttle Pallet Satellite-II (SPAS-
II); the Critical Ionization Velocity (CIV) experiment; three Chemical
Release Observation (CRO) subsatellites; the Space Test Payload (STP-1)
and a classified payload in a Multi-Purpose Experiment Canister (MPEC).
Inside Discovery's crew cabin will be the Cloud Logic to Optimize the
Use of Defense Systems-1A (CLOUDS-1A) experiment and the Radiation
Monitoring Equipment-III (RME-III).
Work with these payloads during the flight will involve extensive
maneuvering, rendezvous and close proximity operations by Discovery.
STS-39 is currently working toward a 3:49 a.m. EST launch on March 9,
1991. Landing is set for Edwards Air Force Base, Calif., at 11:14 a.m. EST
on March 17, giving the flight a planned length of 8 days, 7 hours and 26
minutes.
AFP-675 is a collection of scientific instruments to observe targets
such as the atmosphere, the aurora and stars in infrared, far ultraviolet,
ultraviolet and X-ray wavelengths. AFP-675 instruments also will analyze
the spectrum of various targets and gases released from or around the
Shuttle. AFP-675 is sponsored by the U.S. Air Force's Space Systems
Division and may provide a better understanding of the difficulties in
identifying spacecraft with remote sensors and distinguishing those
spacecraft from naturally occurring phenomena. The AFP-675 instruments
also are to study several astronomical targets of interest.
The Strategic Defense Initiative Organization's IBSS experiment,
mounted on the SPAS-II platform, will be deployed and retrieved by
Discovery so that SPAS-II can observe the Shuttle's engine firings from
afar. IBSS will observe and record the infrared signature of these firings
and also will perform infrared observations of other targets, including
three CRO subsatellites to be released from Discovery. IBSS will observe
common rocket fuels nitrogen tetroxide, monomethyl hydrazine and
dimethyl hydrazine released from the three CRO subsatellites after they
are deployed by Discovery.
IBSS also will observe releases of the gases xenon, neon, carbon
dioxide and nitric oxide from canisters in Discovery's payload bay. These
gases are part of the CIV experiment, which, with instruments in the
payload bay, will observe the releases simultaneously with IBSS. IBSS is
sponsored by SDIO and information from its studies may assist in
developing remote sensors that can identify missiles.
The STP-1 experiment is a varied collection of scientific instruments,
including one that will observe the luminous "airglow" effect of atomic
oxygen on Discovery; one that will test a new method of flowing rocket
propellants in weightlessness to assist in the design of future engines;
and another to observe the fringes of Earth's atmosphere at various times,
including sunrise and sunset, in ultraviolet wavelengths. STP-1 is
sponsored by the Air Force's Space Systems Division.
Inside the crew cabin, the CLOUDS-1A experiment is a camera the crew
will use to photograph various cloud formations on the Earth to better
understand cloud movements and structures. The RME-III experiment is
designed to monitor radiation levels inside the cabin during the flight.
Commanding Discovery will be Navy Capt. Michael L. Coats. Air Force
Major L. Blaine Hammond will serve as pilot. Mission specialists include
Gregory J. Harbaugh; USAF Lt. Col. Don McMonagle; USAF Col. Guion Bluford;
C. Lacy Veach; and Richard J. Hieb.
The flight crew will operate in two teams to accommodate 24-hour a
day observations aboard Discovery, with each team working a 12-hour
shift. On the Red Team will be Hammond, Veach and Hieb. On the Blue Team
will be Harbaugh, McMonagle and Bluford. Coats will keep his own hours,
independent of any assigned shift.
(End of general release. Background information follows.)
STS-39 QUICK LOOK
Launch Date and Site: Mar. 9, 1991
Kennedy Space Center, Fla., Pad 39-A
Launch Window: 3:49 a.m. - 6:51 a.m. EST
Orbiter: Discovery (OV-103)
Orbit: 140 x 140 nautical miles, 57 degrees inclination
Landing Date/Time: Mar. 17, 1991, 11:14 a.m. EST
Primary Landing Site: Edwards Air Force Base, Calif.
Abort Landing Sites:
Return to Launch Site - Kennedy Space Center, Fla.
Transoceanic Abort Landing - Zaragosa and Moron, Spain
Abort Once Around - Northrup Strip, White Sands, N.M.
Crew:
Michael L. Coats, Commander
Blaine Hammond, Jr., Pilot
Gregory L. Harbaugh, Mission Specialist 1
Donald R. McMonagle, Mission Specialist 2
Guion S. Bluford, Mission Specialist 3
C. Lacy Veach, Mission Specialist 4
Richard J. Hieb, Mission Specialist 5
Cargo Bay Payloads:
IBSS/SPAS-II
CIV
CRO
STP-1
MPEC
Middeck Payloads:
Cloud Logic to Optimize the Use of Defense Systems (CLOUDS-1A)
Radiation Monitoring Experiment (RME-III)
SUMMARY OF MAJOR ACTIVITIES
FLIGHT DAY ONE
Ascent
OMS 2
IBSS on-orbit checkout
AFP-675 activation
RME-III activation
DSO
FLIGHT DAY TWO
AFP-675 operations
SPAS pre-deploy checkout
IBSS/SPAS-II unberth; deploy
IBSS/SPAS-II far-field observations
FLIGHT DAY THREE
IBSS/SPAS-II far-field observations
IBSS/SPAS-II near-field observations
CRO-C deploy
FLIGHT DAY FOUR
IBSS/SPAS-II near-field observations
IBSS/SPAS-II rendezvous
CRO-B deploy
IBSS/SPAS-II retrieval; berthing
DSO
FLIGHT DAY FIVE
AFP-675 operations
CRO-A deploy
FLIGHT DAY SIX
SPAS-II pre-deploy checkout
IBSS/SPAS-II unberthing; RMS operations
FLIGHT DAY SEVEN
IBSS/SPAS-II berthing
AFP-675 operations
FLIGHT DAY EIGHT
AFP-675 operations
STP-I operations
Flight Control Systems checkout
MPEC deploy
Payload deactivation
Cabin stow
FLIGHT DAY NINE
RME-III deactivation; stow
Deorbit; landing
SPACE SHUTTLE ABORT MODES
Space Shuttle launch abort philosophy aims toward safe and intact
recovery of the flight crew, orbiter and its payload. Abort modes
include:
* Abort-To-Orbit (ATO) -- Partial loss of main engine thrust late
enough to permit reaching a minimal 105-nautical mile orbit with
orbital maneuvering system engines.
* Abort-Once-Around (AOA) -- Earlier main engine shutdown with
the capability to allow one orbit around before landing at either
Edwards Air Force Base, Calif.; White Sands Space Harbor (Northrup
Strip), NM; or the Shuttle Landing Facility (SLF) at Kennedy Space
Center, FL.
* Trans-Atlantic Abort Landing (TAL) -- Loss of two main engines
midway through powered flight would force a landing at either
Zaragosa or Moron, Spain.
* Return-To-Launch-Site (RTLS) -- Early shutdown of one or more
engines, and without enough energy to reach Zaragosa, would result
in a pitch around and thrust back toward KSC until within gliding
distance of the SLF.
STS-39 contingency landing sites are Edwards AFB, White Sands,
Kennedy Space Center, Zaragosa and Moron.
TRAJECTORY SEQUENCE OF EVENTS
__________________________________________________________
RELATIVE
EVENT MET VELOCITY MACH ALTITUDE
(d:h:m:s) (fps) (ft)
__________________________________________________________
Launch 00/00:00:00
Begin Roll
Maneuver 00/00:00:09 160 .14 600
End Roll
Maneuver 00/00:00:19 410 .37 3,500
Throttle Down to 70% 00/00:00:28 630 .56 7,170
Throttle Up to 104% 00/00:00:58 1,320 1.28 33,230
Max. Dynamic Pressure 00/00:01:03 1,460 1.45 38,540
SRB Staging 00/00:02:06 4,190 3.8 154,810
Main Engine Cutoff 00/00:08:30 24,900 21.94 375,830
Zero Thrust 00/00:08:40 24,974 21.68 375,830
ET Separation 00/00:08:50
OMS 2 Burn 00/00:38:00
IBSS/SPAS-II Deploy 01/21:10:00
IBSS/SPAS-II Retrieval 03/11:18:00
Deorbit Burn 08/06:31:00
Landing 08/07:26:00
Apogee, Perigee at MECO: 136 x 23 nautical miles
Apogee, Perigee post-OMS 2: 140 x 140 nautical miles
VEHICLE AND PAYLOAD WEIGHTS
Pounds
Orbiter (Discovery) empty, and 3 SSMEs 172,517
Remote Manipulator System (payload bay) 1,258
IBSS/SPAS-II (payload bay) 4,197
AFP-675 (payload bay) 203
Chemical Release Observation (CRO) (payload bay) 1,307
Critical Ionization Velocity (CIV) (payload bay) 1,215
Space Test Program (STP-I) (payload bay) 4,288
Radiation Monitoring Experiment-III (RME-III) 8
Cloud Logic to Optimize the Use of Defense Systems (CLOUDS) 8
Total Vehicle at SRB Ignition 4,512,245
Orbiter Landing Weight 211,300
STS-39 PRELAUNCH PROCESSING
Kennedy Space Center workers began preparing Discovery for its 12th
flight into space when the vehicle was towed into the Orbiter Processing
Facility on Oct. 18 following its previous mission, STS-33.
Discovery spent about 15 weeks in the processing facility undergoing
about 22 modifications and routine testing. One of the significant changes
made was the installation of the five new general purpose computers.
Space Shuttle main engine locations for this flight are as follows:
engine 2026 in the No. 1 position, engine 2030 in the No. 2 position, and
engine 2029 in the No. 3 position.
Booster stacking operations on mobile launcher platform 2 began Nov. 7
and were completed Dec. 13. The external tank was mated to the boosters
Dec. 18 and the Orbiter Discovery was bolted to the tank on Jan. 30.
STS-39 primary payloads were installed in Discovery's payload bay in
the OPF and at the launch pad. Payloads installed in the OPF include the
Critical Ionization Velocity payload and the Chemical Release Observatory.
The U.S. Air Force payload 675 and the Shuttle Pallet Satellite-II were
installed at the launch pad Feb. 5. The vehicle was rolled out to Launch
Pad 39-A on Feb. 4. A dress rehearsal launch countdown was held Feb. 7-8
at KSC.
The launch countdown will begin about 3 days prior to the launch.
During the countdown, the orbiter's onboard fuel and oxidizer storage
tanks will be loaded and all orbiter systems will be prepared for flight.
About 9 hours before launch, the external tank will be filled with its
flight load of a half a million gallons of liquid oxygen and liquid hydrogen
propellants. About 2 1/2 hours before liftoff, the flight crew will begin
taking their assigned seats in the crew cabin.
KSC's recovery teams will prepare the orbiter Discovery for the return
trip to Florida following the end-of-mission landing at Edwards AFB,
Calif. Orbiter turnaround operations at Dryden Flight Research Facility
typically take about 5 days.
SHUTTLE ADVANCED GENERAL PURPOSE COMPUTER
On STS-39, Discovery's avionics system will feature the first set of
five upgraded general purpose computers (GPCs), plus a spare, to fly
aboard the Shuttle.
The updated computers have more than twice the memory and three
times the processing speed of their predecessors. Officially designated
the IBM AP-101S, built by IBM, Inc., they are half the size, about half the
weight and require less electricity than the first-generation GPCs. The
central processor unit and input/output processor, previously installed as
two separate boxes, are now a single unit.
The new GPCs use the existing Shuttle software with only subtle
changes. However, the increases in memory and processing speed allow
for future innovations in the Shuttle's data processing system.
Although there is no real difference in the way the crew will operate
with the new computers, the upgrade increases the reliability and
efficiency in commanding the Shuttle systems. The predicted "mean time
between failures" (MTBF) for the advanced GPCs is 6,000 hours. The MTBF
for the original GPCs is 5,200 hours.
Specifications
Dimensions: 19.55" x 7.62" x 10.2"
Weight: 64 lbs
Memory capacity: 262,000 words (32-bits each)
Processing rate: 1 million instructions per second
Power requirements: 550 watts
STS-39 MISSION OVERVIEW
The STS-39 mission is comprised of two primary payloads: Air Force
Program 675 (AFP-675) and the Strategic Defense Initiative's (SDIO)
Infrared Background Signature Survey (IBSS).
There also are two secondary payloads; Space Test Payload (STP-1) and
a Multi-Purpose Experiment Canister (MPEC). Two mid-deck experiments,
CLOUDS-1A and RME III, are included on the STS-39 mission. IBSS and
AFP-675 have scheduled observing time throughout the mission with a
small amount of dedicated time for both STP-1 and MPEC on the last day
of the mission.
The AFP-675 payload is sponsored by SDIO and Air Force Systems
Command's Space Systems Division (SSD). It contains three experiments
sponsored by the Phillips Laboratory's Geophysics Directorate, by the
Naval Research Laboratory, and by the Los Alamos National Laboratory,
respectively. The prime integration contractor for the payload is
Lockheed Missiles and Space Company, Inc. AFP-675 is a unique
demonstration of the ability to command, control and evaluate a system of
experiments without ground commands or telemetry data. Voice (although
not necessary) will be included on this mission for communication
between the crew and the ground to discuss the experiments.
The AFP-675 payload will remain in the payload bay during the mission,
and commanding of the experiments will be accomplished by the crew
from a panel in the aft flight deck. The experiments will be measuring
infrared, ultraviolet, visible and X-ray emissions. One of the important
observations for the mission is the aurora. The launch date and time were
chosen to assure visibility of the aurora.
SDIO's IBSS payload is composed of three separate systems, the Shuttle
Pallet Satellite (SPAS-II), the Critical Ionization Velocity (CIV) system
and the Chemical Release Observation (CRO) experiment. SDIO has program
management responsibility. The SPAS-II was developed by
Messerschmitt-Bolkow-Blohm (MBB). The CIV portion is managed by the
Geophysics Directorate, and the CRO portion is managed by the Western
Space Technology Center. Mission operations are managed by SSD.
The SPAS-II structure supports a cryogenically cooled infrared sensor, an
ultraviolet multispectral sensor and low light level television cameras.
The SPAS-II will be deployed and maneuvered to observe various targets
and can be commanded by the on-board crew or by the ground.
The CRO is composed of three separate subsatellite structures that
will be deployed and will release chemicals upon ground command to be
observed by the SPAS infrared sensors. Each subsatellite is loaded with a
different chemical. The CIV structure is composed of four separate gas
canisters which remain attached to the orbiter and will release gas upon
command to be observed by the SPAS sensors. Each cylinder is loaded
with a different gas; xenon, neon, carbon dioxide and nitrous oxide.
SSD sponsors the STP-1 payload which is a standard Goddard Space
Flight Center (GSFC) Hitchhiker structure supporting five experiments.
Experiments are sponsored by the Naval Research Laboratory, the Rocket
Propulsion Directorate of the Phillips Laboratory, the Geophysics
Directorate, GSFC, and SSD.
STP-1 remains in the cargo bay and is commanded from a control center
at Goddard Space Flight Center. The UVLIM experiment will collect
airglow measurements, ALFE will evaluate advanced propellant
management systems, and SKIRT will collect infrared, visible and
ultraviolet data on Shuttle glow. DSE will test advanced data management
concepts, and APM will collect particles to study particulate
contamination in the Shuttle bay.
MPEC is a multipurpose experiment cannister sponsored by SSD. The
MPEC will deploy a classified experiment on the last day of the mission.
There are two mid-deck experiments on the STS-39 mission. The
CLOUDS-1A experiment will study cloud cover, and the RME-III experiment
will measure ionizing radiation exposure in the orbiter cabin.
AIR FORCE PAYLOAD-675
Cryogenic Infrared Radiance Instrumentation for Shuttle
(CIRRIS-1A)
The CIRRIS instrument is sponsored by the Strategic Defense Initiative
Organization (SDIO), and program responsibility is under the Phillips
Laboratory's Geophysics Directorate at Hanscom Air Force Base, Md. The
sensor prime contractor is Utah State University with major
subcontractors Space Data Corporation, Sensor System Group and Boston
College.
CIRRIS-1A is the highest priority experiment being flown on the AFP-
675 space vehicle. The experiment is designed to be operated by
Discovery's crew from a command panel in the aft flight deck.
The experiment operates in the infrared portion of the electromagnetic
spectrum (wavelength between 2.5 to 25 micro-meters). The experiment
will obtain simultaneous spectral and spatial measurements of airglow
and auroral emissions.
The data obtained from the mission should help answer questions
regarding the optimum atmospheric windows for detecting cold body
targets, the background radiance levels in various regions, the spatial
structure (clutter) of the background, and the variability of Earth limb
emissions during day/night airglow and auroral events. This information
will help DOD design surveillance systems.
There is a low light level television co-aligned on the sensor telescope
which can be used by the crew to acquire and track the auroral displays
and celestial calibration targets.
One primary mission objective is to measure the spectral and spatial
characteristics of auroral emissions. The pre-midnight/midnight sector
of the Northern and Southern auroral oval is expected to exhibit the most
intense infrared emissions and therefore, is of particular interest. An
auroral watch will be maintained by a network of ground personnel to
monitor the level of auroral activity. In the event of an intense auroral
display, this team would alert Discovery's crew of the location and
intensity of the aurora.
Earth limb emissions will be collected covering a range of altitudes,
latitudes, day/night and geomagnetic conditions.
To provide a radiometric calibration of the infrared sensors, certain
known celestial sources will be measured during the mission.
Discovery will be maneuvered to provide the proper attitude for
observations and to provide the required scanning and pointing capability.
The sensor is mounted on a two-axis gimbal.
Gravity gradient is the primary attitude for CIRRIS-1A data collection.
It is the only attitude maintainable by the orbiter without the use of the
reaction control system which produces unacceptable contaminates.
Aurora Details
Aurora are created by solar activity. When a solar flare, sun spot or
coronal hole occurs within a particular area of the sun's disk, an increased
number of energetic particles is directed towards the Earth. As the solar
wind accelerates with the Earth's magnetosphere, a generator effect is
produced which accelerates electrons down the Earth's magnetic field
lines. As these electrons impinge upon the Earth's atmosphere, oxygen and
nitrogen are excited and ionized to produce aurorae. The aurorae emit
visible, ultraviolet, infrared and radio frequencies. Because the electrons
precipitate down the geomagnetic field lines, aurorae are produced in an
oval shaped zone roughly centered around the magnetic pole regions of the
North and South poles.
The shape and size of the oval is dependent on the intensity of the
solar wind. The intensity of the aurora within the oval is variable. The
objective of the mission is to observe an extremely active aurora. The
two primary indicators for predicting when an active aurora might appear
are solar activity and geomagnetic disturbance. These events will both be
monitored during the mission.
A ground station magnetometer network and Defense Meteorological
Satellite Program (DMSP) satellite coverage will be utilized to detect
whether an active aurora is in progress. This network is located in the
Northern Hemisphere and will collect simultaneous scientific
measurements as well as provide a near realtime detection capability.
The southern aurora is a mirror image of the northern aurora. If there is
an active northern aurora then the southern aurora also will be active.
FAR Ultraviolet Cameras (FAR UV)
The FAR Ultraviolet Cameras experiment is sponsored by the Naval
Research Laboratory. The hardware is a part of the AFP-675 payload. The
instrumentation consists of two electrographic Schmidt cameras. A
course-pointing two axis gimbal platform and a low light level TV camera
for finding the objects and guiding the instrument. The instrument also
has a stabilization system for long exposures on celestial objects. The
instrument weighs approximately 550 pounds and the dimensions are
approximately 60" x 32" x 20".
The cameras will record naturally-occurring and man-made emission
phenomena in near-Earth space in the 1050-1600 angstroms (A) and 1230-
2000A wavelength ranges. The phenomena of interest include day and
night airglow, diffuse aurorae and the orbiter environment. Of particular
interest is the orbiter thruster and surface glow effects.
The experiment also will make observations of interplanetary and
interstellar media, stars, extragalactic objects, effects of chemical
deposition and atmospheric density measurements by stellar occultation.
Each camera has a film transport loaded with 150 feet of film yielding
up to 900 frames of data. The gimbaled platform allows pointing of FAR
UV to be somewhat independent of orbiter attitude. The outer gimbal can
travel between +/- 80 degrees and the inner gimbal can travel between
+/- 22 degrees.
The experiment is commanded by a crew member who views the TV
monitor to determine where the camera is pointing as he moves the
camera into position.
The sun sensor is an array of silicon solar cells which outputs a
voltage of 5 volts in full sunlight. As the output from the sun sensor in
excess of 3 volts indicates the sun is shining into the payload bay and
hence, the FAR UV high voltage must be turned off and the doors closed.
The terrestrial atmospheric observations include northern and southern
diffuse aurora, snapshot views of discrete aurora, night airglow with
attention to the tropical arcs and twilight airglow. Stellar occultation
observations will occur concurrent with airglow observations. Any unique
phenomena such as meteor showers should be noted if they occur in
airglow or aurora viewing periods.
The celestial target observations include the diffuse nebulae, diffuse
galactic background, star fields at high and low galactic latitudes, and
also nearby external galaxies.
The primary Shuttle environment events are the primary RCS
and OMS thruster firings (in daylight and dark) and Shuttle
glow. Secondary interests are Shuttle contamination effects such
as fuel cell purges, flash evaporator events and water dumps.
Uniformly Redundant Array (URA)
The URA experiment is sponsored by the Department of Energy and Los
Alamos National Laboratory.
The URA is designed to conduct studies of astrophysical sources of
X-ray radiation. The instrument, a part of the AFP-675 payload, is an
assembly consisting of a detector, a 35mm camera and an electronics
package. The aperture plate of the detector contains over 26,000
hexagonal holes to collect the X-ray photons. Objects will be selected to
test the capability of the URA to image point sources, complex collections
of point sources and extended objects. The instrument will be operated
both in a staring and slow scan mode. The URA experiment will be
controlled by a mission specialist via the CMP (Command and Monitor
Panel).
The URA must not only detect X-rays of interest but must also suppress
detection of particles that are present as background. The backgrounds of
concern are mainly cosmic rays (relativistic protons and alpha particles)
and charged particles (electrons above a 50 keV energy) trapped by the
Earth's magnetic field. Because such particles penetrate the detector
walls or window, the backgrounds are rejected by anti-coincidence,
second moment and rise time discrimination techniques.
The extended charge distribution from an energetic charged particle, as
opposed to an X-ray photon, produces a slower amplifier pulse because it
is collected over a finite period of time. Rise time discrimination is thus
an independent means of background rejection.
Despite the background rejection provisions, URA will not operate
usefully at high levels of background. Cosmic ray background is less at
low latitude and altitude because of the shielding effect of the Earth's
magnetic field. X-ray experiments are not successful in high background
regions, which are found at high altitude, and high magnetic latitude, and
in the South Atlantic Anomaly. Low altitude, low latitude will increase
the success of the URA observations.
Horizon Ultraviolet Program (HUP)
The HUP is an AF Geophysics Laboratory experiment to demonstrate a
capability to measure the spatial and spectral characteristics of the
Earth's horizon as observed in the ultraviolet wavelength region and to
analyze Shuttle contamination.
The instrument weighs less than 40 pounds and is approximately 15" x
21" x 9". The ultraviolet instrument is smaller and does not require
cooling like the infrared instruments. The experiment runs continuously
during the mission. The line of sight of the instrument is in the -Z
direction, vertically out of the Shuttle bay.
The telescope assembly is pivoted about an axis which enables the field
of view to vary from local horizontal to a few degrees below the hard
Earth horizon. Data will be collected using continuous angle scans at a
series of wavelengths in the range of 1100-1900 A, continuous
wavelength scans in a fixed direction and a fixed wavelength fixed
direction.
To prevent damage from the sun, a solar protection sensor closes the
spectrometer shutter when the sun is within 3 degrees of the line of
sight. The spectrometer then automatically starts a calibration cycle and
resumes data taking when the sun is no longer in the field of view.
The HUP instrument will measure the atmospheric radiance as a
function of tangent altitude. The horizon limb profiles are necessary to
develop attitude sensors for spacecraft and to obtain backgrounds for
above the horizon missile detection techniques. The radiance is due to
solar scattering, airglow and auroral excitation. Contamination of the
orbiter environment also will be measured.
The experiment should yield data radiation backgrounds from the
airglow and aurora Earth limb measurements, and information on
variability and clutter in the atmosphere.
Quadrupole Ion-Neutral Mass Spectrometer (QINMS)
The QINMS experiment is sponsored by the Phillips Laboratory's
Geophysics Directorate. The mass spectrometer instrument weighs
approximately 28 pounds. The hardware, part of the AFP-675 payload, is
mounted to the ESS and does not gimbal.
The primary role of QINMS is to support CIRRIS by measuring the
amount and nature of orbiter bay contamination, particularly water
concentration. CIRRIS will not be operated until contamination levels are
low.
QINMS will collect data continuously throughout the flight with
operations controlled by a Mission Specialist via the CMP.
Data also will be collected while passing through the auroral zone and
polar latitude. Levels of hydrogen, oxygen, water vapor and other gases
will be measured.
INFRARED BACKGROUND SIGNATURE SURVEY (IBSS)
IBSS Overview
Infrared Background Signature Survey is a Strategic Defense Initiative
Organization sponsored program for the purpose of obtaining scientific
data for use in the development of ballistic missile defense sensor
systems.
IBSS is composed of three separate elements: the Shuttle Pallet
Satellite II (SPAS -II), the Critical Ionization Velocity (CIV) package, and
the Chemical Release Observation (CRO) experiment. In addition to
sponsoring the program, SDIO also manages the overall program.
Supporting SDIO in program management are several systems engineering
and technical analysis firms, including: Stears, Kiya and Wright of
Arlington, Va; Orbital Systems Limited of Lanham, Md; Nichols Research
Corp. of Vienna, Va., and Hernandez Engineering Inc. of Houston, Tex. The
SPAS-II hardware is developed and manufactured by Messerschmitt-
Bolkow-Blohm GmbH of Munich, Germany. Mounted on the SPAS-II are two
sensor systems: an infrared spectrometer/radiometer built by Kayser-
Threde of Germany housed in cryostat (cryogenically cooled instrument
chamber) built by Linde of Germany and a multispectral Arizona
Imager/Spectrograph (AIS) built by the University of Arizona at Tucson,
Ariz.
Shuttle Pallet Satellite II (SPAS-II)
The SPAS-II element incorporates a liquid helium cooled infrared
sensor, the Arizona Imager/Spectrograph (AIS) multispectral sensor, two
low light level television cameras and various support subsystems on a
modular graphite-epoxy structure. SPAS-II will be deployed from the
orbiter using the Remote Manipulator System (RMS) and will maneuver at
ranges of up to 20 km from the orbiter to gather spectral and spatial data
during several experiments.
Chemical Release Observation (CRO)
The Chemical Release Observation (CRO) portion of the Infrared
Background Signature Survey (IBSS) mission is an experiment designed to
collect infrared, visible and ultraviolet time-resolved radiometric data
associated with the release of liquid rocket propellants in near Earth
orbit. The experiment is composed of three separate subsatellites
containing chemicals and their launchers.
Since the three chemical releases will produce short-lived clouds of
vapor and frozen particles in orbit near the Shuttle, it is possible that a
faint glow of visible light may occur due to the interaction of the vapor
cloud with oxygen atoms in the upper atmosphere. It is not expected,
however, that the vapor glow from any of the releases will be bright
enough to be detected by the unaided eye on the ground. The chances of
observers near Vandenberg seeing the first and only nighttime scheduled
release experiment are very remote.
The cloud of frozen particles, however, can scatter sunlight producing
visible light with much greater intensity. The sunlight scattered from the
particle cloud will not be as intense as the daytime sky, however, so it is
unlikely that either the second or third release can be viewed from the
ground for the scheduled launch and mission time line. If the launch is
delayed a couple of hours, however, the first scheduled release could
occur under pre-dawn twilight conditions on the west coast. This
situation would provide optimal viewing conditions as the release would
occur in sunlight while a west coast observer would be in darkness. Under
these conditions, the release would initially appear as a disk of white
light approximately the size of the full moon (though somewhat dimmer).
The cloud will continue to grow and gradually dim after the flow of liquid
ends. The remnants of the bright cloud will only persist for a few
minutes.
CRO Management
The CRO element is managed by the Air Force Space Technology Center
from their West Coast (Los Angeles) office. The CRO subsatellites and
launcher mechanisms are designed and manufactured by Defense Systems
Inc,. of McLean, Va, while the launcher cylinders and support beams are
provided by NASA/Goddard Space Flight Center at Greenbelt, Md.
Subsatellite ground control and telemetry is provided by USAF 6595th
Test & Evaluation Group and the Western Test Range at Vandenberg AFB,
Calif., supported by Federal Electric Corp. Aircraft sensor platform
operations for collecting CRO data in the VAFB area are provided by the
HALO aircraft, operated by Phillips Laboratory's Weapons Directorate and
4950th Test Group at Kirtland AFB, N.M., supported by BDM Corp. of
Albuquerque, N.M.
IBSS mission integration, launch site operations and payload flight
operations are managed by the Space Systems Division, Air Force Systems
Command, supported by The Aerospace Corporation and Rockwell
International Space Division.
Critical Ionization Velocity (CIV)
The Critical Ionization Velocity experiment will investigate the
interaction of neutral gases with the ambient weakly-magnetized plasma.
The CIV element includes four compressed gas canisters (xenon, neon,
carbon dioxide and nitrous oxide) which release plumes of the gas out of
the orbiter bay upon crew command. The plumes are then observed by the
SPAS-II sensors at different orientations to the orbiter's direction of
travel and the local geomagnetic lines of force. The CIV hardware weighs
about 500 lbs.
Kinetic energy of the gas will exceed its ionization potential due to
its relative velocity with the ambient plasma. The resulting plasma
instability is expected to enhance ionization. Charge exchange between
the gases released and ambient ions (mainly oxygen) is expected to
produce other ions.
Both mechanisms can lead to the release of radiation. Therefore,
radiation in the infrared, visible and ultraviolet bands will be collected by
the sensors from the deployed SPAS-II. The CIV experiment also has a
data acquisition package, its radiometers will measure both visible and
ultraviolet radiation from the payload bay. The CIV experiment, in the
payload bay, has a Langmuir probe which will measure the ambient
electron density and temperature.
Four different gases have been selected, and the release mechanism
was designed such that the critical ionization velocity should be reached
for three of the four gases when they are released in the RAM direction.
Because the orientation and strength of the local magnetic field is
expected to affect the intensity of the ionization phenomenon, the gas
releases will be observed both when the local magnetic field is
approximately parallel to RAM and when it is perpendicular to RAM. The
effect of ambient electron density on the phenomenon will be observed by
repeating the observations in both the daylight and darkness.
Four observations are planned with the SPAS-II deployed at a location
near the Orbiter. Lighting and magnetic field orientation will be varied to
produce four unique observations.
CIV Management
The CIV element is managed by Geophysics Laboratory/Space Physics
Division at Hanscom AFB, Mass. Supporting contractors include:
Physical Sciences Inc., Andover, Mass. Gas Release System & System
Integration
Northeastern University, Boston, Mass. Payload Support System
Manufacturer
Wentworth Inst. of Tech, Boston, Mass. General Mechanical Mfg.
John Hopkins University, Baltimore, Md. Pressure Gauge Subsystems
Research Science Inc., Washington, D.C. Radiometer Subsystem
University of Iowa, Iowa City, Iowa Langmuir Probe
IBSS Objectives
The Infrared Background Signature Survey is a Strategic Defense
Initiative Organization sponsored program for the purpose of obtaining
scientific data for use in the development of ballistic missile defense
sensor systems. The IBSS mission will involve the collection of infrared,
ultraviolet and visible measurements of natural and induced geophysical
phenomena.
Using the SPAS-II sensors at various ranges from the orbiter, spectral,
spatial and temporal radiometric observations will be made of the exhaust
plumes when the orbiter's orbital maneuvering systems (OMS) fires and
creates replications of ICBM booster and midcourse engine firings.