voyagers 1 and 2 backgrounder press kit

8/8/2019 Voyagers 1 and 2 Backgrounder Press Kit

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N h ~ t N e w sNational Aeronautics andSpace Administration

Washington. DC 20546AC 202 755-8370

For Release THURSDAY

February 22, 1979

Press Kit Project VOYAGERS 1 and 2BACKGROUNDER

RELEASE NO: 79-22

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RELEASE NO: 79-22

-CONTENTS

2LHE VOYAGER SPACECRAFT............................... 1-22

Structure and Configuration....................... 2Communications..................................... 8Power.............................................. 13Attitude Control and Propulsion................... 16Temperature Control................................ 21

JUPITER.............................................. 23-30

SATURN............................................... 31-36

PLANETARY ATMOSPHERIC AN D SURFACE DATA.............. 37-38

COMPARISON (Chart)..... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

TH E SATELLITES OF JUPITER (Chart)................... 40

TH E SATELLITES OF SATURN (Chart).................... 41

VOYAGER SCIENCE...................................... 43-60

Voyager Science Investigations.................... 44Cosmic Ray Investigation.......................... 46Low-Energy Charged-Particle Investigation ......... 46Magnetic Fields Inves~tigation..................... 47Infrared Spectroscopy and Radiometry

Investigation...... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48IRIS Instruments ............................... 49Photopolarimetry Investiation.................... 50Planetary Radio Astronomy Investigation .......... 50Plasma Investigation...... . . . . . . . . . . . . . . . . . . . . . . . . . 51Plasma Wave Investigation......................... 53Radio Science Investigation....................... 54Imaging Science Investigation..................... 54Ultraviolet Spectroscopy Investigation............ 57

TRACKING AN D DATA ACQUISITION....................... 61-63

MISSION CONTROL AND COMPUTING CENTER . . . . . . . . . . . . . . . 64-65

VOYAGER TEAM....... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66-69

VOYAGER SUBCONTRACTORS....... . . . . . . . . . . . . . . . . . . . . . . . . 69-71

CONVERSION TABLE..................................... 72

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TH E VOYAGER SPACECRAFT

The two Voyager spacecraft ar e designed to operate atistances from Earth an d the Su n greater than those of an yrevious NASA mission. Communications capabili ty, hardwareeliability, navigation and temperature control were amonghe major challenges. Th e spacecraft ar e identical. Eachan meet the objectives of either mission and their variousptions.

Each Voyager at launch consisted of a mission module --he planetary vehicle -- an d a propulsion module, which pro-ided th e final energy increment necessary to inject the mis-io n module into the Jupiter transfer trajectory. Th e propul-ion module was jettisoned after th e requiredvelocity wa sttained. (For purposes of mission description, "spacecraft"and "mission module" will be used interchangeably. In des-* cribing the prelaunch configuration and launch phase, "space-raft" will refer to the combined "mission module" an d "pro-ulsion module.")

The mission module after injection weighed 826 kilograms(1,820 pounds), including a 105-kg (231-lb.) science instru-ent payload. The propulsion module, with it s large solidropellant rocket motor, weighed 1,220 kg (2,690 lb.). Th epacecraft adaptor joins the spacecraft with the Centaur stagef the launch vehicle. It weighed 47.2 kg (104 lb.). Totalaunchweight of the spacecraft was 2,100 kg (4,630 lb.).

To assure proper operation fo r the four-year fl ight toaturn, an d perhaps well beyond, mission module subsystems wereesigned with high reliability and extensive redundancy.

Like the Mariners that explored the solar system's innerlanets an d the Viking Mars Orbiters, the Voyagers are stabilizedn three axes using the Sun and a star (Canopus) as celestialeference points.

Three engineering subsystems ar e proglammable for onboardontrol of spacecraft: functions. (Only trajectory correctionaneuvers must be enabledby ground command.) These subsystemsre the computer command subsystems (CCS), the flight data sub-ystems (FDS) an d the attitude and articulation control sub-ystem (AACS).

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Th e memories of these units ca n be updated or modifiedbyground command at an y time.

Ho t gas jets provide thrust fo r attitude stabilizationas well as fo r trajectory correction maneuvers.

A nuclear power source -- three radioisotope thermo-electric generators -- provides th e spacecraft electricalpower.

Th e science instruments required to view th e planets andtheir moons ar e mounted on a two-axis scan platform at theen d of th e science boom fo r precise pointing. Other body-fixed an d boom-mounted instruments ar e aligned fo r properinterpretationof their measurements.

Data storage capacity on the spacecraft is about 536million bits of information -- th e equivalent of about 100full-resolution photos.

Dual frequency communication links -- S-band an d X-band-- provide accurate navigation data an d large amounts ofscience information during planetary encounter periods (up to115,200 bits pe r second at Jupiter an d 44,800 bp s at Saturn).Dominant feature of th e spacecraft is th e 3 .66-meter(12-foot) diameter high-gain antenna which points toward Earthcontinually.

While the high-gain antenna dish is white, most visibleparts of the spacecraft ar e black -- blanketed or wrapped forthermal control an d micrometeoroid protection. A fe w smallareas ar e finished in gold foil or have polished aluminumsurfaces.

Structure and Confiquration

The nasic mission module structure is a 2 9.5-kg (65-lb.)10-sided aluminum framework with 10 electronics packaging com-partments. Th e structure is 47 centimeters (18.5 inches) highand 1.78 m (5.8 ft.) across. Th e electronicsassemblies arestructural ele. ants of the 10-sided box.

Th e spherical propellant tank, which supplies fuel tohydrazine thrusters for attitude control an d trajectory cor-rection maneuvers (TCM), occupies the center cavity of thedecagon. Propellant lines carry hydrazine to 12 small atti-tude control an d four TCM thrusters on the mission module.

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VOYAGER SCIENCE

Th e Voyager mission to Jupiter an d Saturn willaddress fundamental questions about the origin and natureof th e solar system. Understanding interplanetary spacean d th e other planets should give scientists a greaterknowledge of Earth.

According to current theoretical models of the originan d evolution of the solar system, a gaseous nebula composedof solar material -- gases and dust of various elements --collapsed to form the Sun. Some of th e material remainedbehind and began to coalesce to form the planets, theirsatellites, th e asteroids, comets an d meteors. Temperature,pressure and density of th e gas decreased with distance fromthe Sun. Formation of the planets is believed to haveresulted from accretion of the nebular material. Observeddifferences in th e planets ar e accounted fo r in thesetheories by variations in material and conditions at theplaces where they formed. Thus, knowledge gained at eachplanet can be related to others an d should contribute toan overall understanding of th e solar system as well asou r own planet Earth.

Missi'ons to Mars, Venus, Mercury an d th e Moon havecontributed greatly to the body of knowledge. Each plancthas its ow n personality, significantly different from

others because of it s unique composition an d relationshipto th e Sun. Individual as they are, th e inner planetsar e related as bodies that originated near the Su n an dthat ar e composed mainly of heavier elements. They ar eclassified as "terrestrial planets," since the Earth isapproximately representative.

Scientists have known fo r a long time that Jupiter,Saturn an d the other outer planets differ significantlyfrom terrestrial planets. They have lo w average densities;only hydrogen and helium among al l the elements are lightenough to match observations to date. Jupiter and Saturnar e sufficiently massive (318 and 95 times Earth's mass,respectively) to insure that they have retained almostal l their original material. They are, however, onlyrelatively pristine examples of the material from whichthe solar system formed. While almost no material ha sbeen lost, the planets have evolved over their 4.6-billion-year lifetimes and the nature an d ratio of the materialsma y have changed. If that 4.6-billion-year evolution canbe traced, scientists will obtain a clearer picture of thee a r I y stt -of theair regzio f Innf t-ha so l ar a s y s t e m

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Voyager Science Investigations

The scientific investigations of the Jupiter-Saturnission are multipurpose taking data in a variety ofnvironments. Fo r example, the ultraviolet spectrometertudies planetary an d satellite atmospheres an d alsonterplanetary an d interstellar hydrogen and helium.he magnetic fields experiment will examine the magnetospheresf th e planets and also search fo r the transition betweenolar an d galactic regions.

It is difficult to separate "planetary" from "inter-lanetary" instruments and investigations.there is,owever, another grouping.

First, the optical scanners, mounted on the spacecraft'scan platform, have narrow fields of view an d must beccurately pointed. They collect radiant energy (light,or example) from their targets an d create images or spectralnformation that permit scientists to understand the physicalorm or chemical composition of the planets an d satellites.nvestigations in this group include the imaging sciencenstruments (TV), infrared interferometer-spectrometerandadiometer, ultraviolet spectrometer an d photopolarimeter.

The second family of investigations senses magneticields an dfluxes of charged particles as the spacecraftasses through them. These instruments are fixed to theod y of the spacecraft and have various fields of view.heir data taken together will give information onlanetary magnetic fields (and indirectly, interiortructure), on Sun-planet and planet-satellite interactionsnd on cosmic rays and the outer reaches of the solar plasma.hese investigations ar e plasma, low energy charged particles,osmic ray an d magnetic fields.

A third family is planetary radic astronomy an d plasma-av e investigations whose long antennca whips listen forlanetary emissions, like those from Jupiter.

A radio inves t iga t ion uses S-band and X-band l inksetween spacecraf t and Earth to gather information onlanetary and satellite ionospheres an d atmospheres an dpacecraft tracking data to chart gravitational fieldsha t affect Voyager's course.

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TRACKING AND DATA ACQUISITION

Tracking, commanding and obtaining data from th e space-craft are part of the mission assigned to the Je t PropulsionLaboratory (JPL), Pasadena, Calif. These tasks cover all phasesof the flight, including telemetry from launch vehicle andspacecraft, metric data on both launch vehicle and Voyager,command signals to the spacecraft and delivery of data to theMission Control and Computing Center (MCCC) at JPL.

The Tracking and Data System (TDS) will include elementsof the world-wide NASA JPL Deep Space Network (DSN), Air ForceEastern Test Range (AFETR), the NASA Spaceflight Tracking andData Network (STDN) and the NASA Communications System (NASCOM).

During the launch phase of the mission, data acquisitionwa s accomplished through use of the near Earth facilities--the AFETR stations, downrange elements of th e STDN, instrumen-ted jet aircraft and a communications ship. Radar-metric dataQbtained immediately after liftoff and through the near Earthphase was delivered to and computed at th e AFETR Real timeComputer system facility in Florida so that accurate predictionscould be transmitted to Deep Space Network stations givingthe locations of the spacecraft in the sky when they appearon the horizon.

Tracking and communications with the Voyagers frominjection into Jupiter transfer trajectory until the end ofthe mission ar e beinq carried out by the Deep Space Network(DSN).

The DSN consists of nine deep space communications sta-tions on three continents, a spacecraft monitoring station irFlorida, the Network Operations Control Center in the MCCC atJPL and ground communications linking al l locations.

DSN stations are located strategically around theEarth--at Goldstone, Calif.; Madrid, Spain; and at Canbcrra,Australia. Each location is equipped with a 64-m diameter(210 ft.) antenna station and two 26-m (85 ft.) antennastations.

The three multi-station complexes are spaced at widelyseparated longitudes around the world so that spacecraftbeyond Earth orbit--and, for the Voyager mission, thepla.ints Jupiter and Saturn--are never ou t of view. Thespacecraft monitoring equipment in the STDN station atMerritt Island, Fla., covered th e Prelaunch and launchphases of the mission. A simulated DSN station at JPL,called CTA-21, provided prelaunch compatibility support.

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In addition to the giant antennas, each of the stationsis equipped with transmitting, receiving, data handling andinterstation communication equipment. Th e downlink includessupercooled lownoise amplifiers. The 64-m antenna stationsin Spain and Australia have 100-kw transmitters. At Goldstone,the uplink signal can be radiated at up to 400 kw. Trans-mitter power at all six 26-m stations is 20 kw.

The downlink is transmitted from th e spacecraft at S-band (2295 mHz) and X-band (8400 mHz) frequencies. The up-link operates at S-band (2113 mHz) only, carrying commandsand ranging signals from ground stations to th e spacecraft.

Only the 64-m antenna stations can receive the X-bandsignal and can receive at both frequencies simultaneously.The 64-m stations will provide continuous coverage duringplanetary operations an d periodically during th e cruisephase for maneuvers, spacecraft recorder playbacks and dual-frequency navigation sequences. A 26-m antenna subnet willprovide continuous coverage--shared by the two spacecraft--throughout the mission.

Various data rates for each type of telemetered infor-mation ar e required by th e changing length of the telecommuni-cations link and the possible adverse weather effects atground stations on reception of X-band radio signals.

Nerve center of the DSN is the Network Operations ControlCenter at JPL which provides for control and monitoring of DSNperformance. All incoming data is validated at this point,while being simultaneously transferred to the computingfacilities c. the Mission Control and Computing Center for

real time use by engineers and science investigators.

Ground communications facilities used by the DSN tolink th e global s ta t ions with th e control center ar e partof a l a rger network, NASCOM, %*hich onnects a ll of NASA'sstations around the world. Data from the spacecraft ar etransmitted over high speed c i r cu i t s . Telemetry a t ra tesup to and including 115.2 k.b .p .s . wil l be carried in realtime on wideband lines from Golastone and Madrid. The Can-berra stations will send encounter data in real time atrates up to and including 44.8 k.b.p.s. Higher downlinkrates will be recorded at the station and played back toMCCC at 44.8 k.b.p.s.

Simultaneously with the routing to the MCCC of thespacecraft telemetry, range and range rate informationwill be generated by the DSN and transmitted to the controlcenter for spacecraf t navigation. To achieve the desiredmaneuver and encounter accuracies, very precise navigationdata is required. Navigation information includes S-Xranging, DRVID (differenced range versus integrated Doppler)and multi-station tracking cycles.

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Commands ar e sent from th e MCCC to on e of th e DSN stations

where they ar e loaded into a command processing computer, auto-

matically verified fo r accuracy an d transmitted to th e proper

spacecraft at 16 bps. Commands may be aborted, if necessary.Manual control an d entry of command data at th e station is pos-sible in th e event of a failure in th e high speed data linefrom th e control center.

Fo r al l of NASA's unmanned missions in deep space, th e DS N

provides th e tracking information on course an d direction of th e

flight, velocity and range from Earth. It receives engineering

and science telemetry an d sends commands fo r spacecraft opera-tions on a multi-mission basis.

Concurrent with th e four-year or longer Voyager mission,

th e network is supporting th e extended mission activities of

the Viking Projectwith tw o Landers on Mars an d tw o Orbiters

circling th e planet; maintaining post-Jupiter communicationswith Pioneers 10 an d 11; an d complementing West Germany's space

communications facilities on tw o Helios Sun-orbiting missions.

The DSN also supported a Venus exploration mission by tw oPioneer Venus spacecraft -- a planetary orbiter an d five atmos-pheric probes -- launched in May an d August, 1978, an d planetaryscience activities in December 1978.

All of NASA's networks ar e under the direction of th e Of-ice

of Tracking an d Data Systems. JP L manages th e DSN. The STDT

facilities an d NASCOM ar e managed by NASA's Goddard Space F! 1ht

Center, Greenbelt, Md.

The Goldstone DS N stations ar e operated an d maintained ILJPL with th e assistance of the Bendix Field Engineering Corp.

Th e Canberra stations ar e operated by th e Australian Department

of Supply. Th e stations near Madrid ar e operated by the Spanish

government's Instituto Nacional de Tecnica Aerospacial.

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MISSION CONTROL AND COMPUTING CENTER

The Mission Control an d ComputingCenter (MCCC) athe Jet Propulsion Laboratory is th e focus of al l Voyagerroject flight operations. It is through th e center's com-uter systems that data from the Voyagers pass, ar e pro-essed an d presented to th e engineers an d scientists fo rnalysis. Through the extensive and varied displays of theomputers in th e MCCC, th e flight analysts observe andontrol the many ground processing functions and the space-raft.

The MCCC is housed in two JPL buildings containing it somputer systems, communications and display equipment,photo processing la b an d mission support areas. Th e variousreas ar e outfitted to satisfy th e diverse needs of theoyagermission operations team--requirements of the missionontrollers, spacecraft performance analysts an d sciencenvestigators.

Th e MCCC contains several computer systems designed toeceive the incoming Voyager data, process it in real time,isplay it an d organize it fo r further processing and analysis.fter the data have been received as radio signals by th eee p Space Network (DSN) stations located around the world,he y are transmitted to Pasadena an d into the MCCC computers,here th e processing begins. Software developed by the MCCC,perating in these computers, performs the receiving, dis--laying an d organizing functions. Computer programs genera-ed by other elements of th e VoyagerProject further processhe data.

Commands causing th e spacecraft to maneuver, gathercience data and perform other complex mission activities arentroduced into the MCCC computers an d comm.iunicated to a sta-ion of the DS N fo r transmission to the appropriate space-raft.

Th e MCCC is composed of three major elements, eachith it s ow n computer system. They are the Mission Controlnd Computing Facility (MCCF), the General Purpose Computingacility (GPCF) and the Mission Test an d Computing FacilityMTCF).

Th e MCCF consists of three IB M 360-75 processors andupports th e Voyager command, data records and tracking sys-ems. Th e 3 6 0-75s provide th e means through which commandsre sent to th e spacecraft. They also are used to processnd display tracking and data an d provide th e data manage-ent capability to produce plots an d printouts for the day toay determination of spacecraft operating conditions. The6 0-75s also produce the final records of data for detailednalysis by th e science community.

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Th e GPCF, with three UNIVAC 1108 computers, supports

the Voyager Project's navigation and mission sequence

systems. Th e 1108s also ar e used to develop predictionprograms and detailed spacecraft engineering performance

analysis. Computer terminals located in th e mission sup-

port area allow project analysts to execute their programs

an d obtain results displayed on TV monitors, or on various

printers an d plotters.

Th e MTCF provides telemetry data processing fo r th e

science an d engineering information transmitted from the

Voyagers. Within th e MTCF are the telemetry system, imaging

system an d photo system. Th e telemetry system uses three

strings of UNIVAC an d Modcomp computers to receive, record,

process and display the data as requested by analysts in

th e mission support areas. Th e imaging andphoto systems

produce th e photographic products from data generated by

Voyager's TV cameras. Pictures of Jupiter, Saturn an d their

moons will be analyzed by scientists housed in the mission sup-

port areas. Scientists will be provided both electronicand

photographic displays.

MCCC, like the DSN, also supports th e other flight

missions, Viking, Pioneers 10 and 11, Helios an d th e

Pioneer/Venus orbiter.

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VOYAGER TEAM

NASA Headquarters

Office of Space Science

Dr. Noel W. HinnersAssociate Administrator

for Space ScienceAndrew J. Stofan

Deputy Associate AdministratorDr . Adrienne F. Timothy Assistant Associate Adminis-

trator - ScienceRodney A. Mills

Program Manager

Arthur Reetz, Jr . Deputy Program ManagerDr. Milton A. Mitz Program ScientistOffice of Tracking an d Data Systems

Dr. William C. Schneider Associate Administrator forTracking an d Data Systems

Charles A. Taylor Director, Network Operationsan d Communication Programs

Arnold C. BelcherProgram Manager

for DS NOperationsFrederick B. Bryant Director, Network System

Development ProgramsMaurice E. Binkley Director, DSN SystemsOffice of Space ransQotation Systems

John F. YardleyAssociator Administrator

for Space Transportation SystemsJoseph B. Mahon Director, Expendable Launch

VehiclesJoseph E. McGolrick Director, Small and Medium

Launch VehiclesB. C. Lam

Titan III Manager

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NASA Jet Propulsion Laboratory

Dr. Bruce C. Murray Director

Gen. Charles H. Terhune, Jr. Deputy Director

Robert J. Parks Project Manager

Raymond L. Heacock Spacecraft System Manager

Charles E. Kohlhase Mission Analysis andEngineering Manager

James E. Long Science Manager

Richard P. Laeser Mission Operations System

Manager

Esker K. Davis Tracking an d Data SystemManager

James F. Scott Mission Control and ComputingCenter Manager

Ronald F. Draper Spacecraft System Engineer

William S. Shipley Spacecraft Development Manager

William G. Fawcett Science Instruments Manager

Michael Devirian Chief of Mission Operations

California Institute of Technology

Dr . Edward C. Stone Project ScienList

Lewis Reseaich Center

Dr . John F. McCarthy, Jr. Director

H. 0. Slone Launch Vehicle Systems Manager

Carl B. Wentworth Chief, Program IntegrationDivision

Gary D. Sagerman Voyager Mission Analyst

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Lewis Center (cont'd.)

Richard P. Geye Voyager Mission ProjectEngineer

Richard A. Flage Launch Vehicle Test

Integration Engineer

Richard E. Orzechowski TDS Support Engineer

Larry J. Ross Chief, Vehicles EngineeringDivision

James E. Patterson Associate Chief, EngineeringDivision

Frank L. Manning TC-6 and TC-7 Vehicle Engineer

Ken~nedy Space Center

Lee R. Scherer Director

Walter J. Kapryan Director of Space VehicleOperations

George F. Page Director, Expendable Vehicles

John D. Gossett Chief, Centaur OperationsDivision

Creighton A. Terhune Chief Engineer, OperationsDivision

Jack E. B~altar Centaur Operations Branch

Donald C. Sheppard Chief, Spacecraft and SupportOperations Division

James E. Weir Spacecraft Operations Branch

Floyd A. Curington Voyager Project Engineer

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Department of Energy

Douglas C. Bauer Director, Nuclear Researchan d Applications

Be~rnard J. Rock Assistant Director fo rSpace Applications

James J. Lombardo Chief, Power Systems Branch

Thaddeus G. Dobry Chief, Flight Safety Branch

Norman Thielke Chief, Heat Source Branch

Alfred L. Mowery Chief, Technical Support

Branch

VOYAGER SUBCONTRACTORS

Following are some key subcont rac tors who provided ir.stru-ments, hardware an d services:

Algorex Data Corp. Automated Design Support fo rSyosset, N.Y. Flight Data Subsystem

Boeing Co. Radiation CharacterizationSeattle, Wash. of Parts an d Materials

Fairchild Space and Temperature Control LouversElectronics Co.

Germantown, Md.

Ford Aerospace an d S/X-Band Antenna Subsystem;Communications Corp. Solid-State Amplifiers

Palo Alto, Calif.

Frequency Electronics, In:. Ultra Stable OscillatorsNe w Hyde Park, N.Y.

General Electric Co. Radioisotope ThermoelectricSpace Division GeneratorsPhiladelphia, Pa.

General Electric Co. Computer Command Subsystem;Utica, N.Y. Flight Control Processors

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-70-General Electric Co. Attitude Control andSpace Systems Organization Articulation SubsystemValley Forge, Pa .

Hi-Shear Corp. Pyrotechnic SquibsOrdnance DivisionTorrance, Calif.

Honeywell, Inc. Canopus Star TrackersLexington, Mass.

Hughes Aircraft Co . Radiation CharacterizationAerospace Group of Parts and MaterialsCulver City, Calif.

Lockheed Electronics Co . Data Storage Tape Transportndustrial Technology DivisionPlainfield, N.J.

Martin Marietta Aerospace Attitude Control Electronics;enver, Colo.Propulsion Subsystem

Motorola, Inc. Modulation-Demodulation Sub-overnment Electronics Div. system; Radio Frequency Sub-cottsdale, Ariz. system

Rocket Research Corp. Rocket Engine and Thrusteredmond, Wash. Valve Assemblies

SCI Systems, Inc. Computer Cowmand Subsystemuntsville, Ala. Memories

Teledyne Microelectronics Hybrid Memories for Flightos Angeles, Calif. Data Subsystem

Texas InstrumentsData Storage ElectronicsDallas, Tex.

Tl e Singer Co . Dry Inertial Reference Unitsittle Falls, N.J. (Gyroscopes)

Thiokol Chemical Corp. Solid Rocket MotorElkton DivisionEl!ton, Mld.

Watkins-Johnson Co. S/X-Band Traveling Wavealo Alto, Calif. Tube Amplifiers

Xerox Coxp.Power Subsystem

Electro-Optical SystemsPasadena, Calif.

Yardney Electronics Corp. Flirht and T-st BdLLcryDenver, Colo.

Assemblies

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Science Instruments

Massachusetts Institute Plasma Subsystemof Technology

Cambridge, Mass.

University of Colorado Photopolarimeter Si.bsystem* Boulder, Colo.

University of Iowa Plasma Wave SubsystemIowa City, Towa

Xerox Corp. Imaging Science (TV)Electro-Optical Systems Electronics

* Pasadena, Calif.

Kitt Peak National Observatory Ultraviolet SpectrometerTucsoni, Ariz.

Johns Hopkins University Low-Energy Charged P~rticlesApplied Physics Laboratory SubsystemBaltimore, Md.

Goddard Space Flight Center Magnetometers; Cosmic-RayGreenbelt, Md. Subsystem

Texas Instruments Modified Infrared Inter-

Dallas, 'Pex. ferometer, Spectrometeran d Radiometer

Martin Marietta Aerospace Planetary Radio Astronomy

DneColo. Subsystem

Astro Research Corp. Magnetometer Boomn; PlanetarySanta Barhara, Calif. Radio Astronomy Antennas

TR W Defense an d Space Systems Ultraviolet SpectrometerRedondo Beach, Calif. Electronics

Matrix Corp. Plasma Subsystem ElectronicsActon, Mlass.

General Electrodynamics Corp. TV ViLdiconsDallas, Tex.

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Instruments


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CONVERSION TABLE

Multiply By To Get

Inches 2.54 Centimeters

Centimeters 0.3937 Inches

Feet 30.48 Centimeters

Centimeters 4.7244 Feet

Feet 0.3048 Meters

Meters 3.2808 Feet

Yards 0.9144 Meters

Meters 1.0936 Yards

Statute Miles 1.6093 Kilometers

Kilometers 0.6214 Miles

Feet Pe r Second 0.3048 Meters Per Second

Meters/Second 3.281 Feet/Second

Meters/Second 2.237 Statute Miles/Hour

Feet/Second 0.6818 Miles/Hour

Miles/Hour 1.60%3 Kilomcters/llour

Kilometers/Hour 0.6214 Miles/Hour

Pounds u.4563 Kilograms

Kilograms 2.2046 Pounds

voyagers 1 and 2 backgrounder press kit

Documents