heos-a2 press kit

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    im / NATIONAL AERONAUTICS ANDSPACE ADMIN1STRAiON\\Washington, D. C. 20546202-755-8370

    FOR RELEASE:UPON RECEIPTt~ ~ ~ o~fow^o79-17p PROJECT: HEOS-A2RcontentsE GENERAL RELEASE --------------------------------- 1-4MISSION --------------------------------------- 5SPACECRAFT DESCRIPTION -------------------------- 6

    SPACECRAFT EXPERIMENTS -------------------------- 7-8DELTA-L LAUNCH VEHICLE CHARACTERISTICS -------- 9-10FLjGHT SEQUENCE OF EVENTS ---------------------- 11PROJECT MANAGEMENT ------------------------------ 12-13

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    AERONAUTICS AND1SPACEDMINISTRATIONWashington,). C. 20546~Phone: (202) 755-8370

    FOR RELEASE:Howard Allaway UPON RECEIPT'(Phone: 202/755-3680)James Kukowski (GSF--)(Phone: 301/982-4955)RELEASE NO: 72-17

    NASA TO LAUNCH EUROPEAN SPACECRAFT

    Another European satellite will be launched this monthby the National Aeronautics and Space Administration on areimbursable basis. The launch of the European Space ResearchOrganization's (ESRO) Highly Eccentric Orbit Satellite (HEOS-A2)is scheduled no earlier than January 30, from the WesternTest Range, Lompoc, Calif.

    The HEOS-A2 will expand man's knowledge of the magne-tosphere, the hugh teardrop-shaped envelope surrounding theEarth. It is formed by the solar wind "blowing" on the Earth'smagnetic field. The HEOS spacecraft, with its highly ellipticalpolar orbit, will travel through a region of the magnetospheredescribed as the northern neutral point where it is believedthat particles enter from interplanetary space.

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    This possible entry point for particles suggeststhat the magnetosphere differs in configuration betweenthe high latitudes and the lower latitudes. The HEOS-A2is the first spacecraft to investigate the high latitudeportion of the magnetosphere.

    A three-stage Delta rocket will be used to place thespacecraft into a highly elliptical orbit of approximately409 kilometers (253 statute miles) by 245,150 kilometers(151,995 statute miles) at an inclination of 90 degrees.

    After entering orbit the spacecraft (HEOS-2 in orbit) willstudy interplanetary physics and the high latitude magneto-sphere. The spacecraft carries seven experiments toinvestigate the strength and direction of the magnetic fieldsencountered, the energy distribution of protons and electrons,the nature of the solar winds, make very low frequency (VLF)solar observations and detect micrometeorites.

    The nature of the experiments requires that the spacecraftbe placed into the highly elliptical polar orbit with anapogee of approximately 38 Earth radii, outside the Earth'smagnetosphere and shockwave, and have a one-year minimumoperational lifetime.

    ESRO will reimburse NASA approximately $6.6 million forthe cost of the Delta launch vehicle and for required pre-launch and launch support services.

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    The HEOS is a 16-sided cylinder weighing 117 kilograms(257 pounds). Approximately 70 percent of its outer surfaceis covered by solar cells. A tripod-type boom is located onthe upper part of the spacecraft. It supports a magneticfield sensor and the RF antenna.

    During normal spacecraft operations, following insertioninto the planned orbit, HEOS will be controlled from theEuropean Space Operations Centre (BSOC), Darmstadt, WestGermany. Spacecraft tracking, data acquisition and commandoperations will be performed by the European Space TrackingStations (ESTRACK).

    The Delta launch vehicle will first boost the HEOS space-craft into a preliminary parking orbit. Subsequently,Delta's second stage rocket engine will be restarted andtogether with the third stage will place the spacecraft intoits planned highly elliptical orbit.

    The European Space Technology Centre (ESTEC), Noordwijk,Holland, has the project management responsibility for thismission.

    The Goddard Space Flight Center, Greenbelt, Md., isresponsible for NASA project management for the mission andfor project management of the Delta launch vehicle.

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    NASA's Kennedy Space Center, Western Test Range, willprovide prelaunch and launch support.

    (END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS)

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    -5-MISSION

    The orbit selected for HEOS is unique since nosatellite has flown in this region of space. The primaryscientific mission will be the investigation of inter-planetary space and of the high latitude magnetosphere andits boundary in the region of the northern neutral point.It is for this reason that a polar orbit has been selected.Scientific Objectives

    The space environment near the Earth which is controlledby either the Sun or the geomagnetic field is shown in figure1. It is predicted that at the boundary of the magnetosphere,where the magnetic field is nominally zero, neutral pointsexist. At these points the geomagnetic field lines changefrom being closed on the Sun-side to being swept back overthe polar caps to the night side. These neutral points arebelieved to serve as entry ports through the magnetic boundaryfor particles originated in interplanetary space. Further,it is also believed that the configuration of the shock frontand magnetopause are different at high latitudes compared withlow latitudes. Although much is known about the lowerlatitudes, the high latitude area has not yet been explored.It is for this reason this unique orbit for HEOS has beenselected and that the instrumentation of this satellite in-cludes a magnetometer and a number of particle countingexperiments. HEOS also carries a solar VLF observation experi-ment and a micrometeorite detector.Orbit Information

    In order to achieve the scientific objectives described4 above, an orbit with the following parameters has been selected:* Apogee: 245,150 kn (151,995 miles)

    Perigee: 409 km (253 miles)Inclination: 90 degreesThe selected orbit will guarantee that the apogee willremain outside the shock front for the rinyst 3l'CC day an.d tthe northern neutral point will be traversed during this period.

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    g SPACECRAFT DESCRIPTION

    The HEOS-A2 is a 16-sided cylinder having approximately70 percent of its outer surface covered by solar cells.The spacecraft weighs 117 kilograms (257 pounds. Thermalprotection for the interior and structural reinforcement areprovided by top and bottom panels.Acentral octagonal tube forms the primary structure andholds most of the spacec-raft's experiment instrumentation,i electronic controls, batteries, telemetry and command equip-p; ment. The sensors for experiments and the attitude sensor areA' located in the outer zone of the spacecraft. Experimentelectronics are located on the outside of the central octagonaltube. A tripod-type boom approximately 2 meters (6 feet) longis located on the upper portion of the octagonal tube. Theboom supports the sensor for the magnetic field vector experi-entnd the RF antenna.

    elecTwo noz zles for spin rate control are mounted in the space-craft's equatorial plane, and the nozzle for the attitude con-ltro is mounted in a canted position near the bottom ring ofthe 16-sided outer cylinder.tttoro e

    is l c t d o > h e o t on o h c a o a ue hboo suprstesnolo h antcfedvco xeimetan h R ntna

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    SPACECRAFT EXPERDENTS

    Magnetic Field MeasurementThe primary purpose of the magnetic field measurementexperiment is to determine the magnetic field vector ininterplanetary space and in the outer magnetosphere. Themeasurement range of this experiment is plus and minus 144gamma. The secondary purpose of this experiment is to per-form a low frequency noise measurement (1 to 5 Hz).Participating agency: Imperial College of Science and Tech-nology, London, England.

    Plasma MeasurementThe purpose of the plasma measurement experiment is todetermine the direction and to measure the energy level ofelectrons and protons inside and outside the magnetospherein the range of 20 ev to 50 kev. Participating agency:

    Instituto di Fiscia, Officine Galileo, University of Rome,Florence, Italy.VLF Solar Frequency Measurement

    The primary purpose of the VLF solar frequency measure-ment experiment is to measure the very low frequency (20 to250 Hz) emissions from the Sun. The secondary purpose ofthis experiment is to determine the amount of electrostaticand electromagnetic noise in the magnetosphere. Participatingagency: Danish Space Research Institute, Lyngby, Denmark.Particle Measurement

    The purpose of the particle measurement experiment is tomeasure energy and direction of electrons, protons and alphaparticles, in particular around the boundary of the polarmagnetosphere and the neutral point, as well as outside themagnetosphere. The energy levels will be measured in thefollowing ranges: electrons, 540 kev to 3.1 Mev; protons,8 to 32 Mev; and alpha particles, 32 to 132 Mev. Participatingagency: European Space and Technology Centre, Noordwijk, Holland.High Energy Electron Experiment

    The purpose of the high energy electron measurementexperiment is to measure the flux and energy spectrum ofprimary electrons in the range of 10-600 Mev. Participatingagencies: Instituto di Science Fisiche, University of Milan,Milan, Italy; and the Centre d'Etudes Nucleaires, Saclay, France.

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    -8-Solar Wind Measurement

    The solar wind measurement experiment consists of twoinstruments, either of which is selected by ground command.The one instrument will make measurements in interplanetaryspace to determine the direction and energy level of protonscoming from the Sun, in the range of 231 ev to 16 kev. Thesecond instrument will make measurements in the magnetosphereto determine the direction and energy level of protons andelectrons in the range of 100 ev to 50 kev. Participatingagency: Max Planck Institut fur Physik Und Astrophysik,Garching, Germany.ji Micrometeoroid Measurement

    The purpose of the micrometeoroid measurement experimentis to measure the flux, velocity and mass of micrometeoritesas a function of distance from Earth. Participating agency:Max Planck Institut fur Kernphysik, Heidelberg, Germany.

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    * -9 -DELTA-L LAUNCH VEHICLE CHARACTERISTICS

    Height: 32.3 meters (106 feet) (includesshroud)Maximum Diameter: 2.4 meters (8 feet) (without attachedsolids)Liftoff Weight: 89,050 kg (197,890 pounds)Liftoff Thrust: 326,000 poundsFirst Stage Modified Air Force Thor, producedby McDonnell Douglas AstronauticsCompany, engines produced by Rocket-dyne Division of North AmericanRockwell.Diameter: 2.4 meters (8 feet)

    - Height: 32.3 meters (75 feet)Propellants: RP-1 is thle fuel and liquid oxygen (LOX)is the oxidizer for the Thor stage.Thrust: 172,000 pounds at sea levelBurn time: 3 minutes 38 secondsGross weight: 69,750 kg (155,000 pounds)Strap-on Solids Three solid propellant Castor II rocketsproduced by the Thiokol Chemical Corp.

    i Diameter: .94 meters (31 Inches)Height: 7.3 meters (24 feet)Gross weight: 4,500 kg (10,000 pounds each)Thrust: 52,000 pounds eachBurn time: 38 seconds

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    -10-Second Stage Produced by McDonnell DouglasAstronautics Company, utilizingthe Aerojet General Corp. AJ10-118E Propulsion SystemPropellants: IRFNA/UDMHDiameter: 1.6 meters (5.3 feet)Height: 3.9 meters (12 feet 10 inches)Gross weight: 5,850 kg (13,000 pounds)Thrust: About 7,700 poundsBurn time: 369 seconds, first burn;10.3 seconds, second burnThird Stage Produced by McDonnell DouglasAstronautics Company, utilizirgthe United Technology Center FW-4Dsolid propellant rocket motorThrust: 5,910 pounds (vacuum)Gross weight: 313 kg (697 pounds)Burn time: 30.8 seconds

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    FLIGHT SEQUENCE OF EVENTSEvent Time

    Seconds Minutes/SecondsLiftoff T+0.000Solid Motorsburnout T+38.190 38 sec.

    Jettison solidmotors casing T+100.000 1 min. 40 sec.

    Main engine cutoff(MECO) T+218.513 3 min. 38 sec.Stage I-II

    separation T+223.563 3 min. 43 sec.Jettison fairing T+244.513 4 min. 4 sec.Second stage

    cutoff (JECO-I) T+593.489 9 min. 53 sec.Second stage restart T+2715.563 45 min. 15 sec.Second stage cutoff* (SECO-II) T+2725.852 45 min. 25 sec.Third staaeignition T+2770.513 46 min. 10 sec.Third stage burnout T+2801.313 46 min. 41 sec. fSpacecraftseparation T+28'i5.513 47 min. 55 sec.

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    -12-PROJECT MANAGEMENT

    ESRO Management PersonnelProject Manager Mr. Maurice Delahais, European SpaceTechnology Center (ESTEC)Project Scientist Dr. Bryan Taylor, ESTECOperations Director Mr. George Harris, Head, SpacecraftData Acquisition Department, ESOCSpacecraft Coordinator Mr. Hubert A. Bath, ESOCGoddard Management PersonnelDirector Dr. John FP Clark, Director, GoddardSpace Flight Center (GSFC)Launch Vehicle Mgr. Mr. William R. Schindler, DeltaProject Manager, GSFCProject Manager Mr. Robert Goss, Delta Projecc Office,

    GSFC

    Mission OperationsSystem Manager andMission Support Mgr. Mr. Robert G. Sanford, Project Opera-tions Branch, GSFCNetwork Support Mgr. Mr. Gerald A. David, Operations PlanningBranch, GSFCControl CenterOperations Mgr. Mr. Richard A. Schumacher, ControlCenter Operations Branch, GSFCOrbital ComputationsEngineer Mrs. Ellen L. Herring, OrbitalOperations Branch, GSFC

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    NASA HEADQUARTERS, Office of Space ScienceDr. John E. Naugle Associate Administrator for OSSVincent L. Johnson Deputy Associate Administrator, OSSJoseph B. Mahon Director, Launch VehiclesRobert W. Manville Manager, Small Launch Vehicles andInternational ProgramsIsaac T. Gillam Delta Program ManagerNASA Kennedy Space Center, Unmanned Launch OperationsDirector, Unmanned John NeilonLaunch OperationsManager, Western Test Henry R. Van Goey

    Range Operations Div.Spacecraft Coordinator Eugene Langenfeld

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