grs-a press kit

8/7/2019 GRS-A Press Kit

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NATIONAL AERONAUTICS AND SPACE ADMINISTRAtION TELS WO 2-4155WASHINGTON, D.C. 20546 S WO 3-6925FOR RELEASE: SUNDAYRELEASE NO: 69-146 November 2, 1969

PROJECT: German ResearchSatellite (GRS-A)

CoontentsS ENERAL RELEASE---------------------------------------------1-4LAUNCH VEHICLE-----------------------------------------------5W Flight Sequence-----------------------------------------5> GRS-A/AZUR FACT SHEET---------------------------------------6-8

DESCRIPTION OF EXPERIMENTS----------------------------------9-11GRS-A/AZUR PROGRAM PARTICIPANTS-----------------------------12-14MEMORANDUM OF UNDERSTANDING BETWEEN GERMANMINISTRY FOR SCIENTIFIC RESEARCH AND THEK U.S. NATIONAL AERONAUTICS & SPACE ADMIN.-------------------15-18

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P ^ - NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (202) 962-4155NEWS WASHINGTONID.C. 20546 (202) 963-6925FOR RELEASE: SUNDAYNovember 2, 1969

RELEASE NO: 69-146

GERMAN SATELLITE LAUNCH

The first satellite in a cooperative space program betweenthe Federal Republic of Germany and the United States isscheduled to be launched into a near polar orbit no earlierthan November 6, 1969, from the Western Test Range, California.The launch vehicle will be a four-stage, solid-fuel Scoutrocket.

Called GRS-A (for German Research Satellite), the 157-pound, German-built satellite will carry seven scientificexperiments designed to study the earth radiation belt, theaurorae, and solar particle events. Special emphasis isplaced on measuring the intensity and distribution of protonsand electrons in terms of time and location. In orbit thesatellite will be called AZUR.

The launching of GRS-A is a major milestone marking thesecond phase of a two-phase cooperative program between theGerman Ministry for Scientific Research (Bundesministerium Ifuer wissenschaftliche Forschung)-BMwF) and the NationalAeronautics and Space Administration (NASA).

The first phase consisted of a series of sounding rocketlaunchings--from sites in Canada, Sweden and Brazil--designedto checkout GRS-A instrumentation. These activities wereconducted during 1966 and 1967.

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The formal agreement for the program was signed in July1965 by representatives of BMwF and NASA. Under it the BMwFis generally responsible for providing spacecraft hardwareand experiments, while NASA provides launch vehicles, techni-cal consultation, training, and tracking and data acquisitionsupport. Close coordination between the two organizationsexists on matters relating to all phases of the program--design, final construction, test, and satellite/launch vehiclecompatibility.

The orbit planned for GRS-A will have an apogee of about2,000 statute miles and a perigee of about 240 statute miles inclined102 degrees to the equator. It will. take about two hours andtwo minutes for the satellite to complete oe orbit. Itsplanned operational lifetime is one year.

The spacecraft is stabilized at injection by spinning upthe fourth stage to about 178 rpm. After separation the spinrate is reduced to about zero rpm by a two-stage yo-yo despinsystem. An internal grid of eight hysteresis damping rodsprovides further damping of satellite oscillations so thatafter approximately 10 days in orbit the spacecraft will auto-matically align itself and become stabilized along the linesof force of the Earth's magnetic field. This alignment isaccomplished by means of in-board permanent magnets.

The seven scientific experALinents carried by GRS-A areprovided by five different German research institutes.

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In general the experiment objectives continue studiesconducted by earlier NASA Explorer-series satellites as wellas the Orbiting Geophysical Observatories launched by NASAinto near polar orbits.

The satellite will be tracked and interrogated by a systemof stations operated under direction of BMwF augmented by NASA'sworld-wide Space Tracking and Data Acquisition Network (STADAN).BMwF will be responsible for data reduction, analysis, andpublication of experiment results.

Data will be made available exclusively to the Germanprincipal investigations for a period of one year, duringwhich they will exercise their rights of first publication.

After this one-year period data records will be depositedwith the NASA Space Science Data Center operated by the GoddardSpace Flight Center, Greenbelt, Maryland, and will be madegenerally available to any interested scientist.

The Office of Space Science & Applications, NASA Head-quarters, Washington, D. C., has program responsibility forthe NASA portion of this cooperative effort, which is coor-dinated through the NASA Headquarters Office of InternationalAffairs.

The NASA Goddard Space Flight Center is charged withmanagement of the project for NASA. The NASA Langley ResearchCenter is responsible for providing the launch vehicle andlaunch services. The U. S. Air Force 6595th Air Test Wing

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provides the Western Test Range launch team. NASA's KennedySpace Center Unmanned Launch Operations provides launch opera-tions support at WTR. The Scout launch vehicle is built byLing-Temco-Vought, Inc., Dallas, Texas.

The German project management responsibility is assignedby BMwF to the Gesellschaft fuer Weltraumforschung (GfW)Space Research Corporation, Bonn, Germany.

The design, manufacture, integration, and testing ofthe spacecraft was accomplished by seven German aerospace andelectronic companies coordinated by Messerschmitt-Boelkow-Blohm, Corporation, Munich, Germany.

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GRS-5 -LAUNCH VEHICLE

The Scout program is managed by NASA's Langley ResearchCenter, Hampton, Va.Scout is a four-stage solid propellant launch vehicle.

The four Scout motors, Algol, Castor, Antares, and Fw-4Sare interloched with transition sections that contain guidance,control, ignition, instrumentation system, separation mechanics,and the spin motors needed to stabilize the fourth stage.Guidance for Scout is provided by an autopilot and con-trol achieved by a combination of aerodynamic surfaces, jetvanes and hydrogen peroxide jets. The launch vehicle is

approximately 73 feet long and weighs about 40,000 pounds atliftoff. Scout vehicle number S-169 and the GRS-A spacecraftwill be set on an initial launch azimuth of 197.2110 to obtaina retrograde orbit.

Flight SequenceEvent Time (seconds)Liftoff -First stage burnout 76.57Second stage ignition 83.63Second stage burnout 123.06Heatshield ejection 147.00Third stage ignition 148.70Third stage burnosu. 184.60Spin-up 472.96Third stage separation 474.46Fourth stage ignition 478.96Fourth stage burnout & orbital injection 513.66

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FEET72 - /N

FOURTH STAGE S fACCCRTAND FW-4SSPACECRAFT SOLID-PROPELLANT

60 - MOTORANTARES-II91SOLI D -PROPELLANTTHIRD STAGE MOTOR

50 _ _

CASTOR-=40 - SOLID-PROPELLANT

SECOND STAGE MOTOR

30 -

20 -ALGOL-US

FIRST STAGE SOLID-PROPELLANTMOTORo0 !

;S.-out Latinch Vehicle

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Proton Counter El 101Guide Rail for -_BoomAurorol PhotometerEl 102Proton Telescope - 4 \ C Guide

Detector El 93El 95PlatfonnPower Supply an d ATelecommunications e-Damping RodsSoaCelMounting forDamping RodsStabilizing Magnets'Centrw4 Tube(GfK)Aurovul Photometer..El 102

Adaptor Boom (Deployed)Antenna l.25ft -Mognetometer El 15

German Research Satellite A


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GRS-6 -GRS-A/AZUR FACr SHEET

Launch Window: 20--minute window which changes onlyslightly from day-to-day. Window opensat 5:51 PM (PST), November 6, 1969.

Launch Sil.e: Western Test Range, Lompoc, California,Pad SLC-5

Launch Rocket: Four stage solid fuel ScoutOrbit: Apogee: About 3,200 km (2,000

statute miles)Perigee: About 390 km (240 statute

miles)Period: 122 minutesInclination: 102 degrees

Spacecraft: Weight: 157 pounds with about 37pounds of experiments.

Structure: Cvlinder 30 inches indiameter with overalllength of 48 flaches.Conical shaped tot; flatbottom from which protrudefour antennas and a 33-inch-Jong magnetometer boom.

Power: Practically entire exteriorportion of spacecraft iscovered with solar cellsto charge silver-cadmium

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GRS-7 -GRS-A/AZUR FACT SHEET (CONT'D.)

Power: battery pack. Powor(cont'd) needed to operate GRS-Aranges from 17 watts tipto 29 watts during peakoperating period.

Telemetry: Two PCM/PM trarnsmittorsoperating at 136,74 MHzand 136.56 MHz, reopec-tively.

Tracking and DataAcquisition: Tracking, scientific and spacecraftperformance data will be acquired fromthe GRS-A by the following stations:

* The Central German Ground Station,Lichtenau, Federal Republic of

-. - Germany, which will relay real-timuand taped data and commands botwoonspacecraft and the German ControlCenter at Oberpfaffenhofen, nearMunich.

* Stations of ESTRAC operated by theEuropean Space Research Organization(ESRO) located in Ny Alesund,Spitsbergen; Fairbanks, Alaska;Redu, Belgium; and Port Stanley,Falkland Islands.

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GRS-8 -GRS-A/AZUR FACT SHEET (CONT'D.)

Tracking and Dat * Special stations under contractAciiuiisiti~on:(CO.7 d.) to Gesellschaft fuer Weltraum-forschung, mbH (Space ResearchCorporation) at Kevo, Finland;Churchill Research Range, Canada;and Reykjavik, Iceland.

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sta -@9 -DESCRIPTION OF EXPERIMENTS

El 15 MAGNETOMETERA two component flux gate magnetometer mounted on an

extendable boom will be used. The two components are orientednormal to each other and normal to the magnetic axis of the satellite.The analog outputs of the two flux gates will be digitized usinga 12-bit analog digital converter. The 12-bit information willbe included twice in the main data frame which has a ten secondduration, while the last 6 bits will be transmitted in real timeevery 100 milliseconds in order to measure small amplitudetransient disturbances of the geomagnetic field.EI 88 PROTON-ALPHA TELESCOPE

This unit uses seven semiconductor surface barrier detec-tors mounted one behind the other. Particles entering the 28degree cone of acceptance will be detected using a three-foldcoincidental/anti-coincidental scheme according to their energyin seven different channels. A scintillation counter surroundsthe detector stack and gives veto signals if particles fromunwanted directions enter the device. Two sets of this tele-scope will be used on the satellite. The one is oriented underan angle of 90 degrees relative to the magnetic axis, the otherunder an angle of 135 degrees. A magnet in the entrance aperturewill sweep off electrons which otherwise might disturb the pro-ton measurements.

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GRS-10 -DESCRIPTION OF EXPERIMENTS (CONT'D)

EI 92 LOW ENERGY PROTON TELESCOPETwo surface barrier semiconductor detectors mounted

one behinO the other serve fr>r low energy proton detection.Particles entering the back detector will not be counted byusing the signal from this one as a veto. Directional pro-perties are achieved by using a solid aperture. A magnet in theaperture will prevent electrons from reaching the first detec-tor. Information will be obtained by counting into sixdifferent energy channels:EI 93 PROTON-ELECTRON DETECTOR

'Two different units are used of the same build up. Alithium diffused cubic semiconductor detector is installed ineach unit and is covered by a semispherically-shaped absorber,whicn has different wall thicknesses in the two units. Two-level pulse height discrimination is done on each of both unitsthus allowing the measurement of Drotons and electrons in two energyranges. The units accept particles from a hemisphereand are therefore mounted to the spacecraft's skin such thatthe spacecraft will not shadow the two units.EI 95 ELECTRON DETECTOR

This unit uses three Geiger Muellcr Counters which havea very thin mica windows so that 40 keV electrons maybe detected. They are oriented such that one looks normal tothe magnetic axis of the satellite while the other two look

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DESCRIPTION OF EXPERIMENTS (CONT'D)

parallel and anti-parallel relative to the magnetic momentvector of the satellite. A fourth detector is shielded inorder to get background information. One dat. channel perdetector is used. Information is transmitted twice in each10-second data frame, and in addition in real time with about a12 millisecond time resolution.EI 101 PROTON MONITOR

Two Geiger Mueller Counters with range cross sections areplaced on top of the satellite. The two counters areshielded by different masses, so they respond to charged parti-cles with energy above two different energy thresholds.El 102 PHOTOMETER

Aphotnmultiplier watching the optical intensity behind aninterference filter is used, its output current being digitizedby a neon glow tube circnit. Three such units will be used,two looking toward the earth, over the northern hemisphere, thethird one away from the earth as a background reference. The3914 A0 and 2972 A0 auroral optical emission lines will be ob-served. Data will be transmitted in real time only. Measure-ments will be performed during shadow times only.


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GRS-12 -GRS-A/AZUR PROGRAM PARTICIPANTS

FEDERAL REPUBLIC OF GERMANYMinistry for Scientific Research (BMwF)

Mr. Max Mayer Head, Department of Space andAeronautics Research

Mr. Bernhard Gaedke Head, Subdepartment for SpaceFlight and TechnologyMr. Herbert Lindner Head, Subdepartment for GeneralAffairs and Space ScienceDr. Arthur Schendel Head, Satellite Systems SectionDr. Walther Regula Head, Extraterrestrial Research

SectionMr. Manfred Otterbein Azur Program ManagerDr. Eckhard Luebbert Azur Program Scientist

Space Research Corporation (GfW)Mr. Walter Luksch Technical DirectorMr. Ants Kutzer Azur Project ManagerMr. Dieter von Eckardstein Azur Deputy Project ManagerMr. Martin Schurer Tracking & Data AcquisitionManager, German Satellite Control

CenterMax, Planck Institute for Aeronomy

Dr. Erhard Keppler Azur Project ScientistGRS-A/Azur Experimenters

Dr. Gunter Musmann Institut fuir Geophysik undMeteorologie der TechnischenHochschule, BraunschweigMagnetometer (El-15)

Dr. Dierk Hovestadt Max-Planck-Institut fu rExtraterrestrische Physik,Garching b. MfinchenProton Telescope (EI 88) andProton Electron Detector (EI 93)

Mr. Jurgen Moritz Institut fur Reine-und-Angewandte-kernphysik der Universit9At Kiel,KielProton Telescope (EI-92)


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NASA Langley Research CenterMr. Roland D. English Head, Scout Project OfficeMr. Larry R. Tant Scout Payload CoordinatorMr. Clyde W. Winters Scout Project Launch Director

Western Test Range - Launch OperationsMr. William D. Hinshaw Head, Langley Mission SupportOffice, Western Test RangeMr. Henry R. Van Goey Chief, Kennedy Space Center,Unmanned Launch Operations,

Western Test RangeMr. Canuto R. Fuentes GRS-A Coordinator, Kennedy SpaceCenter, Unmanned Launch Operations,

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MEMOPANDUM OF UNDERSTANDTIiOGBFJT'VEEN TPV

GTPHMAN MINISTER FOR SC~rENTIFI.C PESEARCHAND THE UNITED STATRSNATIONAT. AERONAUTICS ANDr SPACE AOMINT.STRETION

1. Thor Germnn Min.stry fo.' Scientific Research (Bv'ndesministeri.um furWisserscbaf.tliche Fortgchung (BMwF) and the United States National Aeronau-tics snr Space Administration (NASA) affTirm a mutuaJ. interest in cooperatingin spaenc research for peaccftLl scientific purposes by conducting, on a timelybasis, a satellite project to investigate the earth's radiation belts. Itis hoped that this project will mature in 196 with the launching of a satel-lite carrying energetic particles experiments from the Western Test Range ofthe United States into dn elliptical earth orbit.

2. The cooperative project is planned to consist of two consecutive phases,the second to proceed with mutual agreement that scientific and technical fea-sibility has been demonstrated in the first:

Phase I--Appropriate sounding rocket and balloon payloads will belaunched, as mutually agreed, to test the functioning of prz. ..ed satelliteinstrumentation and to verify the performance of the proposed satellite ex-per ents.

Phase lI--A scientific satellite carrying experiments to perform anintegrated study of the spectra and fluxes of energetic particles in theearth's inner radiation belts will be placed into an elliptical earth orbitby a Scout vehicle.

3. It is understood that this program is experimental in character and,therefore, subject to change, by mutual agreement, on the basis of the resultsof Phase I and other technical requirements.

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4. The BMwF shall, in general, assume responsibility for:a. Providing inst.rumentation for the agreed experiments for Phases

I and II.b. Providing balloons and balloon launching support for experiments

to be tested in balloon flights.c. Designing, fabricating, and testing of all payloads for sounding

rocket balloon and satellite flights, including satellite structureand airborne telemetry, and delivering to the launch site two-*flight-qualified payloads or spacecraft for each flight mission.

d. Supplying payload and spacecraft ground checkout and launch supportequipment.

e. Providing such tracking and data acquisition for Phase II as maybe feasible with the use of projected ground stations in WestGermany.

f. Reducing and analyzing the data in all phases of the program.

5. NASA shall, in general, assume responsibility for:a. Providing a Javelin rocket and a Nike-Apache'rociet, with back-

ups, including appropriate nosecones, for Phase I.b. Providing a Scout booster, with backup, including heat shields

and spacecraft tiedown and separation mechanisms, for Phase II.c. Launching of the sounding rockets in Phase I and of the satellite

in Phase II.d. Making available such training of German personnel in BMwF areas of

responsibility as may be required and feasible within the limitationsof NASA operational requirements.

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e. Providing relevant technical consultation and technical data asappropriate.

f. Providing technical assistance in spacecraft testing and review-ing of final acceptance tests of satellite flight and backup units.Final determination of the suitability of flight units for launchingwilJl be by joint BMwF/NASA decision.

g. Tracking and data acquisition, as mutually agreed, in Phases Iand II of the program, using existing NASA sounding rocket andscientific satellite tracking and data-acquisition facilities.

6, No exchange of funds is contemplated between the two cooperatingagencies. Each agency will bear the costs of discharging its respectiveresponsibilities, including travel and subsistence of its own personnel andtransportation charges on all equipment for which it is responsible.

7. Each agency agrees to designate a single Project Manager to be respon-sible for coordinating the agreed functions and responsibilities of eachagency with the other in the implementation of this agreement. Togetherthey will establish a Joint Working Group with appropriate membership. De-tails for implementation shall be resolved on a mutual basis within thisworking group.

8. The scheduling of the two phases of the program shall be as mutuallyagreed.

9. BMwF and NASA will use their best efforts to arrange for free customsclearance of equipment required in this project.

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10 . Data obtained from the experiments siaUl be provided to the BMwFprincipal investigators fo x -heir analysis and evaluation for a period ofapproximately 1 year. (However, du.ring this period, NASA may, for its ownuse, obtain copies of tapes or reduced data records as soon as they becomeavailable, without prejudice to the principal investigators' interests infirst publication.)

During this 1-year period, ill requests for data shall be referred tothe BMwF principal investigators. After this period, records or copies ofreduced data will be deposited with the NASA Space Science Data Center andlisted with the appropriate World Data Center. Such records will then bemade available to interested scientists, upon reasonable request, by theWorld Data Center or other selected repository. Preliminary and final re-sults of the experiments will be made available to the scientific communityin general through publication in appropriate journals and other establishedchannels.

11 . Release of public infoxmation regarding the Joint project may be madeby each agency for its own portions of the project as desired and, insofaras the participation of the other is involved, after suitable coordination.

r th CaBtellieri s u Huegh L. DrydenFor the Bundesministerium fur For the National AeronauticsWissenschaftliche Forschung and Space Administration

July 17, 1-Date

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r7SNATIONAL AERONAUTICS AND SPACE ADMINISTRATION (202) 962-4155N EWS3 WASHINGTON,-D.C. 20546 SSW: (202) 963-6925

FOR RELEASE: IMMEDIATEOctober 28, 1969UEITEASE NO: 69-i47

BOEING LRV CONTRACT

The National Aeronautics and Space Administration hasselected The Boeing Co., Aerospace Group, Huntsville, Ala.,to design, develop, test and deliver four flight-qualifiedlunar roving vehicles and related test and training equip-ment.

The four flight vehicles will be used in manned ex-ploration of the Moon's surface. Boeing was one of fourcontractors who had submitted proposals for this work.

Estimated value of the cost-plus-incentive-fee contractis $19 million.

The lunar rover will provide transportation on the Moonfor two astronauts and equipment for the collection of lunarsamples and performance of other experiments.

The four-wheeled vehicles will be carried to the Moonaboard the descent stages of the Apollo spacecraft lunarmodule on flights planned in the 1971-72 period.

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