imp-e press kit

8/8/2019 IMP-E Press Kit

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;E~W~U NAIIk VNAL AlIR IrIAIJIl(S AN() SPACE ADMINISTRATION TELS WI-WASIIlN(,lt)N 0)( 70'Afh Wr) 1-1,'s'7'

FOR RELEASEt TIURSDAY P.M.July 13J 1967RELEASE NO: 67-178

tA ~PROJECT: Inlterplane tary MonitoringPlatform-E (IMP-E)r (To be launched no earlierPO T than July 19, 1967)

CONTENTSGENERAL RELEASE.--------------------- ------- ----------6FLIGHT PLAN - ------------------------------------- 7SPACECRAFT -----------ma------------------------------

Spaeoraft Communications System--------------------8Power Supplym------------------------------------a --a 9Attitude Control Systema-----------------------------9Contamination Monitor-------------------------------9EXPERIMENTS -------------------------------------------- 0Magnetic Field Experiments--------------------------10Radiation Experiments-------------------------------10-12Solar Wind Experiment----------------------a-a-a 12Cosmic Dust Experimenta------------------------------ 13Passive Experiment a------------------------------aaalASolar Cell Damage Experiment--------------- a-------14DELTA LAUNCH ROCKET ----------------------------------m15Delta Statistics------------------------ --------- 15 16K MP-E PROJECT OFFICIALS, EXPERIMENTERS,AND MAJOR CONTRACTORS ------------------------------ 17-18IMP-E FACT SHEET-------------------------------------- 19-20

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NEWNATIONAL AERONAUTICS AND SPACE ADMINISTRATION TELS WO 2-4155WASHINGTOND.C. 20546 WO 3-6925FOR RELEASE: THURSDAY P. .July 13, 1967

RELEASE NO: 67-178

IMP-E LAUNCHSET JULY 19

AT CAPE KENNEDY

A scientific laboratory, designed to study interplanetaryspace phenomena in the vicinity of the Moon, is scheduled forlaunch by the National Aeronautics and Space Administrationno earlier than July 19 from Cape Kennedy, Fla.

The 230-pound spacecraft is the Interplanetary MonitoringPlatform-E (IMP-E), to be renamed Explorer XXXV in orbit.It will be the sixth IMP launched and the second one designedto collect data at lunar distances. IMP-D (Explorer XXXIII)was launched on July 1, 1966, and placed in a highly-ellipticalEarth orbit which carries the spacecraft beyond the distanceto the Moon and back.

The primary mission objective of the IMP-E is to studythe solar wind and interplanetary magnetic field at lurtrdistances and their interaction with the Moon. This can beaccomplished by orbiting the spacecraft around the Moon or byplacing it in an Earth orbit with an apogee near or beyond thevicinity of the Moon.

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Attainment of .a unar orbit would permit the secondaryobjectives of the IMP-E mission to be met, These includethe collection of data on the dust distributions around theMoon, the lunar gravitational field, the weak lunar ionosphereand the radiation environment.

Placing the IMP-E into orbit around the Moon anchorsit in interplanetary space and provides for the collectionof data over extended ;eriodL of time away from the influenceof the Earth's magnetic field. (The lunar magnetic field Isabout 1,000 times weaker than that of the 3arth,) Additionallysthe Moon's orbit would take IMP-E through the Earth'smagnetic tail once each lunar month (29.5 days) as comparedto once a year possible from highly-elliptical Earth orbits.

The launch vehicle employed for the IMP-E mission isthe three-stage thrust augmented Delta rocket. A smallthrust retromotor, mounted on top of IMP-E, will be fired bycommand at the direction of the mission control director atGoddard Space Flight Center, Greenbelt, Md. This will eithermake it possible for the Moon's gravitational field tocapture the spacecraft or limit IMP-E's apogee to near-lunardistances.

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-3-Since no trajectory adjustment will be made during the

planned 72-hour flight to the vicinity of the Moon, theflight trajectory must be exceedingly precise and the per-formance of the Delta rocket flawless if lunar orbit is tobe attained. The trajectory goal limits the launchingwindow to a daily three-minute period between July 19 and 22.This is one of the shortest launch periods for U.S. rocketmissions.

A decision to try for a lunar orbit will be made aboutsix hours after liftoff when the performanoe of the Delta'sthree stages can be evaluated. The probability of attaininga lunar orbit has been enhanced by an improved launch tra-jectory and the addition of an attitude control system toIMP-E.

The attitude control system will be used to reorient thespacecraft and its retromotor if this maneuver is required toobtain a lunar orbit or an improved lunar orbit. It can alsobe us6d to orient the spacecraft in its final orbit for thebenefit of the solar arrays and experiments.

If all goes well for a lunar orbit, the spaceoraft willattain a lunar orbit with an apolune or high point above theMoon of less than 28,500 statute miles and a perilune greaterthan 300 statute miles.

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The orbit period will be between 10 and 70 hoursdepending upon the orbit achieved. The orbit will be in-lined between 140 to 180 degrees to the Moon's equator.

If plaued into an elliptical Earth orbit, IMP-E wouldcircle the globe no more than once every two weeks with anapogee in the vicinity or 280,000 miles and a perigee ofapproximately 18,700 miles. The path of this orbit would beinclined initially 28 to 33 degrees to the Earth's equator.

With IMP-E in a lunar orbit, data from this spacecraftcan be correlated with that from Explorers XXXIII and XXXIV,two IMP-type spacecraft now in Earth orbit. This would offeran opportunity to separate the effects of the Sun on theEarth's magnetosphere from time effects on it. Themagnetosphere is an envelope formed by the interaction of thesolar wind with the Earth's magnetic field.

Valuable information about the effects of solar eventson the Earth's environment has already been obtained byExplorer XXXIII (IMP-D) and other IMP satellites along withOrbiting Geophysical Observatory (00o) spacecraft. Data fromthese spacecraft are also useful in determining the radiationand micrometeorite levels to be expected during Apollo flightsto the Moon as well as aiding in the eventual development of'a solar flare prediction capability for that program,

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-5-The IMP-E payload consists of seven scientific experiments,

two paassve experiments, and one engineering experiment--aaolar cell damage study. These were provided by scientists fromthe University of California, Berkeley; the University of Iowa,Iowa City; Stanford University, Palo Alto, Calif.; the Massa-chusetta Institute of Teohnology, Cambridge, Mass.; TempleUniversity, Philadelphia; NASA's Ames Research Center, MountainView, Cal., and Goddard Space Flight Centert Greenbelt, Md.

Wherever possible9 handling of all spacecraft components--as well au the fully assembled spacecraft--has been under atrictcleanroom conditions. Decontamination controls and proceduresfor the IMP-E have been highly effective resulting in theattalnment of the lowest level of contamination of any space-craft fabricated for any flight program to date. In addition,every effort has been made to make IMP-E magnetically clean.

The launching will be the 50th flight for the DeltaLaunch Vehicle. To date, Delta has achieved orbit 116 timesout of 49 attempts.

It will. be the 14th flight for NASA's Thrust-AugmentedImproved Delta which has the capability of hurling almostthree times more weight into orbit than the earlier Deltas.

The IMP spacecraft are part of the scientific spaceexploration program conducted by NASA's Office of Space Scienceand Applications.

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Projeot technical management for both programs indirected by the Goddard Spacoe Flight Center. The designsfabrioation and experiment integration of these spacecraftin conducted at Goddard with limited contractor support,

(END OF GENERAL RELEASE; BACKGROUND INFORMATION FOLLOWS)

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REQ WN1S OF EVESTIGATKNM

AIMP-E (RENAMED EXPLORER 35 ONCEILN WNR OR EARTH ORBIT)

SOLAZ WINDY MON lM*OON'S WAKEI

EXPLORER 34 (IMP-F)

RADIATIONBELTS

SOK WAVEEXPLER 33 ( ITMPD)

NEUTRALSHEET


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-7-THELI0T PLANThe three minute launoh window opens at the followingtimes for the indioated days:19th - 101I a.m. EYDT20th - 1l:1t a.m. EDT21st - 12:14 p.m. EDT22nd - 1:O9 p.m. EDTAfter liftoff, the Delta Launch Vehicle will be shootingat a target well ahead of the Moon. Orbital insertion shouJdoccur 72 hours after liftoff, about 3,000 miles ahead of theMoon when the retromotor is fired.The purpose of the retromotor is to decelerate thespacecraft as It approaches the Moon to a velocity slow enoughto allow it to be captured by the Moon's gravitational field,

or to slow the spacecraft so that the apogee in an Zarth orbitis about 280,000 miles.Ooddard's IMP-H Control Center will determine the timeof firing the retromotor about five or six hours after launching.Nominal burn tize of the motor Is about 20 Seoonda and itdevelops a thrust of about 916 pounds.About two hours after burnout, the retromotor will beseparated from the spacecraft either by ground command or byan automatic jettison system.

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ANCWDRW ViP LAUNCH SEOUENCESequence No Tomelsec Event

I 0 Liftoff2 43 Sol.d Motors Burnout Vc3 70 Jettison Solid Motors4 149 Main Eng ne Cutoff IQ5 153 Stage 11 Ignitson Signal IS/ "I6 154 Stage till Separation I\,7 216 Jettison FairingS 533 Stage 11Cutoff Comman|9 1315 Fire Spin Rockets Isomn Lp/

10 1317 Jettison Stage 11Active Retro System /11 1330 Staee ItI Ignition \12 1361 Stage h1 Burnout \ C13 1390 DeSpin Stage Ill.Spaceciaft /C14 145 Solar Cell Paddle Release /

0 1415 Flux gate Boom Release / 516 144.5 Spacecraft.'Stage itt Separation /17 Spin StabulLzed Coast / C CIS 08C Command Time Energiec/19 DBC-T Command Stage IV Ignition20 DBC-T-22 Stage IV Burnout c21 D8C-T-720C Separate Stage IV22 72 Hours Atter Spacecraft in Lunar Orbit ,/Ldtoff /

T =Timer/DBC - Determined By Computer O/ON C SEA H

\, THRU 169

NASA G67- 9'26


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THE SPACECRAFT

The 230-pound IMP-E spacecraft resembles the earlierOoddard-designed and built Interplanetary Monitoring Plat-form (IMP) spacecraft. The primary difference is an 82-poundr#ltromotor located on the top of the octagon-shaped main bodyof DMP-E. The standard IMP spacecraft, with the exception ofthe 1MP-F (Explorer xxXIv) carried a ball-shaped rubidiumvapor magnetometer at the end of an extendable boom in thislocation. Additionally, the transmitting antennas are nearerto the outer edge of the main body top cover on IMP-E.The spin-stabilied IMP-E carries an optical aspect sensorcapable of sensing the Moon or the Earth and the Sun to d&oer-mine the spin axis to plus or minus 5/lOths of a degree.Five of the seven experiments carried by IMP-E an wellas the spacecraft's mechanical and electrical systems arehoused inside the 28-inch diameter by a seven-inch high mainbody. The remaining two experiwents, fluxgate magnetometers,are carried on two booms extendring about seven feet out fromthe main body.

Spacecraft Communicationp SystemThe IMP-E communications sy.tam provides a radio linkbetween the spacecraft and Goddard'n worldwide Space Trackingand Data Acquisition Network (STADAN). Thin link will beused by the spacecraft for receiving ground-based commands aswell as range and range-rate signals. It will also be usedfor transmitting experiment and spacecraft housekeeping datafrom the spacecraft back to Earth.Transmitted power will be at least seven watts which iscapable of covering the distance between the Moon and theEarth. The telemetry transmitter operates on a frequency of136:110 mgahertz.

Power Supply

Like most unmanned spacecraft, the IMP-E operates onsolar power. Energy from the Sun is collected by 7,680solar cells located on four solar arrays attached to the mainspacecrift body. This system provides the power (38 wattsaverage) required to operate the spacecraft; systems and theexperiments.-more-


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Included in the power supply system is a battery paokto provide energy when the spacecraft in not in the sunlight.The battery is a sealad nonmagnetic silver-oadmium batterycomposed of 13 cells connected in series. It has an 11ampere-hour storage capability. This is sufficient to operatethe spacecraft and its experiments ror three and a half hourswithout recharge.

Attitude Control System

A cold gas (Freon 14) attitude control system 'scarried onboard the IMP-E. This system, operated by groundcommand, might be used to reorient the spacecraft along withthe fourth stage prior to ignition If required to achievelunar orbit or an enharoed Earth orbit. It will also beused to orient the spacecraft once it is in lunar orbit.This system is now to the IMP spacecraft.Contamination Monitor

The IMP-9 carries a contamination monitor designed todetermine the source of contamination which degraded the thermalcoatings on the top cover ot the IMP-D. Information fromthis monitor should prove useful in eliminating the contaminationsource on futur& spacecraft.The monitor system is located on the outboard edge of thespacecraft's top cover. It consists of associated electronic

and a collimated light source shining on a highly polishedsurface which reflects the light thvough focusing lons ontoa solar oell. If a contaminant coats the polished surface,the change in the reflootivity of the sarfaceo will be detected.The monitor will operate unt 4 l fourth stage separation.It will use part of the telemetry data assigned to the MITexperiment while in operation.

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-9'.-ANCHORED INTERPLANETARY MON IORING PLATFORM

109 r -- 54-RETRO MOTOR

GSFC FLUXOATEMAGNETOMETER

SOLAR PANELMAGNETOMETER

O EASUREMENTS SHOWN IN INCHES

ATTITUDE CONTROL SYSTEMNOZZLE (DOWN)

ATTITUDE CONTROL SYSTEMNOZZLE (UP)

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EXPERIMENTS

Magnetic Field Experiments

The basic devico for measuring magnetic fields ia themagnetometer. Two magnataumters--both of the fluxgate variety--are carried by the IMP. They were oontributed by the NASAGoddard Space Flight Center and the NASA Ames Research Center.

The Goddard Mognotomet-ei, This device consists of aboom-mountsa sernsor unIt located about seven seet from thecenter of IMP-H. Electronics for the device are mounted inthe maln body. It consists or three orthogonally-mountedfluxgate sensors, two of which are mounted perpendicular tothe spacecraft spin axis and one parallel to the spin axis.A flipper system will rotate the two sensors about 90 dogroeseach day to permit aalibration or the sensors which are parallelto the spin axis.This very sensitive device will be able to measurespatial and temporal variations of interplanetary and lunarmagnetic fields in ranges of from 0.1 to 64 gammas.The Ames MPanetometer. This device is also boom-mountedand is a thrMe-oomponent rluxgate device with a flipper mech-anisn.The sensors are arranged so that one is parallel to thespacecraft spin axis and two are perpendicular to the spinaxis. A flipper device reorients the array every 24 hourpby rotating two sensors about 90 degrees to permit caliblxtion.This magnetomeber is sensitive to magnetic rields fror0.2 to 200 gammas. In addition to measuring interplanetaryand lunar magnetic fields, the Ames magnetometer is designedto obtain information on the interaction of the solar windwith the lunar magnetic field.

Radiation ExperimentsThree different radiation detecting experiments will be

flown on the IMP-H. They include an energetic particles ex-periment designed by the University of California; an electronand proton experiment from the University of Iowa; and athermal ion and electron experiment from the Goddard SpaceFlight Center.-more-


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Energetic Particles Experiment. Designed and builtby the Unversity or California at Berkeley, this experimenthas the rollowing objoctives;* Measurement of low energy solar electronu. Recently,electrons with energies of 40 KeV were discovered beingemitted from solar flares. This experiment will provide moreinformation on solar and interplanetary correlations of theseparticles, their energy and spatial distribution.* The study or energetic electron fluxes in the geo-magnetic tail or the Earth's magnetosphere. From ExplorerXVIII (IMP-I) measurements it was found that isolated rluxesof high energy electrons occasionally appear in the geo-magnetic tail. It Is hoped data fron IMP-Ewill help indetermining how these electron "island" fluxes originate andwhat significano. they havie in relation to other phenomenaIn this region of space.* Low energy solar flare protons measurements will beconducted and the time history of these events obtained indetail.* An Ion chamber it.cluded with the expetiment will pro-

vide a monitor of the galactic cosmic ray intensity and ofsolar protons above 12 M*V.Electrons and Protons Experiment. Contributed by theUniversity or Iowa, the basic objectives of this experimentare to:* Study the spatial, temporal and angular distribution

of electrons with energies exceeding 40 KeV in the magneto-spheric wake of the Earth at distances up to 60 Earth radii.* Search for electrons with energies exceeding 40 KeYin the wake of the Moon, and to conduct a detailed study oftheir distribution, if in fact, intensities of this levelare deteoted.* Study the incidence and intensity of low-energy solarcosmic rays versus time profile (protons and alpha particlesseparately) in interplanetary space, and determine theirenergy speotra and angular distribution.* Study solar X-Rays in the 0-14 Angstrom range.The experiment consists of a series of three electrondevices having different view angles.

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Thermal Ion and Electron Experiment. Designed andbuilt by the Goddard Space Flight center, this experimenthas the following objeotives:* To measure low energy electrons and Ions in thevicinity of the Moon.* To detect the presence or absence ot a lunar magneto-sheath and/or shook front.* To obsorve the flow of the solar wind around theMoon.* To make a comparison with data from the MIT plasmaprobe to determine if the observed electron high energy oom-ponent as measured by an integral spectrum experiment can beinterpreted in terms of solar wind electron temperature andnumber density.The sensor for this experiment is also oa the Faradaycup variety.

Solar Wind ExperigentPlasma Probe. The single solar wind experiment onboardIMP-9 i called a plasma probe. It was provided by theMassachusetts Institute oa Technology and Is intended tomeasure the (ollowing phenomena:* Angular distribution oa the total proton flux in the

equatorial meridian plane oa the spaoecraft.* Energy distribution oa the proton flux at or nearthe same angle as the peak of the total proton flux.The sensorD a Faraday oup, is mounted with its directionof view at right angles to the spin axis of the spacecraft.As it rotates with the spacecraft, the variation of the signalwith time will be determined by the directional characteristics

oa the plasma in the equatorial plane and by the angplaracceptance function of the sensor itself. The experiment willmeasure the energy spectrum and angular distribution of theproton and electron flux of the plasma in the range of 100Key to 5 KoV.

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Solar Coll Dmage KxperimevtThe solar-cell damage study in a Ooddard Space PlightCenter engineering experiment which will provide informationon radiation damage to solar cells and solar-oll coverglass of varying thicknesses and aopositions, as well as onthe protection afforded solar calls by various types ofcover glass.An area on the spacecraft main body will carry a panel

of four groups of 16 one-by-two centimeter n-on-p siliconsolar cells. One group of cello will be unshielded. Thesecond will have an integral 25-micron cover glass. Thethird will have a six-mil fused silica cover glass. The fturthgroup will have a s*x-mil sicroshest cover.The 16 solar calls composing each group will beseries-conneoted to a 60-ohm preoision resistor of th lseorequired to produce a 4.0- to 4.5-volt output under 'spaco"conditions with normal illumination. The solar calls selotedare production items of a type which have undergone *xten-alve laboratory testing to determine electron and proton effects.Therefore, output variations among solar-call groups can berelated to solar-oell or solar-cell cover-glass damage. Athermistor Imbedded Jn the solar-cell panel Just under thecells will monitor variations In experiment temperature.To assure experiment accuracy, the cell groups will becalibrated for illumination, angle of incidence, and temperature

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-'5-THE DELTA LAUNCH ROCKET

The IMP-E will be launched by NASA.s Improved Delta rocket,The launch vehicles including a thrust-augmented Thor firststage, the enlarged Delta scond tage, and the PW-4 third stage,is known an the Thrust-Augmented Improved Delta (TAID),Delta project management in directed by the Ooddard SpaceFlight Center, Oreenbelt, Md. The Douglas Aircraft Co., SantaMonioa, Calif., in the prime contractor,

Delta StatisticsThe three-stage Delta for the IMP-E mission has the follow-ing characteristicsaHeight: 92 feet (includes shroud)Maximum Diameters 8 feet (without attached solids)Liftoff Weights about 75 tonsLiftoff Thrust: 333,820 pounds (including strap-on solids)First StNa (liquid only): Modified Air Force Thor, pro-duced'bysDouglas Aircraft Co., engines produced by RooketdyneDivision ol North American Aviation.Diameter: 8 feetHeight: 51 feetPropellantas RP-1 kerosene ts used as the fuel and liquidoxygen (LOX) is utilized as the oxidizer.Thrustc 172,000 poundsWeights Approximately 53 tonsStrqg.on Solids; Three solid propellant Sergeant rocketsproducea by the ohIokol Chemical Corp,Diameter: 31 inchesHeight: 19.8 feetWeight: 27,510 pounds (9,170 each)Thrusts 161,820 pounds (53,940 each)

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80aond st^>os Producod by the Douglas Aircraft Co.,utillizing thefojet-Goneral Corp, A8110-118 propulsion system;major contractors for the auto-pilot include Itinneapolis-Honeywell, Inca, Texas Instruments, Ina., and Blectrosolids Corp.Propellants: Liquid -- Unsymmetrioal Dimothyl Hydrasine

(UDMb) fo r the fuel and Inhibited Red Fuming Nitric Acid rorthe oxidizer.

Diameters 4.7 feet (compared to 2.7 root fo r the earlierDeltas)Height: 16 foetWeights 6t tons (compared to 2t tons (or the earlierDeltas)Thrusts about 7,800 poundsGuidance: Western Electric Co.4Thiv Stae:t United Technology Corp, PW-4Thrust; 5,450 poundeFuels solid propellantWeights about 660 poundsLengths about 62 inchesDiameter: 19t6 inches

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t -17-IMP-E PROJECT OPFICIALS EXPERIMENTERS,

AND MAJOR CONTRACTORSNASA Headquarters

Dr. Homer S. Newell, Associate Administrator for SpaceScience and Applications.Jesse E. Mitchell, Director, Physics and Astronomy Programs.Prank W. Gaetano, Associate Program Manager.Dr. A. Schardt, Program Scientist.Robert W. Manville, Delta Program Manager.

Goddard Space Plight CenterPaul O. Marcotte, Project Manager,Jeremiah J. Madden, Assistant Project Manager.Dr. Norman R, Ness, Project Scientist.John J. Brahm, Project Coordinator.Peter L. Luppino, Tracking and Data Manager.William B. Schindler, Delta Project Manager.

Kennedy Spgace CenterRobert H. Gray, Assistant Director, Unianned Launoh Operations,Kennedy Space Center.

ExperimentersActiveDr. K. A. Anderson, University of California (Berkeley)Energetic Particle Plux.Dr. James A. Van Allen, University of IowaElectrons and IProtons.Dr. H. S. Bridge, Massachusetts Institute of TechnologyPlasma Probe.Dr. Charles P. Sonett, NASA Ames Research CenterMagnetometer,

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Dr, Norman F. Ness, NASA Goddard Space Flight CenterMagnetometer.Dr. J. L. Bohn and W. M. Alexander, Temple University(Philadelphia) Micrometeorite Flux Experiment.Gideon P. Serbu and Dr. Eugene J. Maier, NASA Goddard SpaceFlight Center Thermal Ion and Electron.Luther W. Slifer, Jr., NASA Goddard Space Flight CenterSolar Coll Damage.

PassiveDr. A. M. Peterson, Stanford UniversityLunar Ionosphere and Radiowave Propagation(Passive experiment using spacecrart telemetry signal)Dr. W. M. Kaula, University of California (Los Angeles)Selenodetic Studios (Passive experiment based on analysisor range of range-rate tracking data)

Major ContractorsAerospace Division, Westinghouse Electric Corp., Baltimore,Md.Space Integration.Douglas Aircraft Co., Santa Monica, Calif.Delta Rocket.Thiokol Chemical Corp., Elkton, Md.Thiokol TE.m. 458 Retro Motor.

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-19-IMP-E FACT SHEET

Launch: Four-day launch window (three minutes each day)beginning July 19, 1967, at Launch Complex 17, CapeKennedy, Fla.Launch Rocket: Thrust-Augmented Improved Delta (TAID), withThiokol retromotor mounted in base of space-

craft to achieve luncr orbl.t.Lunar Orbit: Apolune: less than 28,500 statute milesPerilune: greater than 300 statute mileBPeriod: between 10 and 70 hoursInclination: between 140 and 180 degrees to Moon'sequatorEarth Orbit: Apogee: about 280,000 statute milesPerigee: about 18,700 statute milesPeriod: more than two weeksInclination: 28 to 31 degrees initially2acecraft Welpts 230 pounds including 82-pound retrouotor, withabout 30 pounds of experiments.Main Structure: Octagon shape, 28 Inches by 28 inches, 34 incheshigh (from top of third stage adapter to topof retromotor).Appendages: Your rectangular-shaped solar panels.Your tranhlitting antennas, 16 inches long.Two hinGed. agnetometer booms about seven feet long.Power Ystem: Power Supply: Slar cells mountod on four panelsto supply average power of 36 wattswith one silver cadmium batterycapable or tupplyang 45 wattf orpower for thrs and ong-hwla houro.Cosmunications and Data-Handllng System:

Telemetry: Pulsed-frequency modulation phase-modulated (PPM-PM).Transmitter: Seven watt output at a frequency of 136:110mcEncoder: ?PR with digital data processor (DDP) fo r accumu-lation and storage of data.

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Tracking and Data-Acquisition Stations: Space Tracking and DataAcquisition Network (STADAN)operated by GoddardSpace Flight Center withprimary stations located at:Tracking: Carnarvon, AustraliaSantiago, ChileTananarive, MalagasyRosman, North CarolinaTelemetry: Tananarive, NalagasyJohannesburg, Republic or South AfricaSantiago, ChileOrroral, AustraliaRosman, North CarolinaFairbanks, Alaska

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imp-e press kit

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