2327 lines
92 KiB
Plaintext
2327 lines
92 KiB
Plaintext
STS-34 PRESS KIT
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CONTENTS
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GALILEO
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GALILEO MISSION EVENTS
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EARTH TO JUPITER
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VENUS
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FIRST EARTH PASS
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FIRST ASTEROID
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SECOND EARTH PASS
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SECOND ASTEROID
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APPROACHING JUPITER
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AT JUPITER
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The probe at Jupiter
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The orbiter at Jupiter
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SCIENTIFIC ACTIVITIES
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Spacecraft scientific activities
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Probe scientific activities
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Orbiter scientific activities
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GROUND SYSTEMS
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SPACECRAFT CHARACTERISTICS
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JUPITER'S SYSTEM
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WHY JUPITER INVESTIGATIONS ARE IMPORTANT
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GALILEO MANAGEMENT
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GALILEO ORBITER AND PROBE SCIENTIFIC INVESTIGATIONS
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STS-34 INERTIAL UPPER STAGE (IUS-19)
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Specifications
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Airborne Support Equipment
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IUS Structure
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Equipment Support Section
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IUS Avionics Subsystems
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IUS Solid Rocket Motors
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Reaction Control System
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IUS to Spacecraft Interfaces
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Flight Sequence
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SHUTTLE SOLAR BACKSCATTER ULTRAVIOLET INSTRUMENT (SSBUV)
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GROWTH HORMONE CONCENTRATIONS AND DISTRIBUTION IN PLANTS
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POLYMER MORPHOLOGY
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GENERAL RELEASE
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RELEASE: 89-151
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SHUTTLE ATLANTIS TO DEPLOY GALILEO PROBE TOWARD JUPITER
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Space Shuttle mission STS-34 will deploy the Galileo planetary
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exploration spacecraft into low-Earth orbit starting Galileo on its journey
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to explore Jupiter. Galileo will be the second planetary probe deployed
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from the Shuttle this year following Atlantis' successful launch of
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Magellan toward Venus exploration in May.
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Following deployment about 6 hours after launch, Galileo will be
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propelled on a trajectory, known as Venus-Earth-Earth Gravity Assist
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(VEEGA) by an Air Force-developed, inertial upper stage (IUS). Galileo's
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trajectory will swing around Venus, the sun and Earth before Galileo
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makes it's way toward Jupiter.
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Flying the VEEGA track, Galileo will arrive at Venus in February 1990.
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During the flyby, Galileo will make measurements to determine the
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presence of lightning on Venus and take time-lapse photography of Venus'
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cloud circulation patterns. Accelerated by Venus' gravity, the spacecraft
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will head back to Earth.
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Enroute, Galileo will activate onboard remote-sensing equipment to
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gather near-infrared data on the composition and characteristics of the
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far side of Earth's moon. Galileo also will map the hydrogen distribution
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of the Earth's atmosphere.
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Acquiring additional energy from the Earth's gravitational forces,
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Galileo will travel on a 2-year journey around the sun spending 10 months
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inside an asteroid belt. On Oct. 29, 1991, Galileo wlll pass within 600
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miles of the asteroid Gaspra.
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On the second Earth flyby in December 1992, Galileo will photograph
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the north pole of the moon in an effort to determine if ice exists.
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Outbound, Galileo will activate the time-lapse photography system to
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produce a "movie" of the moon orbiting Earth.
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Racing toward Jupiter, Galileo will make a second trek through the
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asteroid belt passing within 600 miles of asteroid Ida on Aug. 29, 1993.
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Science data gathered from both asteroid encounters will focus on surface
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geology and composition.
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Five months prior to the Dec. 7, 1995, arrival at Jupiter, Galileo's
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atmospheric probe, encased in an oval heat shield, will spin away from the
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orbiter at a rate of 5 revolutions per minute (rpm) and follow a ballistic
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trajectory aimed at a spot 6 degrees north of Jupiter's equator. The probe
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will enter Jupiter's atmosphere at a shallow angle to avoid burning up like
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a meteor or ricocheting off the atmosphere back into space.
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At approximately Mach 1 speed, the probe's pilot parachute will deploy,
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removing the deceleration module aft cover. Deployment of the main
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parachute will follow, pulling the descent module out of the aeroshell to
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expose the instrument-sensing elements. During the 75-minute descent
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into the Jovian atmosphere, the probe will use the orbiter to transmit
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data back to Earth. After 75 minutes, the probe will be crushed under the
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heavy atmospheric pressure.
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The Galileo orbiter will continue its primary mission, orbiting around
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Jupiter and four of its satellites, returning science data for the next 22
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months.
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Galileo's scientific goals include the study of the chemical
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composition, state and dynamics of the Jovian atmosphere and satellites,
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and the investigation of the structure and physical dynamics of the
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powerful Jovian magnetosphere.
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Overall responsibility for management of the project, including orbiter
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development, resides at NASA's Jet Propulsion Laboratory, Pasadena,
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Calif. The NASA Ames Research Center, Mountain View, Calif., manages
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the probe system. JPL built the 2,500-lb. spacecraft and Hughes Aircraft
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Co. built the 740-lb. probe.
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Modifications made to Galileo since flight postponement in 1986
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include the addition of sunshields to the base and top of the antenna, new
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thermal control surfaces, blankets and heaters. Because of the extended
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length of the mission, the electrical circuitry of the thermoelectric
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generator has been revised to reduce power demand throughout the
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mission to assure adequate power supply for mission completion.
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Joining Galileo in the payload bay of Atlantis will be the Shuttle Solar
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Backscatter Ultraviolet (SSBUV) instrument. The SSBUV is designed to
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provide calibration of backscatter ultraviolet instruments currently being
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flown on free-flying satellites. SSBUV's primary objective is to check the
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calibration of the ozone sounders on satellites to verify the accuracy of
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the data set of atmospheric ozone and solar irradiance data.
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The SSBUV is contained in two Get Away Special canisters in the
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payload bay and weighs about 1219 lbs . One canister contains the SSBUV
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spectrometer and five supporting optical sensors. The second canister
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houses data, command and power systems. An interconnecting cable
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provides the communication link between the two canisters.
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The Galileo probe arrived at the Spacecraft Assembly and
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Encapsulation Facility (SAEF) 2 on April 17 and the spacecraft arrived on
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May 16. While at SAEF-2, the spacecraft and probe were joined and tested
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together to verify critical connections. Galileo was delivered to the
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Vertical Processing Facility (VPF) on Aug. 1. The Inertial Upper Stage
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(IUS) was delivered to the VPF on July 30. The Galileo/IUS were joined
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together on Aug. 3 and all integrated testing was performed during the
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second week of August.
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GALILEO
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Galileo is a NASA spacecraft mission to Jupiter to study the planet's
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atmosphere, satellites and surrounding magnetosphere. It was named for
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the Italian renaissance scientist who discovered Jupiter's major moons by
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using the first astronomical telescope.
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This mission will be the first to make direct measurements from an
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instrumented probe within Jupiter's atmosphere and the first to conduct
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long-term observations of the planet and its magnetosphere and satellites
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from orbit around Jupiter. It will be the first orbiter and atmospheric
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probe for any of the outer planets. On the way to Jupiter, Galileo also will
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observe Venus, the Earth-moon system, one or two asteroids and various
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phenomena in interplanetary space.
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Galileo will be boosted into low-Earth orbit by the Shuttle Atlantis and
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then boosted out of Earth orbit by a solid rocket Inertial Upper Stage. The
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spacecraft will fly past Venus and twice by the Earth, using gravity
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assists from the planets to pick up enough speed to reach Jupiter. Travel
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time from launch to Jupiter is a little more than 6 years.
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In December 1995, the Galileo atmospheric probe will conduct a brief,
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direct examination of Jupiter's atmosphere, while the larger part of the
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craft, the orbiter, begins a 22-month, 10-orbit tour of major satellites
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and the magnetosphere, including long-term observations of Jupiter
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throughout this phase.
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The 2-ton Galileo orbiter spacecraft carries 9 scientific instruments.
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There are another six experiments on the 750-pound probe. The spacecraft
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radio link to Earth serves as an additional instrument for scientific
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measurements. The probe's scientific data will be relayed to Earth by the
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orbiter during the 75-minute period while the probe is descending into
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Jupiter's atmosphere. Galileo will communicate with its controllers and
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scientists through NASAUs Deep Space Network, using tracking stations in
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California, Spain and Australia.
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GALILEO MISSION EVENTS
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Launch Window (Atlantis and IUS).....................Oct. 12 to Nov. 21, 1989
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(Note: for both asteroids, closes in mid-October)
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Venus flyby ( 9,300 mi).............................*Feb. 9, 1990
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Venus data playback..................................Oct. 1990
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Earth 1 flyby ( about 600 mi).......................*Dec. 8, 1990
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Asteroid Gaspra flyby (600 mi)......................*Oct. 29, 1991
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Earth 2 flyby (200 mi)..............................*Dec. 8, 1992
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Asteroid Ida flyby (600 mi).........................*Aug. 28, 1993
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Probe release........................................July 1995
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Jupiter arrival......................................Dec. 7, 1995
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(includes Io flyby, probe entry and relay, Jupiter orbit insertion)
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Orbital tour of Galilean satellites Dec '95-Oct '97
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*Exact dates may vary according to actual launch date
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EARTH TO JUPITER
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Galileo will make three planetary encounters in the course of its
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gravity-assisted flight to Jupiter. These provide opportunities for
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scientific observation and measurement of Venus and the Earth-moon
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system. The mission also has a chance to fly close to one or two
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asteroids, bodies which have never been observed close up, and obtain data
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on other phenomena of interplanetary space.
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Scientists are currently studying how to use the Galileo scientific
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instruments and the limited ability to collect, store and transmit data
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during the early phase of flight to make the best use of these
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opportunities. Instruments designed to observe Jupiter's atmosphere from
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afar can improve our knowledge of the atmosphere of Venus and sensors
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designed for the study of Jupiter's moons can add to our information about
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our own moon.
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VENUS
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The Galileo spacecraft will approach Venus early in 1990 from the
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night side and pass across the sunlit hemisphere, allowing observation of
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the clouds and atmosphere. Both infrared and ultraviolet spectral
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observations are planned, as well as several camera images and other
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remote measurements. The search for deep cloud patterns and for
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lightning storms will be limited by the fact that all the Venus data must
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be tape-recorded on the spacecraft for playback 8 months later.
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The spacecraft was originally designed to operate between Earth and
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Jupiter, where sunlight is 25 times weaker than at Earth and
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temperatures are much lower. The VEEGA mission will expose the
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spacecraft to a hotter environment from Earth to Venus and back.
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Spacecraft engineers devised a set of sunshades to protect the craft. For
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this system to work, the front end of the spacecraft must be aimed
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precisely at the Sun, with the main antenna furled for protection from the
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Sun's rays until after the first Earth flyby in December 1990. This
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precludes the use of the Galileo high-gain antenna and therefore,
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scientists must wait until the spacecraft is close to Earth to receive the
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recorded Venus data, transmitted through a low-gain antenna.
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FIRST EARTH PASS
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Approaching Earth for the first time about 14 months after launch, the
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Galileo spacecraft will observe, from a distance, the nightside of Earth
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and parts of both the sunlit and unlit sides of the moon. After passing
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Earth, Galileo will observe Earth's sunlit side. At this short range,
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scientific data are transmitted at the high rate using only the
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spacecraft's low-gain antennas. The high-gain antenna is to be unfurled
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like an umbrella, and its high-power transmitter turned on and checked
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out, about 5 months after the first Earth encounter.
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FIRST ASTEROID
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Nine months after the Earth passage and still in an elliptical solar
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orbit, Galileo will enter the asteroid belt, and two months later, will have
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its first asteroid encounter. Gaspra is believed to be a fairly
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representative main-belt asteroid, about 10 miles across and probably
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similar in composition to stony meteorites.
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The spacecraft will pass within about 600 miles at a relative speed of
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about 18,000 miles per hour. It will collect several pictures of Gaspra
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and make spectral measurements to indicate its composition and physical
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properties.
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SECOND EARTH PASS
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Thirteen months after the Gaspra encounter, the spacecraft will have
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completed its 2-year elliptical orbit around the Sun and will arrive back
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at Earth. It will need a much larger ellipse (with a 6-year period) to reach
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as far as Jupiter. The second flyby of Earth will pump the orbit up to that
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size, acting as a natural apogee kick motor for the Galileo spacecraft.
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Passing about 185 miles above the surface, near the altitude at which
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it had been deployed from the Space Shuttle almost three years earlier,
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Galileo will use Earth's gravitation to change the spacecraft's flight
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direction and pick up about 8,000 miles per hour in speed.
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Each gravity-assist flyby requires about three rocket-thrusting
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sessions, using Galileo's onboard retropropulsion module, to fine-tune the
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flight path. The asteroid encounters require similar maneuvers to obtain
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the best observing conditions.
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Passing the Earth for the last time, the spacecraft's scientific
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equipment will make thorough observations of the planet, both for
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comparison with Venus and Jupiter and to aid in Earth studies. If all goes
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well, there is a good chance that Galileo will enable scientists to record
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the motion of the moon about the Earth while the Earth itself rotates.
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SECOND ASTEROID
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Nine months after the final Earth flyby, Galileo may have a second
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asteroid-observing opportunity. Ida is about 20 miles across. Like
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Gaspra, Ida is believed to represent the majority of main-belt asteroids in
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composition, though there are believed to be differences between the two.
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Relative velocity for this flyby will be nearly 28,000 miles per hour, with
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a planned closest approach of about 600 miles.
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APPROACHING JUPITER
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Some 2 years after leaving Earth for the third time and 5 months
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before reaching Jupiter, Galileo's probe must separate from the orbiter.
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The spacecraft turns to aim the probe precisely for its entry point in the
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Jupiter atmosphere, spins up to 10 revolutions per minute and releases
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the spin-stabilized probe. Then the Galileo orbiter maneuvers again to
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aim for its own Jupiter encounter and resumes its scientific
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measurements of the interplanetary environment underway since the
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launch more than 5 years before.
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While the probe is still approaching Jupiter, the orbiter will have its
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first two satellite encounters. After passing within 20,000 miles of
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Europa, it will fly about 600 miles above Io's volcano-torn surface,
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twenty times closer than the closest flyby altitude of Voyager in 1979.
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AT JUPITER
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The Probe at Jupiter
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The probe mission has four phases: launch, cruise, coast and
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entry-descent. During launch and cruise, the probe will be carried by the
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orbiter and serviced by a common umbilical. The probe will be dormant
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during cruise except for annual checkouts of spacecraft systems and
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instruments. During this period, the orbiter will provide the probe with
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electric power, commands, data transmission and some thermal control.
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Six hours before entering the atmosphere, the probe will be shooting
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through space at about 40,000 mph. At this time, its command unit
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signals "wake up" and instruments begin collecting data on lightning, radio
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emissions and energetic particles.
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A few hours later, the probe will slam into Jupiter's atmosphere at
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115,000 mph, fast enough to jet from Los Angeles to New York in 90
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seconds. Deceleration to about Mach 1 -- the speed of sound -- should
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take just a few minutes. At maximum deceleration as the craft slows
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from 115,000 mph to 100 mph, it will be hurtling against a force 350
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times Earth's gravity. The incandescent shock wave ahead of the probe
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will be as bright as the sun and reach searing temperatures of up to
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28,000 degrees Fahrenheit. After the aerodynamic braking has slowed the
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probe, it will drop its heat shields and deploy its parachute. This will
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allow the probe to float down about 125 miles through the clouds, passing
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from a pressure of 1/10th that on Earth's surface to about 25 Earth
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atmospheres.
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About 4 minutes after probe entry into JupiterUs atmosphere, a pilot
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chute deploys and explosive nuts shoot off the top section of the probe's
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protective shell. As the cover whips away, it pulls out and opens the main
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parachute attached to the inner capsule. What remains of the probe's
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outer shell, with its massive heat shield, falls away as the parachute
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slows the instrument module.
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From there on, suspended from the main parachute, the probe's capsule
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with its activated instruments floats downward toward the bright clouds
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below.
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The probe will pass through the white cirrus clouds of ammonia
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crystals - the highest cloud deck. Beneath this ammonia layer probably lie
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reddish-brown clouds of ammonium hydrosulfides. Once past this layer,
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the probe is expected to reach thick water clouds. This lowest cloud layer
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may act as a buffer between the uniformly mixed regions below and the
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turbulent swirl of gases above.
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Jupiter's atmosphere is primarily hydrogen and helium. For most of its
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descent through Jupiter's three main cloud layers, the probe will be
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immersed in gases at or below room temperature. However, it may
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encounter hurricane winds up to 200 mph and lightning and heavy rain at
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the base of the water clouds believed to exist on the planet. Eventually,
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the probe will sink below these clouds, where rising pressure and
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temperature will destroy it. The probe's active life in Jupiter's
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atmosphere is expected to be about 75 minutes in length. The probe
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batteries are not expected to last beyond this point, and the relaying
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orbiter will move out of reach.
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To understand this huge gas planet, scientists must find out about its
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chemical components and the dynamics of its atmosphere. So far,
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scientific data are limited to a two-dimensional view (pictures of the
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planet's cloud tops) of a three-dimensional process (Jupiter's weather).
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But to explore such phenomena as the planet's incredible coloring, the
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Great Red Spot and the swirling shapes and high-speed motion of its
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topmost clouds, scientists must penetrate Jupiter's visible surface and
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investigate the atmosphere concealed in the deep-lying layers below.
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A set of six scientific instruments on the probe will measure, among
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other things, the radiation field near Jupiter, the temperature, pressure,
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density and composition of the planet's atmosphere from its first faint
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outer traces to the hot, murky hydrogen atmosphere 100 miles below the
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cloud tops. All of the information will be gathered during the probe's
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descent on an 8-foot parachute. Probe data will be sent to the Galileo
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Orbiter 133,000 miles overhead then relayed across the half billion miles
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to Deep Space Network stations on Earth.
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To return its science, the probe relay radio aboard the orbiter must
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automatically acquire the probe signal below within 50 seconds, with a
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success probability of 99.5 percent. It must reacquire the signal
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immediately should it become lost.
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To survive the heat and pressure of entry, the probe spacecraft is
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composed of two separate units: an inner capsule containing the
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scientific instruments, encased in a virtually impenetrable outer shell.
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The probe weighs 750 pounds. The outer shell is almost all heat shield
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material.
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The Orbiter at Jupiter
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After releasing the probe, the orbiter will use its main engine to go
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into orbit around Jupiter. This orbit, the first of 10 planned, will have a
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period of about 8 months. A close flyby of Ganymede in July 1996 will
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shorten the orbit, and each time the Galileo orbiter returns to the inner
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zone of satellites, it will make a gravity-assist close pass over one or
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another of the satellites, changing Galileo's orbit while making close
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observations. These satellite encounters will be at altitudes as close as
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125 miles above their surfaces. Throughout the 22-month orbital phase,
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Galileo will continue observing the planet and the satellites and continue
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gathering data on the magnetospheric environment.
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SCIENTIFIC ACTIVITIES
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Galileo's scientific experiments will be carried out by more than 100
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scientists from six nations. Except for the radio science investigation,
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these are supported by dedicated instruments on the Galileo orbiter and
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probe. NASA has appointed 15 interdisciplinary scientists whose studies
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include data from more than one Galileo instrument.
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The instruments aboard the probe will measure the temperatures and
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pressure of Jupiter's atmosphere at varying altitudes and determine its
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chemical composition including major and minor constituents (such as
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hydrogen, helium, ammonia, methane, and water) and the ratio of hydrogen
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to helium. Jupiter is thought to have a bulk composition similar to that of
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the primitive solar nebula from which it was formed. Precise
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determination of the ratio of hydrogen to helium would provide an
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important factual check of the Big Bang theory of the genesis of the
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universe.
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Other probe experiments will determine the location and structure of
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Jupiter's clouds, the existence and nature of its lightning, and the amount
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of heat radiating from the planet compared to the heat absorbed from
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sunlight.
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In addition, measurements will be made of Jupiter's numerous radio
|
|
emissions and of the high-energy particles trapped in the planet's
|
|
innermost magnetic field. These measurements for Galileo will be made
|
|
within a distance of 26,000 miles from Jupiter's cloud tops, far closer
|
|
than the previous closest approach to Jupiter by Pioneer 11. The probe
|
|
also will determine vertical wind shears using Doppler radio
|
|
measurements made of probe motions from the radio receiver aboard the
|
|
orbiter.
|
|
|
|
Jupiter appears to radiate about twice as much energy as it receives
|
|
from the sun and the resulting convection currents from Jupiter's internal
|
|
heat source towards its cooler polar regions could explain some of the
|
|
planet's unusual weather patterns.
|
|
|
|
Jupiter is over 11 times the diameter of Earth and spins about two and
|
|
one-half times faster -- a jovian day is only 10 hours long. A point on the
|
|
equator of Jupiter's visible surface races along at 28,000 mph. This rapid
|
|
spin may account for many of the bizarre circulation patterns observed on
|
|
the planet.
|
|
|
|
|
|
Spacecraft Scientific Activities
|
|
|
|
The Galileo mission and systems were designed to investigate three
|
|
broad aspects of the Jupiter system: the planet's atmosphere, the
|
|
satellites and the magnetosphere. The spacecraft is in three segments to
|
|
focus on these areas: the atmospheric probe; a non-spinning section of the
|
|
orbiter carrying cameras and other remote sensors; and the spinning main
|
|
section of the orbiter spacecraft which includes the propulsion module,
|
|
the communications antennas, main computers and most support systems
|
|
as well as the fields and particles instruments, which sense and measure
|
|
the environment directly as the spacecraft flies through it.
|
|
|
|
|
|
Probe Scientific Activities
|
|
|
|
The probe will enter the atmosphere about 6 degrees north of the
|
|
equator. The probe weighs just under 750 pounds and includes a
|
|
deceleration module to slow and protect the descent module, which
|
|
carries out the scientific mission.
|
|
|
|
The deceleration module consists of an aeroshell and an aft cover
|
|
designed to block the heat generated by slowing from the probe's arrival
|
|
speed of about 115,000 miles per hour to subsonic speed in less than 2
|
|
minutes. After the covers are released, the descent module deploys its
|
|
8-foot parachute and its instruments, the control and data system, and
|
|
the radio-relay transmitter go to work.
|
|
|
|
Operating at 128 bits per second, the dual L-band transmitters send
|
|
nearly identical streams of scientific data to the orbiter. The probe's
|
|
relay radio aboard the orbiter will have two redundant receivers that
|
|
process probe science data, plus radio science and engineering data for
|
|
transmission to the orbiter communications system. Minimum received
|
|
signal strength is 31 dBm. The receivers also measure signal strength and
|
|
Doppler shift as part of the experiments for measuring wind speeds and
|
|
atmospheric absorption of radio signals.
|
|
|
|
Probe electronics are powered by long-life, high-discharge-rate
|
|
34-volt lithium batteries, which remain dormant for more than 5 years
|
|
during the journey to Jupiter. The batteries have an estimated capacity of
|
|
about 18 amp-hours on arrival at Jupiter.
|
|
|
|
|
|
Orbiter Scientific Activities
|
|
|
|
The orbiter, in addition to delivering the probe to Jupiter and relaying
|
|
probe data to Earth, will support all the scientific investigations of
|
|
Venus, the Earth and moon, asteroids and the interplanetary medium,
|
|
Jupiter's satellites and magnetosphere, and observation of the giant
|
|
planet itself.
|
|
|
|
The orbiter weighs about 5,200 pounds including about 2,400 pounds of
|
|
rocket propellant to be expended in some 30 relatively small maneuvers
|
|
during the long gravity-assisted flight to Jupiter, the large thrust
|
|
maneuver which puts the craft into its Jupiter orbit, and the 30 or so trim
|
|
maneuvers planned for the satellite tour phase.
|
|
|
|
The retropropulsion module consists of 12 10-newton thrusters, a
|
|
single 400-newton engine, and the fuel, oxidizer, and pressurizing-gas
|
|
tanks, tubing, valves and control equipment. (A thrust of 10 newtons
|
|
would support a weight of about 2.2 pounds at Earth's surface). The
|
|
propulsion system was developed and built by
|
|
Messerschmitt-Bolkow-Blohm and provided by the Federal Republic of
|
|
Germany.
|
|
|
|
The orbiter's maximum communications rate is 134 kilobits per second
|
|
(the equivalent of about one black-and-white image per minute); there are
|
|
other data rates, down to 10 bits per second, for transmitting engineering
|
|
data under poor conditions. The spacecraft transmitters operate at
|
|
S-band and X-band (2295 and 8415 megahertz) frequencies between Earth
|
|
and on L-band between the probe.
|
|
|
|
The high-gain antenna is a 16-foot umbrella-like reflector unfurled
|
|
after the first Earth flyby. Two low-gain antennas (one pointed forward
|
|
and one aft, both mounted on the spinning section) are provided to support
|
|
communications during the Earth-Venus-Earth leg of the flight and
|
|
whenever the main antenna is not deployed and pointed at Earth. The
|
|
despun section of the orbiter carries a radio relay antenna for receiving
|
|
the probe's data transmissions.
|
|
|
|
Electrical power is provided to Galileo's equipment by two radioisotope
|
|
thermoelectric generators. Heat produced by natural radioactive decay of
|
|
plutonium 238 dioxide is converted to approximately 500 watts of
|
|
electricity (570 watts at launch, 480 at the end of the mission) to operate
|
|
the orbiter equipment for its 8-year active period. This is the same type
|
|
of power source used by the Voyager and Pioneer Jupiter spacecraft in
|
|
their long outer-planet missions, by the Viking lander spacecraft on Mars
|
|
and the lunar scientific packages left on the Moon.
|
|
|
|
Most spacecraft are stabilized in flight either by spinning around a
|
|
major axis or by maintaining a fixed orientation in space, referenced to
|
|
the sun and another star. Galileo represents a hybrid of these techniques,
|
|
with a spinning section rotating ordinarily at 3 rpm and a "despun" section
|
|
which is counter-rotated to provide a fixed orientation for cameras and
|
|
other remote sensors.
|
|
|
|
Instruments that measure fields and particles, together with the main
|
|
antenna, the power supply, the propulsion module, most of the computers
|
|
and control electronics, are mounted on the spinning section. The
|
|
instruments include magnetometer sensors mounted on a 36-foot boom to
|
|
escape interference from the spacecraft; a plasma instrument detecting
|
|
low-energy charged particles and a plasma-wave detector to study waves
|
|
generated in planetary magnetospheres and by lightning discharges; a
|
|
high-energy particle detector; and a detector of cosmic and Jovian dust.
|
|
|
|
The despun section carries instruments and other equipment whose
|
|
operation depends on a fixed orientation in space. The instruments include
|
|
the camera system; the near-infrared mapping spectrometer to make
|
|
multispectral images for atmosphere and surface chemical analysis; the
|
|
ultraviolet spectrometer to study gases and ionized gases; and the
|
|
photopolarimeter radiometer to measure radiant and reflected energy. The
|
|
camera system is expected to obtain images of Jupiter's satellites at
|
|
resolutions from 20 to 1,000 times better than Voyager's best.
|
|
|
|
This section also carries a dish antenna to track the probe in Jupiter's
|
|
atmosphere and pick up its signals for relay to Earth. The probe is carried
|
|
on the despun section, and before it is released, the whole spacecraft is
|
|
spun up briefly to 10 rpm in order to spin-stabilize the probe.
|
|
|
|
The Galileo spacecraft will carry out its complex operations, including
|
|
maneuvers, scientific observations and communications, in response to
|
|
stored sequences which are interpreted and executed by various on-board
|
|
computers. These sequences are sent up to the orbiter periodically
|
|
through the Deep Space Network in the form of command loads.
|
|
|
|
|
|
GROUND SYSTEMS
|
|
|
|
Galileo communicates with Earth via NASA's Deep Space Network
|
|
(DSN), which has a complex of large antennas with receivers and
|
|
transmitters located in the California desert, another in Australia and a
|
|
third in Spain, linked to a network control center at NASAUs Jet Propulsion
|
|
Laboratory in Pasadena, Calif. The spacecraft receives commands, sends
|
|
science and engineering data, and is tracked by Doppler and ranging
|
|
measurements through this network.
|
|
|
|
At JPL, about 275 scientists, engineers and technicians, will be
|
|
supporting the mission at launch, increasing to nearly 400 for Jupiter
|
|
operations including support from the German retropropulsion team at
|
|
their control center in the FGR. Their responsibilities include spacecraft
|
|
command, interpreting engineering and scientific data from Galileo to
|
|
understand its performance, and analyzing navigation data from the DSN.
|
|
The controllers use a set of complex computer programs to help them
|
|
control the spacecraft and interpret the data.
|
|
|
|
Because the time delay in radio signals from Earth to Jupiter and back
|
|
is more than an hour, the Galileo spacecraft was designed to operate from
|
|
programs sent to it in advance and stored in spacecraft memory. A single
|
|
master sequence program can cover 4 weeks of quiet operations between
|
|
planetary and satellite encounters. During busy Jupiter operations, one
|
|
program covers only a few days. Actual spacecraft tasks are carried out
|
|
by several subsystems and scientific instruments, many of which work
|
|
from their own computers controlled by the main sequence.
|
|
|
|
Designing these sequences is a complex process balancing the desire to
|
|
make certain scientific observations with the need to safeguard the
|
|
spacecraft and mission. The sequence design process itself is supported
|
|
by software programs, for example, which display to the scientist maps of
|
|
the instrument coverage on the surface of an approaching satellite for a
|
|
given spacecraft orientation and trajectory. Notwithstanding these aids,
|
|
a typical 3-day satellite encounter may take efforts spread over many
|
|
months to design, check and recheck. The controllers also use software
|
|
designed to check the command sequence further against flight rules and
|
|
constraints.
|
|
|
|
The spacecraft regularly reports its status and health through an
|
|
extensive set of engineering measurements. Interpreting these data into
|
|
trends and averting or working around equipment failures is a major task
|
|
for the mission operations team. Conclusions from this activity become
|
|
an important input, along with scientific plans, to the sequence design
|
|
process. This too is supported by computer programs written and used in
|
|
the mission support area.
|
|
|
|
Navigation is the process of estimating, from radio range and Doppler
|
|
measurements, the position and velocity of the spacecraft to predict its
|
|
flight path and design course-correcting maneuvers. These calculations
|
|
must be done with computer support. The Galileo mission, with its
|
|
complex gravity-assist flight to Jupiter and 10 gravity-assist satellite
|
|
encounters in the Jovian system, is extremely dependent on consistently
|
|
accurate navigation.
|
|
|
|
In addition to the programs that directly operate the spacecraft and
|
|
are periodically transmitted to it, the mission operations team uses
|
|
software amounting to 650,000 lines of programming code in the sequence
|
|
design process; 1,615,000 lines in the telemetry interpretation; and
|
|
550,000 lines of code in navigation. These must all be written, checked,
|
|
tested, used in mission simulations and, in many cases, revised before the
|
|
mission can begin.
|
|
|
|
Science investigators are located at JPL or other university laboratories
|
|
and linked by computers. From any of these locations, the scientists can
|
|
be involved in developing the sequences affecting their experiments and,
|
|
in some cases, in helping to change preplanned sequences to follow up on
|
|
unexpected discoveries with second looks and confirming observations.
|
|
|
|
|
|
|
|
|
|
JUPITER'S SYSTEM
|
|
|
|
Jupiter is the largest and fastest-spinning planet in the solar system.
|
|
Its radius is more than 11 times Earth's, and its mass is 318 times that of
|
|
our planet. Named for the chief of the Roman gods, Jupiter contains more
|
|
mass than all the other planets combined. It is made mostly of light
|
|
elements, principally hydrogen and helium. Its atmosphere and clouds are
|
|
deep and dense, and a significant amount of energy is emitted from its
|
|
interior.
|
|
|
|
The earliest Earth-based telescopic observations showed bands and
|
|
spots in Jupiter's atmosphere. One storm system, the Red Spot, has been
|
|
seen to persist over three centuries.
|
|
|
|
Atmospheric forms and dynamics were observed in increasing detail
|
|
with the Pioneer and Voyager flyby spacecraft, and Earth-based infrared
|
|
astronomers have recently studied the nature and vertical dynamics of
|
|
deeper clouds.
|
|
|
|
Sixteen satellites are known. The four largest, discovered by the
|
|
Italian scientist Galileo Galilei in 1610, are the size of small planets.
|
|
The innermost of these, Io, has active sulfurous volcanoes, discovered by
|
|
Voyager 1 and further observed by Voyager 2 and Earth-based infrared
|
|
astronomy. Io and Europa are about the size and density of Earth's moon (3
|
|
to 4 times the density of water) and probably rocky inside. Ganymede and
|
|
Callisto, further out from Jupiter, are the size of Mercury but less than
|
|
twice as dense as water. Their cratered surfaces look icy in Voyager
|
|
images, and they may be composed partly of ice or water.
|
|
|
|
Of the other satellites, eight (probably captured asteroids) orbit
|
|
irregularly far from the planet, and four (three discovered by the Voyager
|
|
mission in 1979) are close to the planet. Voyager also discovered a thin
|
|
ring system at Jupiter in 1979.
|
|
|
|
Jupiter has the strongest planetary magnetic field known. The
|
|
resulting magnetosphere is a huge teardrop-shaped, plasma-filled cavity
|
|
in the solar wind pointing away from the sun. JupiterUs magnetosphere is
|
|
the largest single entity in our solar system, measuring more than 14
|
|
times the diameter of the sun. The inner part of the magnetic field is
|
|
doughnut- shaped, but farther out it flattens into a disk. The magnetic
|
|
poles are offset and tilted relative to Jupiter's axis of rotation, so the
|
|
field appears to wobble with Jupiter's rotation (just under 10 hours),
|
|
sweeping up and down across the inner satellites and making waves
|
|
throughout the magnetosphere.
|
|
|
|
|
|
|
|
|
|
WHY JUPITER INVESTIGATIONS ARE IMPORTANT
|
|
|
|
With a thin skin of turbulent winds and brilliant, swift-moving clouds,
|
|
the huge sphere of Jupiter is a vast sea of liquid hydrogen and helium.
|
|
Jupiter's composition (about 88 percent hydrogen and 11 percent helium
|
|
with small amounts of methane, ammonia and water) is thought to
|
|
resemble the makeup of the solar nebula, the cloud of gas and dust from
|
|
which the sun and planets formed. Scientists believe Jupiter holds
|
|
important clues to conditions in the early solar system and the process of
|
|
planet formation.
|
|
|
|
Jupiter may also provide insights into the formation of the universe
|
|
itself. Since it resembles the interstellar gas and dust that are thought
|
|
to have been created in the "Big Bang," studies of Jupiter may help
|
|
scientists calibrate models of the beginning of the universe.
|
|
|
|
Though starlike in composition, Jupiter is too small to generate
|
|
temperatures high enough to ignite nuclear fusion, the process that
|
|
powers the stars. Some scientists believe that the sun and Jupiter began
|
|
as unequal partners in a binary star system. (If a double star system had
|
|
developed, it is unlikely life could have arisen in the solar system.) While
|
|
in a sense a "failed star," Jupiter is almost as large as a planet can be. If
|
|
it contained more mass, it would not have grown larger, but would have
|
|
shrunk from compression by its own gravity. If it were 100 times more
|
|
massive, thermonuclear reactions would ignite, and Jupiter would be a
|
|
star.
|
|
|
|
For a brief period after its formation, Jupiter was much hotter, more
|
|
luminous, and about 10 times larger than it is now, scientists believe.
|
|
Soon after accretion (the condensation of a gas and dust cloud into a
|
|
planet), its brightness dropped from about one percent of the Sun's to
|
|
about one billionth -- a decline of ten million times.
|
|
|
|
In its present state Jupiter emits about twice as much heat as it
|
|
receives from the Sun. The loss of this heat -- residual energy left over
|
|
from the compressive heat of accretion -- means that Jupiter is cooling
|
|
and losing energy at a tremendously rapid rate. Temperatures in Jupiter's
|
|
core, which were about 90,000 degrees Fahrenheit in the planet's hot,
|
|
early phase, are now about 54,000 degrees Fahrenheit, 100 times hotter
|
|
than any terrestrial surface, but 500 times cooler than the temperature at
|
|
the center of the sun. Temperatures on Jupiter now range from 54,000
|
|
degrees Fahrenheit at the core to minus 248 degrees Fahrenheit at the top
|
|
of the cloud banks.
|
|
|
|
Mainly uniform in composition, Jupiter's structure is determined by
|
|
gradations in temperature and pressure. Deep in Jupiter's interior there is
|
|
thought to be a small rocky core, comprising about four percent of the
|
|
planet's mass. This "small" core (about the size of 10 Earths) is
|
|
surrounded by a 25,000-mile-thick layer of liquid metallic hydrogen.
|
|
(Metallic hydrogen is liquid, but sufficiently compressed to behave as
|
|
metal.) Motions of this liquid "metal" are the source of the planet's
|
|
enormous magnetic field. This field is created by the same dynamo effect
|
|
found in the metallic cores of Earth and other planets.
|
|
|
|
At the outer limit of the metallic hydrogen layer, pressures equal three
|
|
million times that of Earth's atmosphere and the temperature has cooled
|
|
to 19,000 degrees Fahrenheit.
|
|
|
|
Surrounding the central metallic hydrogen region is an outer shell of
|
|
"liquid" molecular hydrogen. Huge pressures compress Jupiter's gaseous
|
|
hydrogen until, at this level, it behaves like a liquid. The liquid hydrogen
|
|
layer extends upward for about 15,000 miles. Then it gradually becomes
|
|
gaseous. This transition region between liquid and gas marks, in a sense,
|
|
where the solid and liquid planet ends and its atmosphere begins.
|
|
|
|
From here, Jupiter's atmosphere extends up for 600 more miles, but
|
|
only in the top 50 miles are found the brilliant bands of clouds for which
|
|
Jupiter is known. The tops of these bands are colored bright yellow, red
|
|
and orange from traces of phosphorous and sulfur. Five or six of these
|
|
bands, counterflowing east and west, encircle the planet in each
|
|
hemisphere. At one point near Jupiter's equator, east winds of 220 mph
|
|
blow right next to west winds of 110 mph. At boundaries of these bands,
|
|
rapid changes in wind speed and direction create large areas of turbulence
|
|
and shear. These are the same forces that create tornados here on Earth.
|
|
On Jupiter, these "baroclinic instabilities" are major phenomena, creating
|
|
chaotic, swirling winds and spiral features such as White Ovals.
|
|
|
|
The brightest cloud banks, known as zones, are believed to be higher,
|
|
cooler areas where gases are ascending. The darker bands, called belts,
|
|
|
|
|
|
|
|
|
|
|
|
|
|
are thought to be warmer, cloudier regions of descent.
|
|
|
|
The top cloud layer consists of white cirrus clouds of ammonia
|
|
crystals, at a pressure six-tenths that of Earth's atmosphere at sea level
|
|
(.6 bar). Beneath this layer, at a pressure of about two Earth atmospheres
|
|
(2 bars) and a temperature of near minus 160 degrees Fahrenheit, a
|
|
reddish-brown cloud of ammonium hydrosulfide is predicted.
|
|
|
|
At a pressure of about 6 bars, there are believed to be clouds of water
|
|
and ice. However, recent Earth-based spectroscopic studies suggest that
|
|
there may be less water on Jupiter than expected. While scientists
|
|
previously believed Jupiter and the sun would have similar proportions of
|
|
water, recent work indicates there may be 100 times less water on
|
|
Jupiter than if it had a solar mixture of elements. If this is the case,
|
|
there may be only a thin layer of water-ice at the 6 bar level.
|
|
|
|
However, Jupiter's cloud structure, except for the highest layer of
|
|
ammonia crystals, remains uncertain. The height of the lower clouds is
|
|
still theoretical -- clouds are predicted to lie at the temperature levels
|
|
where their assumed constituents are expected to condense. The Galileo
|
|
probe will make the first direct observations of Jupiter's lower
|
|
atmosphere and clouds, providing crucial information.
|
|
|
|
The forces driving Jupiter's fast-moving winds are not well understood
|
|
yet. The classical explanation holds that strong currents are created by
|
|
convection of heat from Jupiter's hot interior to the cooler polar regions,
|
|
much as winds and ocean currents are driven on Earth, from equator to
|
|
poles. But temperature differences do not fully explain wind velocities
|
|
that can reach 265 mph. An alternative theory is that pressure
|
|
differences, due to changes in the thermodynamic state of hydrogen at
|
|
high and low temperatures, set up the wind jets.
|
|
|
|
Jupiter's rapid rotation rate is thought to have effects on wind
|
|
velocity and to produce some of Jupiter's bizarre circulation patterns,
|
|
including many spiral features. These rotational effects are known as
|
|
manifestations of the Coriolis force. Coriolis force is what determines
|
|
the spin direction of weather systems. It basically means that on the
|
|
surface of a sphere (a planet), a parcel of gas farther from the poles has a
|
|
higher rotational velocity around the planet than a parcel closer to the
|
|
poles. As gases then move north or south, interacting parcels with
|
|
different velocities produce vortices (whirlpools). This may account for
|
|
some of Jupiter's circular surface features.
|
|
|
|
Jupiter spins faster than any planet in the solar system. Though 11 times
|
|
Earth's diameter, Jupiter spins more than twice as fast (once in 10 hours),
|
|
giving gases on the surface extremely high rates of travel -- 22,000 mph
|
|
at the equator, compared with 1000 mph for air at Earth's equator.
|
|
Jupiter's rapid spin also causes this gas and liquid planet to flatten
|
|
markedly at the poles and bulge at the equator.
|
|
|
|
Visible at the top of Jupiter's atmosphere are eye-catching features
|
|
such as the famous Great Red Spot and the exotic White Ovals, Brown
|
|
Barges and White Plumes. The Great Red Spot, which is 25,000 miles wide
|
|
and large enough to swallow three Earths, is an enormous oval eddy of
|
|
|
|
|
|
|
|
|
|
|
|
|
|
swirling gases. It is driven by two counter-flowing jet streams, which
|
|
pass, one on each side of it, moving in opposite directions, each with
|
|
speeds of 100-200 mph. The Great Red Spot was first discovered in 1664,
|
|
by the British scientist Roger Hook, using Galileo's telescope. In the three
|
|
centuries since, the huge vortex has remained constant in latitude in
|
|
Jupiter's southern equatorial belt. Because of its stable position,
|
|
astronomers once thought it might be a volcano.
|
|
|
|
Another past theory compared the Great Red Spot to a gigantic
|
|
hurricane. However, the GRS rotates anti-cyclonically while hurricanes
|
|
are cyclonic features (counterclockwise in the northern hemisphere,
|
|
clockwise in the southern) -- and the dynamics of the Great Red Spot
|
|
appear unrelated to moisture.
|
|
|
|
The Great Red Spot most closely resembles an enormous tornado, a huge
|
|
vortex that sucks in smaller vortices. The Coriolis effect created by
|
|
Jupiter's fast spin, appears to be the key to the dynamics that drive the
|
|
spot.
|
|
|
|
The source of the Great Red Spot's color remains a mystery. Many
|
|
scientists now believe it to be caused by phosphorus, but its spectral line
|
|
does not quite match that of phosphorus. The GRS may be the largest in a
|
|
whole array of spiral phenomena with similar dynamics. About a dozen
|
|
white ovals, circulation patterns resembling the GRS, exist in the
|
|
southern latitudes of Jupiter and appear to be driven by the same forces.
|
|
Scientists do not know why these ovals are white.
|
|
|
|
Scientists believe the brown barges, which appear like dark patches on
|
|
the planet, are holes in the upper clouds, through which the reddish-brown
|
|
lower cloud layer may be glimpsed. The equatorial plumes, or white
|
|
plumes, may be a type of wispy cirrus anvil cloud.
|
|
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SPACECRAFT CHARACTERISTICS
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Orbiter Probe
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Mass,lbs. 5,242 744
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Propellant, lbs. 2,400 none
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Height (in-flight) 15 feet 34 inches
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Inflight span 30 feet
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(w/oboom)
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Instrument payload 10 instruments 6 instruments
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Payload mass, lbs. 260 66
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Electric power, watts 570-480 730
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(RTGs) (Lithium-sulfur battery)
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GALILEO MANAGEMENT
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The Galileo Project is managed for NASA's Office of Space Science and
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Applications by the NASA Jet Propulsion Laboratory, Pasadena, Calif. This
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responsibility includes designing, building, testing, operating and tracking
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Galileo. NASA's Ames Research Center, Moffett Field, Calif. is responsible
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for the atmosphere probe, which was built by Hughes Aircraft Company, El
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Segundo, Calif.
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The probe project and science teams will be stationed at Ames during
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pre-mission, mission operations, and data reduction periods. Team
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members will be at Jet Propulsion Laboratory for probe entry.
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The Federal Republic of Germany has furnished the orbiter's
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retropropulsion module and is participating in the scientific
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investigations. The radioisotope thermoelectric generators were designed
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and built for the U.S. Department of Energy by the General Electric
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Company.
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GALILEO ORBITER AND PROBE SCIENTIFIC INVESTIGATIONS
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Listed by experiment/instrument and including the Principal Investigator
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and scientific objectives of that investigation:
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PROBE
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Atmospheric Structure; A. Seiff, NASA's Ames Research Center;
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temperature, pressure, density, molecular weight profiles;
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Neutral Mass Spectrometer; H. Niemann, NASA's Goddard Space Flight
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Center; chemical composition
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Helium Abundance; U. von Zahn, Bonn University, FRG; helium/hydrogen
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ratio
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Nephelometer; B. Ragent, NASA's Ames Research Center; clouds,
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solid/liquid particles
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Net Flux Radiometer; L. Sromovsky, University of Wisconsin-Madison;
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thermal/solar energy profiles
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Lightning/Energetic Particles; L. Lanzerotti, Bell Laboratories; detect
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lightning, measuring energetic particles
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ORBITER (DESPUN PLATFORM)
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Solid-State Imaging Camera; M. Belton, National Optical Astronomy
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Observatories (Team Leader); Galilean satellites at 1-km resolution or
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better
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Near-Infrared Mapping Spectrometer; R. Carlson, NASA's Jet Propulsion
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Laboratory; surface/atmospheric composition, thermal mapping
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Ultraviolet Spectrometer; C. Hord, University of Colorado; atmospheric
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gases, aerosols
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Photopolarimeter Radiometer; J. Hansen, Goddard Institute for Space
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Studies; atmospheric particles, thermal/reflected radiation
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ORBITER (SPINNING SPACECRAFT SECTION)
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Magnetometer; M. Kivelson, University of California at Los Angeles;
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strength and fluctuations of magnetic fields
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Energetic Particles; D. Williams, Johns Hopkins Applied Physics
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Laboratory; electrons, protons, heavy ions in magnetosphere and
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interplanetary space
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Plasma; L. Frank, University of Iowa; composition, energy, distribution of
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magnetospheric ions
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Plasma Wave; D. Gurnett, University of Iowa; electromagnetic waves and
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wave-particle interactions
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Dust; E. Grun, Max Planck Institute; mass, velocity, charge of submicron
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particles
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Radio Science - Celestial Mechanics; J. Anderson, JPL (Team Leader);
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masses and motions of bodies from spacecraft tracking;
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Radio Science - Propagation; H. T. Howard, Stanford University; satellite
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radii, atmospheric structure both from radio propagation
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INTERDISCIPLINARY INVESTIGATORS
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F. P. Fanale; University of Hawaii
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P. Gierasch; Cornell University
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D. M. Hunten; University of Arizona
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A. P. Ingersoll; California Institute of Technology
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H. Masursky; U. S. Geological Survey
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D. Morrison; Ames Research Center
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M. McElroy; Harvard University
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G. S. Orton; NASA's Jet Propulsion Laboratory
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T. Owen; State University of New York, Stonybrook
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J. B. Pollack; NASA's Ames Research Center
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C. T Russell; University of California at Los Angeles
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C. Sagan; Cornell University
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G. Schubert; University of California at Los Angeles
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J. Van Allen; University of Iowa
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STS-34 INERTIAL UPPER STAGE (IUS-19)
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The Inertial Upper Stage (IUS) will again be used with the Space
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Shuttle, this time to transport NASA's Galileo spacecraft out of Earth's
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orbit to Jupiter, a 2.5-billion-mile journey.
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The IUS has been used previously to place three Tracking and Data
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Relay Satellites in geostationary orbit as well as to inject the Magellan
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spacecraft into its interplanetary trajectory to Venus. In addition, the
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IUS has been selected by the agency for the Ulysses solar polar orbit
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mission.
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After 2 1/2 years of competition, Boeing Aerospace Co., Seattle, was
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selected in August 1976 to begin preliminary design of the IUS. The IUS
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was developed and built under contract to the Air Force Systems
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Command's Space Systems Division. The Space Systems Division is
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executive agent for all Department of Defense activities pertaining to the
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Space Shuttle system. NASA, through the Marshall Space Flight Center,
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Huntsville, Ala., purchases the IUS through the Air Force and manages the
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integration activities of the upper stage to NASA spacecraft.
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Specifications
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IUS-19, to be used on mission STS-34, is a two-stage vehicle weighing
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approximately 32,500 lbs. Each stage has a solid rocket motor (SRM),
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preferred over liquid-fueled engines because of SRM's relative simplicity,
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high reliability, low cost and safety.
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The IUS is 17 ft. long and 9.25 ft. in diameter. It consists of an aft
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skirt, an aft stage SRM generating approximately 42,000 lbs. of thrust, an
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interstage, a forward-stage SRM generating approximately 18,000 lbs. of
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thrust, and an equipment support section.
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Airborne Support Equipment
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The IUS Airborne Support Equipment (ASE) is the mechanical, avionics
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and structural equipment located in the orbiter. The ASE supports the IUS
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and the Galileo in the orbiter payload bay and elevates the combination for
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final checkout and deployment from the orbiter.
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The IUS ASE consists of the structure, electromechanical mechanisms,
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batteries, electronics and cabling to support the Galileo/IUS. These ASE
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subsystems enable the deployment of the combined vehicle; provide,
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distribute and/or control electrical power to the IUS and spacecraft;
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provide plumbing to cool the radioisotope thermoelectric generator (RTG)
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aboard Galileo; and serve as communication paths between the IUS and/or
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spacecraft and the orbiter.
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IUS Structure
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The IUS structure is capable of supporting loads generated internally
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and also by the cantilevered spacecraft during orbiter operations and the
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IUS free flight. It is made of aluminum skin-stringer construction, with
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longerons and ring frames.
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Equipment Support Section
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The top of the equipment support section contains the spacecraft
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interface mounting ring and electrical interface connector segment for
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mating and integrating the spacecraft with the IUS. Thermal isolation is
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provided by a multilayer insulation blanket across the interface between
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the IUS and Galileo.
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The equipment support section also contains the avionics which
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provide guidance, navigation, control, telemetry, command and data
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management, reaction control and electrical power. All mission-critical
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components of the avionics system, along with thrust vector actuators,
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reaction control thrusters, motor igniter and pyrotechnic stage separation
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equipment are redundant to assure reliability of better than 98 percent.
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IUS Avionics Subsystems
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The avionics subsystems consist of the telemetry, tracking and
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command subsystems; guidance and navigation subsystem; data
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management; thrust vector control; and electrical power subsystems.
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These subsystems include all the electronic and electrical hardware used
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to perform all computations, signal conditioning, data processing and
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formatting associated with navigation, guidance, control, data and
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redundancy management. The IUS avionics subsystems also provide the
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equipment for communications between the orbiter and ground stations as
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well as electrical power distribution.
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Attitude control in response to guidance commands is provided by
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thrust vectoring during powered flight and by reaction control thrusters
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while coasting. Attitude is compared with guidance commands to
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generate error signals. During solid motor firing, these commands gimble
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the IUS's movable nozzle to provide the desired pitch and yaw control. The
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IUS's roll axis thrusters maintain roll control. While coasting, the error
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signals are processed in the computer to generate thruster commands to
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maintain the vehicle's altitude or to maneuver the vehicle.
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The IUS electrical power subsystem consists of avionics batteries, IUS
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power distribution units, a power transfer unit, utility batteries, a
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pyrotechnic switching unit, an IUS wiring harness and umbilical and
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staging connectors. The IUS avionics system provides 5-volt electrical
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power to the Galileo/IUS interface connector for use by the spacecraft
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telemetry system.
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IUS Solid Rocket Motors
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The IUS two-stage vehicle uses a large solid rocket motor and a small
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solid rocket motor. These motors employ movable nozzles for thrust
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vector control. The nozzles provide up to 4 degrees of steering on the
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large motor and 7 degrees on the small motor. The large motor is the
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longest-thrusting duration SRM ever developed for space, with the
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capability to thrust as long as 150 seconds. Mission requirements and
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constraints (such as weight) can be met by tailoring the amount of
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propellant carried. The IUS-19 first-stage motor will carry 21,488 lb. of
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propellant; the second stage 6,067 lb.
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Reaction Control System
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The reaction control system controls the Galileo/IUS spacecraft attitude
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during coasting, roll control during SRM thrustings, velocity impulses for
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accurate orbit injection and the final collision-avoidance maneuver after
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separation from the Galileo spacecraft.
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As a minimum, the IUS includes one reaction control fuel tank with a
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capacity of 120 lb. of hydrazine. Production options are available to add a
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second or third tank. However, IUS-19 will require only one tank.
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IUS To Spacecraft Interfaces
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Galileo is physically attached to the IUS at eight attachment points,
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providing substantial load-carrying capability while minimizing the
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transfer of heat across the connecting points. Power, command and data
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transmission between the two are provided by several IUS interface
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connectors. In addition, the IUS provides a multilayer insulation blanket
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of aluminized Kapton with polyester net spacers across the Galileo/IUS
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interface, along with an aluminized Beta cloth outer layer. All IUS
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thermal blankets are vented toward and into the IUS cavity, which in turn
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is vented to the orbiter payload bay. There is no gas flow between the
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spacecraft and the IUS. The thermal blankets are grounded to the IUS
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structure to prevent electrostatic charge buildup.
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Flight Sequence
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After the orbiter payload bay doors are opened in orbit, the orbiter will
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maintain a preselected attitude to keep the payload within thermal
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requirements and constraints.
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On-orbit predeployment checkout begins, followed by an IUS command link
|
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check and spacecraft communications command check. Orbiter trim
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maneuvers are normally performed at this time.
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Forward payload restraints will be released and the aft frame of the
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airborne-support equipment will tilt the Galileo/IUS to 29 degrees. This
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will extend the payload into space just outside the orbiter payload bay,
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allowing direct communication with Earth during systems checkout. The
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orbiter then will be maneuvered to the deployment attitude. If a problem
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has developed within the spacecraft or IUS, the IUS and its payload can be
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restowed.
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Prior to deployment, the spacecraft electrical power source will be
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switched from orbiter power to IUS internal power by the orbiter flight
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crew. After verifying that the spacecraft is on IUS internal power and
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that all Galileo/IUS predeployment operations have been successfully
|
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completed, a GO/NO-GO decision for deployment will be sent to the crew
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from ground support.
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When the orbiter flight crew is given a "Go" decision, they will
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activate the ordnance that separates the spacecraft's umbilical cables.
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The crew then will command the electromechanical tilt actuator to raise
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the tilt table to a 58-degree deployment position. The orbiter's RCS
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thrusters will be inhibited and an ordnance-separation device initiated to
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physically separate the IUS/spacecraft combination from the tilt table.
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Six hours, 20 minutes into the mission, compressed springs provide the
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force to jettison the IUS/Galileo from the orbiter payload bay at
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approximately 6 inches per second. The deployment is normally performed
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in the shadow of the orbiter or in Earth eclipse.
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The tilt table then will be lowered to minus 6 degrees after IUS and its
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spacecraft are deployed. A small orbiter maneuver is made to back away
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from IUS/Galileo. Approximately 15 minutes after deployment, the
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orbiter's OMS engines will be ignited to move the orbiter away from its
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released payload.
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After deployment, the IUS/Galileo is controlled by the IUS onboard
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computers. Approximately 10 minutes after IUS/Galileo deployment from
|
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the orbiter, the IUS onboard computer will send out signals used by the
|
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IUS and/or Galileo to begin mission sequence events. This signal will also
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enable the IUS reaction control system. All subsequent operations will be
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sequenced by the IUS computer, from transfer orbit injection through
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spacecraft separation and IUS deactivation.
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After the RCS has been activated, the IUS will maneuver to the
|
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required thermal attitude and perform any required spacecraft thermal
|
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control maneuvers.
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At approximately 45 minutes after deployment from the orbiter, the
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ordnance inhibits for the first SRM will be removed. The belly of the
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orbiter already will have been oriented towards the IUS/Galileo to protect
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orbiter windows from the IUS's plume. The IUS will recompute the first
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ignition time and maneuvers necessary to attain the proper attitude for
|
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the first thrusting period. When the proper transfer orbit opportunity is
|
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reached, the IUS computer will send the signal to ignite the first stage
|
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motor 60 minutes after deployment. After firing approximately 150
|
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seconds, the IUS first stage will have expended its propellant and will be
|
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separated from the IUS second stage.
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Approximately 140 seconds after first-stage burnout, the second-
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stage motor will be ignited, thrusting about 108 seconds. The IUS second
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stage then will separate and perform a final collision/contamination
|
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avoidance maneuver before deactivating.
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SHUTTLE SOLAR BACKSCATTER ULTRAVIOLET INSTRUMENT
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|
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The Shuttle Solar Backscatter Ultraviolet (SSBUV) instrument was
|
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developed by NASA to calibrate similar ozone measuring space-based
|
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instruments on the National Oceanic and Atmospheric Administration's
|
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TIROS satellites (NOAA-9 and -11).
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The SSBUV will help scientists solve the problem of data reliability
|
|
caused by calibration drift of solar backscatter ultraviolet (SBUV)
|
|
instruments on orbiting spacecraft. The SSBUV uses the Space Shuttle's
|
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orbital flight path to assess instrument performance by directly
|
|
comparing data from identical instruments aboard the TIROS spacecraft,
|
|
as the Shuttle and the satellite pass over the same Earth location within a
|
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1-hour window. These orbital coincidences can occur 17 times per day.
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|
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The SBUV measures the amount and height distribution of ozone in the
|
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upper atmosphere. It does this by measuring incident solar ultraviolet
|
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radiation and ultraviolet radiation backscattered from the Earth's
|
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atmosphere. The SBUV measures these parameters in 12 discrete
|
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wavelength channels in the ultraviolet. Because ozone absorbs in the
|
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ultraviolet, an ozone measurement can be derived from the ratio of
|
|
backscatter radiation at different wavelengths, providing an index of the
|
|
vertical distribution of ozone in the atmosphere.
|
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|
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Global concern over the depletion of the ozone layer has sparked
|
|
increased emphasis on developing and improving ozone measurement
|
|
methods and instruments. Accurate, reliable measurements from space
|
|
are critical to the detection of ozone trends and for assessing the
|
|
potential effects and development of corrective measures.
|
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The SSBUV missions are so important to the support of Earth science
|
|
that six additional missions have been added to the Shuttle manifest for
|
|
calibrating ozone instruments on future TIROS satellites. In addition, the
|
|
dates of the four previously manifested SSBUV flights have been
|
|
accelerated.
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|
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The SSBUV instrument and its dedicated electronics, power, data and
|
|
command systems are mounted in the Shuttle's payload bay in two Get
|
|
Away Special canisters, an instrument canister and a support canister.
|
|
Together, they weigh approximately 1200 lb. The instrument canister
|
|
holds the SSBUV, its specially designed aspect sensors and in-flight
|
|
calibration system. A motorized door assembly opens the canister to
|
|
allow the SSBUV to view the sun and Earth and closes during the in-flight
|
|
calibration sequence.
|
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|
|
The support canister contains the power system, data storage and
|
|
command decoders. The dedicated power system can operate the SSBUV
|
|
for a total of approximately 40 hours.
|
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|
|
The SSBUV is managed by NASA's Goddard Space Flight Center,
|
|
Greenbelt, Md. Ernest Hilsenrath is the principal investigator.
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|
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GROWTH HORMONE CONCENTRATIONS AND DISTRIBUTION IN PLANTS
|
|
|
|
The Growth Hormone Concentration and Distribution in Plants (GHCD)
|
|
experiment is designed to determine the effects of microgravity on the
|
|
concentration, turnover properties, and behavior of the plant growth
|
|
hormone, Auxin, in corn shoot tissue (Zea Mays).
|
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|
|
Mounted in foam blocks inside two standard middeck lockers, the
|
|
equipment consists of four plant cannisters, two gaseous nitrogen
|
|
freezers and two temperature recorders. Equipment for the experiment,
|
|
excluding the lockers, weighs 97.5 pounds.
|
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|
|
A total of 228 specimens (Zea Mays seeds) are "planted" in special
|
|
filter, paper-Teflon tube holders no more than 56 hours prior to flight.
|
|
The seeds remain in total darkness throughout the mission.
|
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|
|
The GHCD experiment equipment and specimens will be prepared in a
|
|
Payload Processing Facility at KSC and placed in the middeck lockers. The
|
|
GHCD lockers will be installed in the orbiter middeck within the last 14
|
|
hours before launch.
|
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|
|
No sooner than 72 hours after launch, mission specialist Ellen Baker
|
|
will place two of the plant cannisters into the gaseous nitrogen freezers
|
|
to arrest the plant growth and preserve the specimens. The payload will
|
|
be restowed in the lockers for the remainder of the mission.
|
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|
|
After landing, the payload must be removed from the orbiter within 2
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|
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hours and will be returned to customer representatives at the landing site.
|
|
The specimens will be examined post flight for microgravity effects.
|
|
|
|
The GHCD experiment is sponsored by NASA Headquarters, the Johnson
|
|
Space Center and Michigan State University.
|
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|
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POLYMER MORPHOLOGY
|
|
|
|
The Polymer Morphology (PM) experiment is a 3M-developed organic
|
|
materials processing experiment designed to explore the effects of
|
|
microgravity on polymeric materials as they are processed in space.
|
|
|
|
Since melt processing is one of the more industrially significant
|
|
methods for making products from polymers, it has been chosen for study
|
|
in the PM experiment. Key aspects of melt processing include
|
|
polymerization, crystallization and phase separation. Each aspect will be
|
|
examined in the experiment. The polymeric systems for the first flight of
|
|
PM include polyethelyne, nylon-6 and polymer blends.
|
|
|
|
The apparatus for the experiment includes a Fournier transform
|
|
infrared (FTIR) spectrometer, an automatic sample manipulating system
|
|
and a process control and data acquisition computer known as the Generic
|
|
Electronics Module (GEM). The experiment is contained in two separate,
|
|
hermetically sealed containers that are mounted in the middeck of the
|
|
orbiter. Each container includes an integral heat exchanger that transfers
|
|
heat from the interior of the containers to the orbiter's environment. All
|
|
sample materials are kept in triple containers for the safety of the
|
|
astronauts.
|
|
|
|
The PM experiment weighs approximately 200 lb., occupies three
|
|
standard middeck locker spaces (6 cubic ft., total) in the orbiter and
|
|
requires 240 watts to operate.
|
|
|
|
Mission specialists Franklin R. Chang-Diaz and Shannon W. Lucid are
|
|
responsible for the operation of the PM experiment on orbit. Their
|
|
interface with the PM experiment is through a small, NASA-supplied
|
|
laptop computer that is used as an input and output device for the main PM
|
|
computer. This interface has been programmed by 3M engineers to manage
|
|
and display the large quantity of data that is available to the crew. The
|
|
astronauts will have an active role in the operation of the experiment.
|
|
|
|
In the PM experiment, infrared spectra (400 to 5000 cm-1) will be
|
|
acquired from the FTIR by the GEM computer once every 3.2 seconds as the
|
|
materials are processed on orbit. During the 100 hours of processing
|
|
time, approximately 2 gigabytes of data will be collected. Post flight, 3M
|
|
scientists will process the data to reveal the effects of microgravity on
|
|
the samples processed in space.
|
|
|
|
The PM experiment is unique among material processing experiments in
|
|
that measurements characterizing the effects of microgravity will be
|
|
made in real time, as the materials are processed in space.
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
In most materials processing space experiments, the materials have
|
|
been processed in space with little or no measurements made during
|
|
on-orbit processing and the effects of microgravity determined post
|
|
facto.
|
|
|
|
The samples of polymeric materials being studied in the PM experiment
|
|
are thin films (25 microns or less) approximately 25 mm in diameter. The
|
|
samples are mounted between two infrared transparent windows in a
|
|
specially designed infrared cell that provides the capability of thermally
|
|
processing the samples to 200 degrees Celsius with a high degree of
|
|
thermal control. The samples are mounted on a carousel that allows them
|
|
to be positioned, one at a time, in the infrared beam where spectra may be
|
|
acquired. The GEM provides all carousel and sample cell control. The first
|
|
flight of PM will contain 17 samples.
|
|
|
|
The PM experiment is being conducted by 3M's Space Research and
|
|
Applications Laboratory. Dr. Earl L. Cook is 3M's Payload Representative
|
|
and Mission Coordinator. Dr. Debra L. Wilfong is PM's Science Coordinator,
|
|
and James E. Steffen is the Hardware Coordinator.
|
|
|
|
The PM experiment, a commercial development payload, is sponsored by
|
|
NASA's Office of Commercial Programs. The PM experiment will be 3M's
|
|
fifth space experiment and the first under the company's 10-year Joint
|
|
Endeavor Agreement with NASA for 62 flight experiment opportunities.
|
|
Previous 3M space experiments have studied organic crystal growth from
|
|
solution (DMOS/1 on mission STS 51-A and DMOS/2 on STS 61-B) and
|
|
organic thin film growth by physical vapor treatment (PVTOS/1 on STS
|
|
51-I and PVTOS/2 on mission STS-26).
|
|
|
|
|
|
|
|
|
|
STUDENT EXPERIMENT
|
|
|
|
Zero Gravity Growth of Ice Crystals From Supercooled Water With Relation
|
|
To Temperature (SE82-15)
|
|
|
|
This experiment, proposed by Tracy L. Peters, formerly of Ygnacio High
|
|
School, Concord, Calif., will observe the geometric ice crystal shapes
|
|
formed at supercooled temperatures, below 0 degrees Celsius, without the
|
|
influence of gravity.
|
|
|
|
Liquid water has been discovered at temperatures far below water's
|
|
freezing point. This phonomenon occurs because liquid water does not
|
|
have a nucleus, or core, around which to form the crystal. When the ice
|
|
freezes at supercold temperatures, the ice takes on many geometric
|
|
shapes based on the hexagon. The shape of the crystal primarily depends
|
|
on the supercooled temperature and saturation of water vapor. The shapes
|
|
of crystals vary from simple plates to complex prismatic crystals.
|
|
|
|
Many scientists have tried to determine the relation between
|
|
temperature and geometry, but gravity has deformed crystals, caused
|
|
convection currents in temperature-controlled apparatus, and caused
|
|
|
|
|
|
|
|
|
|
|
|
|
|
faults in the crystalline structure. These all affect crystal growth by
|
|
either rapid fluctuations of temperature or gravitational influence of the
|
|
crystal geometry.
|
|
|
|
The results of this experiment could aid in the design of radiator cooling
|
|
and cryogenic systems and in the understanding of high-altitude
|
|
meteorology and planetary ring structure theories.
|
|
|
|
Peters is now studying physics at the University of California at Berkeley.
|
|
His teacher advisor is James R. Cobb, Ygnacio High School; his sponsor is
|
|
Boeing Aerospace Corp., Seattle.
|
|
|
|
Peters also was honored as the first four-time NASA award winner at the
|
|
International Science and Engineering Fair (ISEF), which recognizes
|
|
student's creative scientific endeavors in aerospace research. At the
|
|
1982 ISEF, Peters was one of two recipients of the Glen T. Seaborg Nobel
|
|
Prize Visit Award, an all-expense-paid visit to Stockholm to attend the
|
|
Nobel Prize ceremonies, for his project "Penetration and Diffusion of
|
|
Supersonic Fluid."
|
|
|
|
|
|
|
|
|
|
MESOSCALE LIGHTNING EXPERIMENT
|
|
|
|
The Space Shuttle will again carry the Mesoscale Lightning Experiment
|
|
(MLE), designed to obtain nighttime images of lightning in order to better
|
|
understand the global distribution of lightning, the interrelationships
|
|
between lightning events in nearby storms, and relationships between
|
|
lightning, convective storms and precipitation.
|
|
|
|
A better understanding of the relationships between lightning and
|
|
thunderstorm characteristics can lead to the development of applications
|
|
in severe storm warning and forecasting, and early warning systems for
|
|
lightning threats to life and property.
|
|
|
|
In recent years, NASA has used both Space Shuttle missions and
|
|
high-altitude U-2 aircraft to observe lightning from above convective
|
|
storms. The objectives of these observations have been to determine
|
|
some of the baseline design requirements for a satellite-borne optical
|
|
lightning mapper sensor; study the overall optical and electrical
|
|
characteristics of lightning as viewed from above the cloudtop; and
|
|
investigate the relationship between storm electrical development and
|
|
the structure, dynamics and evolution of thunderstorms and thunderstorm
|
|
systems.
|
|
|
|
The MLE began as an experiment to demonstrate that meaningful,
|
|
qualitative observations of lightning could be made from the Shuttle.
|
|
Having accomplished this, the experiment is now focusing on quantitative
|
|
measurements of lightning characteristics and observation simulations
|
|
for future space-based lightning sensors.
|
|
|
|
Data from the MLE will provide information for the development of
|
|
observation simulations for an upcoming polar platform and Space Station
|
|
|
|
|
|
|
|
|
|
|
|
|
|
instrument, the Lightning Imaging Sensor (LIS). The lightning experiment
|
|
also will be helpful for designing procedures for using the Lightning
|
|
Mapper Sensor (LMS), planned for several geostationary platforms.
|
|
|
|
In this experiment, Atlantis' payload bay camera will be pointed
|
|
directly below the orbiter to observe nighttime lightning in large, or
|
|
mesoscale, storm systems to gather global estimates of lightning as
|
|
observed from Shuttle altitudes. Scientists on the ground will analyze the
|
|
imagery for the frequency of lightning flashes in active storm clouds
|
|
within the camera's field of view, the length of lightning discharges, and
|
|
cloud brightness when illuminated by the lightning discharge within the
|
|
cloud.
|
|
|
|
If time permits during missions, astronauts also will use a handheld
|
|
35mm camera to photograph lightning activity in storm systems not
|
|
directly below the Shuttle's orbital track.
|
|
|
|
Data from the MLE will be associated with ongoing observations of
|
|
lightning made at several locations on the ground, including observations
|
|
made at facilities at the Marshall Space Flight Center, Huntsville, Ala.;
|
|
Kennedy Space Center, Fla.; and the NOAA Severe Storms Laboratory,
|
|
Norman, Okla. Other ground-based lightning detection systems in
|
|
Australia, South America and Africa will be intergrated when possible.
|
|
|
|
The MLE is managed by the Marshall Space Flight Center. Otha H. Vaughan
|
|
Jr., is coordinating the experiment. Dr. Hugh Christian is the project
|
|
scientist, and Dr. James Arnold is the project manager.
|
|
|
|
|
|
|
|
|
|
IMAX
|
|
|
|
The IMAX project is a collaboration between NASA and the Smithsonian
|
|
Institution's National Air and Space Museum to document significant space
|
|
activities using the IMAX film medium. This system, developed by the
|
|
IMAX Systems Corp., Toronto, Canada, uses specially designed 70mm film
|
|
cameras and projectors to record and display very high definition
|
|
large-screen color motion pictures.
|
|
|
|
IMAX cameras previously have flown on Space Shuttle missions 41-C,
|
|
41-D and 41-G to document crew operations in the payload bay and the
|
|
orbiter's middeck and flight deck along with spectacular views of space
|
|
and Earth.
|
|
|
|
Film from those missions form the basis for the IMAX production, "The
|
|
Dream is Alive." On STS 61-B, an IMAX camera mounted in the payload bay
|
|
recorded extravehicular activities in the EAS/ACCESS space construction
|
|
demonstrations.
|
|
|
|
The IMAX camera, most recently carried aboard STS-29, will be used on
|
|
this mission to cover the deployment of the Galileo spacecraft and to
|
|
gather material on the use of observations of the Earth from space for
|
|
future IMAX films.
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
AIR FORCE MAUI OPTICAL SITE CALIBRATION TEST
|
|
|
|
The Air Force Maui Optical Site (AMOS) tests allow ground-based
|
|
electro-optical sensors located on Mt. Haleakala, Maui, Hawaii, to collect
|
|
imagery and signature data of the orbiter during cooperative overflights.
|
|
Scientific observations made of the orbiter while performing Reaction
|
|
Control System thruster firings, water dumps or payload bay light
|
|
activation are used to support the calibration of the AMOS sensors and the
|
|
validation of spacecraft contamination models. AMOS tests have no
|
|
payload-unique flight hardware and only require that the orbiter be in
|
|
predefined attitude operations and lighting conditions.
|
|
|
|
The AMOS facility was developed by Air Force Systems Command
|
|
(AFSC) through its Rome Air Development Center, Griffiss Air Force Base,
|
|
N.Y., and is administered and operated by the AVCO Everett Research
|
|
Laboratory, Maui. The principal investigator for the AMOS tests on the
|
|
Space Shuttle is from AFSC's Air Force Geophysics Laboratory, Hanscom
|
|
Air Force Base, Mass. A co-principal investigator is from AVCO.
|
|
|
|
Flight planning and mission support activities for the AMOS test
|
|
opportunities are provided by a detachment of AFSC's Space Systems
|
|
Division at Johnson Space Center, Houston. Flight operations are
|
|
conducted at JSC Mission Control Center in coordination with the AMOS
|
|
facilities located in Hawaii.
|
|
|
|
|
|
|
|
|
|
SENSOR TECHNOLOGY EXPERIMENT
|
|
|
|
The Sensor Technology Experiment (STEX) is a radiation detection
|
|
experiment designed to measure the natural radiation background. The
|
|
STEX is a self-contained experiment with its own power, sensor, computer
|
|
control and data storage. A calibration pack, composed of a small number
|
|
of passive threshold reaction monitors, is attached to the outside of the
|
|
STEX package.
|
|
|
|
Sponsored by the Strategic Defense Initiative Organization, the STEX
|
|
package weighs approximately 50 pounds and is stowed in a standard
|
|
middeck locker throughout the flight.
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
PAYLOAD AND VEHICLE WEIGHTS
|
|
|
|
Vehicle/Payload Weight (Pounds)
|
|
|
|
Orbiter (Atlantis) Empty 172,018
|
|
|
|
Galileo/IUS (payload bay) 43,980
|
|
|
|
Galileo support hardware (middeck) 59
|
|
|
|
SSBUV (payload bay) 637
|
|
|
|
SSBUV support 578
|
|
|
|
DSO 49
|
|
|
|
DTO 170
|
|
|
|
GHCD 130
|
|
|
|
IMAX 269
|
|
|
|
MLE 15
|
|
|
|
PM 219
|
|
|
|
>SSIP 70
|
|
|
|
STEX 52
|
|
|
|
Orbiter and Cargo at SRB Ignition 264,775
|
|
|
|
Total Vehicle at SRB Ignition 4,523,810
|
|
|
|
Orbiter Landing Weight 195,283
|
|
|
|
|
|
|
|
|
|
|
|
SPACEFLIGHT TRACKING AND DATA NETWORK
|
|
|
|
Primary communications for most activities on STS-34 will be
|
|
conducted through the orbiting Tracking and Data Relay Satellite System
|
|
(TDRSS), a constellation of three communications satellites in
|
|
geosynchronous orbit 22,300 miles above the Earth. In addition, three
|
|
NASA Spaceflight Tracking and Data Network (STDN) ground stations and
|
|
the NASA Communications Network (NASCOM), both managed by Goddard
|
|
Space Flight Center, Greenbelt, Md., will play key roles in the mission.
|
|
|
|
Three stations -- Merritt Island and Ponce de Leon, Florida and the
|
|
Bermuda -- serve as the primary communications during the launch and
|
|
ascent phases of the mission. For the first 80 seconds, all voice,
|
|
telemetry and other communications from the Space Shuttle are relayed to
|
|
|
|
|
|
|
|
|
|
|
|
|
|
the mission managers at Kennedy and Johnson Space Centers by way of the
|
|
Merritt Island facility.
|
|
|
|
At 80 seconds, the communications are picked up from the Shuttle and
|
|
relayed to the two NASA centers from the Ponce de Leon facility, 30 miles
|
|
north of the launch pad. This facility provides the communications
|
|
between the Shuttle and the centers for 70 seconds, or until 150 seconds
|
|
into the mission. This is during a critical period when exhaust from the
|
|
solid rocket motors "blocks out" the Merritt Island antennas.
|
|
|
|
The Merritt Island facility resumes communications to and from the
|
|
Shuttle after those 70 seconds and maintains them until 6 minutes, 30
|
|
seconds after launch when communications are "switched over" to
|
|
Bermuda. Bermuda then provides the communications until 11 minutes
|
|
after liftoff when the TDRS-East satellite acquires the Shuttle.
|
|
TDRS-West acquires the orbiter at launch plus 50 minutes.
|
|
|
|
The TDRS-East and -West satellites will provide communications with
|
|
the Shuttle during 85 percent or better of each orbit. The TDRS-West
|
|
satellite will handle communications with the Shuttle during its descent
|
|
and landing phases.
|
|
|
|
|
|
|
|
|
|
|
|
|
|
STS-34 CARGO CONFIGURATION (illustration)
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
CREW BIOGRAPHIES
|
|
|
|
|
|
Donald E. Williams, 47, Capt., USN, will serve as commander. Selected
|
|
as an astronaut in January 1978, he was born in Lafayette, Ind.
|
|
|
|
Williams was pilot for STS-51D, the fourth flight of Discovery,
|
|
launched April 12, 1985. During the mission, the seven-member crew
|
|
deployed the Anik-C communications satellite for Telesat of Canada and
|
|
the Syncom IV-3 satellite for the U.S. Navy. A malfunction in the Syncom
|
|
spacecraft resulted in the first unscheduled extravehicular, rendezvous
|
|
and proximity operation for the Space Shuttle in an attempt to activate
|
|
the satellite.
|
|
|
|
He graduated from Otterbein High School, Otterbein, Ind., in 1960 and
|
|
received his B.S. degree in mechanical engineering from Purdue University
|
|
in 1964. Williams completed his flight training at Pensacola, Fla.,
|
|
Meridian, Miss., and Kingsville, Texas, and earned his wings in 1966.
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
During the Vietnam Conflict, Williams completed 330 combat missions.
|
|
He has logged more than 5,400 hours flying time, including 5,100 in jets,
|
|
and 745 aircraft carrier landings.
|
|
|
|
|
|
|
|
Michael J. McCulley, 46, Cdr., USN, will be pilot on this flight. Born in
|
|
San Diego, McCulley considers Livingston, Tenn., his hometown. He was
|
|
selected as a NASA astronaut in 1984. He is making his first Space
|
|
Shuttle flight.
|
|
|
|
McCulley graduated from Livingston Academy in 1961. He received B.S.
|
|
and M.S. degrees in metallurgical engineering from Purdue University in
|
|
1970.
|
|
|
|
After graduating from high school, McCulley enlisted in the U.S. Navy
|
|
and subsequently served on one diesel-powered and two nuclear-powered
|
|
submarines. Following flight training, he served tours of duty in A-4 and
|
|
A-65 aircraft and was selected to attend the Empire Test Pilots School in
|
|
Great Britain. He served in a variety of test pilot billets at the Naval Air
|
|
Test Center, Patuxent River, Md., before returning to sea duty on the USS
|
|
Saratoga and USS Nimitz.
|
|
|
|
He has flown more than 50 types of aircraft, logging more than 4,760
|
|
hours, and has almost 400 carrier landings on six aircraft carriers.
|
|
|
|
|
|
|
|
Shannon W. Lucid, 46, will serve as mission specialist (MS-1) on this,
|
|
her second Shuttle flight. Born in Shanghai, China, she considers Bethany,
|
|
Okla., her hometown. Lucid is a member of the astronaut class of 1978.
|
|
|
|
Lucid's first Shuttle mission was during STS 51-G, launched from the
|
|
Kennedy Space Center on June 17, 1985. During that flight, the crew
|
|
deployed communications satellites for Mexico, the Arab League and the
|
|
United States.
|
|
|
|
Lucid graduated from Bethany High School in 1960. She then attended
|
|
the University of Oklahoma where she received a B.S. degree in chemistry
|
|
in 1963, an M.S. degree in biochemistry in 1970 and a Ph.D. in biochemistry
|
|
in 1973.
|
|
|
|
Before joining NASA, Lucid held a variety of academic assignments
|
|
such as teaching assistant at the University of Oklahoma's department of
|
|
chemistry; senior laboratory technician at the Oklahoma Medical Research
|
|
Foundation; chemist at Kerr-McGee in Oklahoma City; graduate assistant in
|
|
the University of Oklahoma Health Science Center's department of
|
|
biochemistry; and molecular biology and research associate with the
|
|
Oklahoma Medical Research Foundation in Oklahoma City. Lucid also is a
|
|
commercial, instrument and multi-engine rated pilot.
|
|
|
|
|
|
|
|
Franklin Chang-Diaz, 39, will serve as MS-2. Born in San Jose, Costa
|
|
|
|
|
|
|
|
|
|
|
|
|
|
Rica, Chang-Diaz also will be making his second flight since being
|
|
selected as an astronaut in 1980.
|
|
|
|
Chang-Diaz made his first flight aboard Columbia on mission STS 61-C,
|
|
launched from KSC Jan. 12, 1986. During the 6-day flight he participated
|
|
in the deployment of the SATCOM KU satellite, conducted experiments in
|
|
astrophysics and operated the materials science laboratory, MSL-2.
|
|
|
|
Chang-Diaz graduated from Colegio De La Salle, San Jose, Costa Rica, in
|
|
1967, and from Hartford High School, Hartford, Conn., in 1969. He received
|
|
a B.S. degree in mechanical engineering from the University of Connecticut
|
|
in 1973 and a Ph.D. in applied plasma physics from the Massachusetts
|
|
Institute of Technology in 1977.
|
|
|
|
While attending the University of Connecticut, Chang-Diaz also worked
|
|
as a research assistant in the physics department and participated in the
|
|
design and construction of high-energy atomic collision experiments.
|
|
Upon entering graduate school at MIT, he became heavily involved in the
|
|
United State's controlled fusion program and conducted intensive research
|
|
in the design and operation of fusion reactors. In 1979, he developed a
|
|
novel concept to guide and target fuel pellets in an inertial fusion reactor
|
|
chamber. In 1983, he was appointed as visiting scientist with the MIT
|
|
Plasma Fusion Center which he visits periodically to continue his research
|
|
on advanced plasma rockets.
|
|
|
|
Chang-Diaz has logged more than 1,500 hours of flight time, including
|
|
1,300 hours in jet aircraft.
|
|
|
|
|
|
|
|
Ellen S. Baker, 36, will serve as MS-3. She will be making her first
|
|
Shuttle flight. Baker was born in Fayetteville, N.C., and was selected as
|
|
an astronaut in 1984.
|
|
|
|
Baker graduated from Bayside High School, New York, N.Y., in 1970. She
|
|
received a B.A. degree in geology from the State University of New York at
|
|
Buffalo in 1974, and an M.D. from Cornell University in 1978.
|
|
|
|
After medical school, Baker trained in internal medicine at the
|
|
University of Texas Health Science Center in San Antonio, Texas. In 1981,
|
|
she was certified by the American Board of Internal Medicine.
|
|
|
|
Baker joined NASA as a medical officer at the Johnson Space Center in
|
|
1981 after completing her residency. That same year, she graduated with
|
|
honors from the Air Force Aerospace Medicine Primary Course at Brooks
|
|
Air Force Base in San Antonio. Prior to her selection as an astronaut, she
|
|
served as a physician in the Flight Medicine Clinic at JSC.
|
|
|
|
|
|
|
|
NASA PROGRAM MANAGEMENT
|
|
|
|
|
|
NASA Headquarters
|
|
|
|
|
|
|
|
|
|
|
|
|
|
Washington, D.C.
|
|
|
|
Richard H. Truly
|
|
NASA Administrator
|
|
|
|
James R. Thompson Jr.
|
|
NASA Deputy Administrator
|
|
|
|
William B. Lenoir
|
|
Acting Associate Administrator for Space Flight
|
|
|
|
George W.S. Abbey
|
|
Deputy Associate Administrator for Space Flight
|
|
|
|
Arnold D. Aldrich
|
|
Director, National Space Transportation Program
|
|
|
|
Leonard S. Nicholson
|
|
Deputy Director, NSTS Program
|
|
(located at Johnson Space Center)
|
|
|
|
Robert L. Crippen
|
|
Deputy Director, NSTS Operations
|
|
(located at Kennedy Space Center)
|
|
|
|
David L. Winterhalter
|
|
Director, Systems Engineering and Analyses
|
|
|
|
Gary E. Krier
|
|
Director, Operations Utilization
|
|
|
|
Joseph B. Mahon
|
|
Deputy Associate Administrator
|
|
for Space Flight (Flight Systems)
|
|
|
|
Charles R. Gunn
|
|
Director, Unmanned Launch Vehicles
|
|
and Upper Stages
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George A. Rodney
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Associate Administrator for Safety, Reliability,
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Maintainability and Quality Assurance
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Charles T. Force
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Associate Administrator for Operations
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Dr. Lennard A. Fisk
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Associate Administrator for Space Science
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and Applications
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Samuel Keller
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Assistant Deputy Associate Administrator
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NASA Headquarters
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Al Diaz
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Deputy Associate Administrator for
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Space Science and Applications
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Dr. Geoffrey A. Briggs
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Director, Solar System Exploration Division
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Robert F. Murray
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Manager, Galileo Program
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Dr. Joseph Boyce
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Galileo Program Scientist
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Johnson Space Center
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Houston, Texas
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Aaron Cohen
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Director
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Paul J. Weitz
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Deputy Director
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Richard A. Colonna
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Manager, Orbiter and GFE Projects
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Donald R. Puddy
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Director, Flight Crew Operations
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Eugene F. Kranz
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Director, Mission Operations
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Henry O. Pohl
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Director, Engineering
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Charles S. Harlan
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Director, Safety, Reliability and Quality Assurance
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Kennedy Space Center
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Florida
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Forrest S. McCartney
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Director
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Thomas E. Utsman
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Deputy Director
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Jay F. Honeycutt
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Director, Shuttle Management
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and Operations
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Robert B. Sieck
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Launch Director
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George T. Sasseen
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Shuttle Engineering Director
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Conrad G. Nagel
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Atlantis Flow Director
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James A. Thomas
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Director, Safety, Reliability and
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Quality Assurance
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John T. Conway
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Director, Payload Managerment
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and Operations
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Marshall Space Flight Center
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Huntsville, Ala.
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Thomas J. Lee
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Director
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Dr. J. Wayne Littles
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Deputy Director
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G. Porter Bridwell
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Manager, Shuttle Projects Office
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Dr. George F. McDonough
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Director, Science and Engineering
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Alexander A. McCool
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Director, Safety, Reliability and Quality Assurance
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Royce E. Mitchell
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Manager, Solid Rocket Motor Project
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Cary H. Rutland
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Manager, Solid Rocket Booster Project
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Jerry W. Smelser
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Manager, Space Shuttle Main Engine Project
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G. Porter Bridwell
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Acting Manager, External Tank Project
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Sidney P. Saucier
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Manager, Space Systems Projects Office
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[for IUS]
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Stennis Space Center
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Bay St. Louis, Miss.
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Roy S. Estess
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Director
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Gerald W. Smith
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Deputy Director
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William F. Taylor
|
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Associate Director
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J. Harry Guin
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Director, Propulsion Test Operations
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Edward L. Tilton III
|
|
Director, Science and Technology Laboratory
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John L. Gasery Jr.
|
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Chief, Safety/Quality Assurance
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and Occupational Health
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|
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Jet Propulsion Laboratory
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|
Pasadena, Calif.
|
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|
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Dr. Lew Allen
|
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Director
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|
|
Dr. Peter T. Lyman
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Deputy Director
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|
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Gene Giberson
|
|
Laboratory Director for Flight Projects
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John Casani
|
|
Assistant Laboratory Director for Flight Projects
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|
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Richard J. Spehalski
|
|
Manager, Galileo Project
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|
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William J. O'Neil
|
|
Manager, Science and Mission Design,
|
|
Galileo Project
|
|
|
|
Dr. Clayne M. Yeates
|
|
Deputy Manager, Science and Mission Design,
|
|
Galileo Project
|
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|
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Dr. Torrence V Johnson
|
|
Galileo Project Scientist
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Neal E. Ausman Jr.
|
|
Mission Operations and Engineering Manager
|
|
Galileo Project
|
|
|
|
A. Earl Cherniack
|
|
Orbiter Spacecraft Manager
|
|
Galileo Project
|
|
|
|
Matthew R. Landano
|
|
Deputy Orbiter Spacecraft Manager
|
|
Galileo Project
|
|
|
|
William G. Fawcett
|
|
Orbiter Science Payload Manager
|
|
Galileo Project
|
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Ames Research Center
|
|
Mountain View, Calif.
|
|
|
|
Dr. Dale L. Compton
|
|
Acting Director
|
|
|
|
Dr. Joseph C. Sharp
|
|
Acting Director, Space Research Directorate
|
|
|
|
Joel Sperans
|
|
Chief, Space Exploration Projects Office
|
|
|
|
Benny Chin
|
|
Probe Manager
|
|
Galileo Project
|
|
|
|
Dr. Lawrence Colin
|
|
Probe Scientist
|
|
Galileo Project
|
|
|
|
Dr. Richard E. Young
|
|
Probe Scientist
|
|
Galileo Project
|
|
|
|
|
|
|
|
Ames-Dryden Flight Research Facility
|
|
Edwards, Calif.
|
|
|
|
Martin A. Knutson
|
|
Site Manager
|
|
|
|
Theodore G. Ayers
|
|
Deputy Site Manager
|
|
|
|
|
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|
|
Thomas C. McMurtry
|
|
Chief, Research Aircraft Operations Division
|
|
|
|
|
|
|
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|
|
|
Larry C. Barnett
|
|
Chief, Shuttle Support Office
|
|
|
|
|
|
|
|
Goddard Space Flight Center
|
|
Greenbelt, Md.
|
|
|
|
Dr. John W. Townsend
|
|
Director
|
|
|
|
Peter Burr
|
|
Director, Flight Projects
|
|
|
|
Dale L. Fahnestock
|
|
Director, Mission Operations and Data Systems
|
|
|
|
Daniel A. Spintman
|
|
Chief, Networks Division
|
|
|
|
Gary A. Morse
|
|
Network Director
|
|
|
|
Dr. Robert D. Hudson
|
|
Head, Atmospheric Chemistry and Dynamics
|
|
|
|
Ernest Hilsenrath
|
|
SSBUV Principal Investigator
|
|
|
|
Jon R. Busse
|
|
Director, Engineering Directorate
|
|
|
|
Robert C. Weaver Jr.
|
|
Chief, Special Payloads Division
|
|
|
|
Neal F. Barthelme
|
|
SSBUV Mission Manager
|
|
|