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    WO 2-4155AT ION AL AERONAUTICS A N D SPACE ADMINISTRATIONs WASHINGTON,D .C. 20546 W O 3-6925ELEASE: SUNDAYJune 2,

    RELEASE NO: 68-9791968

    GPO PRICE $1 CfSTl PRICELS) $I1contents Hard copy (HC)II Microfiche (MF) .rI

    ff 653 July 65

    5/28/68

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    NA TIO NA L AERONAUTICS AN D SPACE ADMINISTRATION WO -4155E W S WASHINGTON,D.C. 20546 TELS W O 3-6925FOR RELEASE: SUPJDAYJune 2, 1968

    RELEASE NO: 68-97

    SOUTH ATLANTIC ANOMALY PROBE

    Z"he National Aeronautics and Space Administration willlaunch from Natal, Brazil, a scientific payload to evaluatethe radiation environment over the South Atlantic. The launchis scheduled f o r no earlier ehan June 11.

    The South Atlantic Anomaly Probe (SAAP) is in supportof NASA's Apollo Program of' manned flights. It provides thecapability for a "fast response" evaluation of the SouthAtlantic Anomaly, a region of trapped radiation located overthe South Atlantic Ocean.

    PJASA will be assisted in the launch by the BrazilianComissao Nacional de Actividades Espaciais and persoonel atthe Barreria do Inferno range near Natal.

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    Launch vehicle f o r SAAP is the Black Brant Iv, atwo-stage solid-propellant vehicle m The 37-foo Brantw i l l boost the rscientl lf ic payload t o an al t i tu d e of 480nau t ica l mi les above the South Atlantic.

    e n t package, which weighs approx ima tely 80pounds, co ns is ts of magnetometers f o r magnetic f i e l d measuse-ments, a f ive-channel el ect ron spectrometer fo r defini ng thee l ec t r o n f lux of the Anomaly, three ion chambers f o r radia-tion dose measurements and a heavy ion de tec to r .

    Measuremenix withln the Anomaly w i l l begin when t h erocket reaches 360,000 f e e t a t 50 seconds into the f l i g h t .The experiment package will t ransmit data to ground s ta t i on sa t Bar re r ia do Inferno range. Data w i l l be collected on

    ouston, which is managing the SAAP Program,

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    -4-PRE-LAUNCH EVENTS

    The launch ve hic le buildup, the assembling o f the twostages and placement of the SAAP payload, begins a t T-5 daysand i s scheduled for completion a t T-2, The launch vehiclei s in s t a l le d on the launch r a i l s a t T-4 hours.

    T - 150 mins, in s t a l la t i on of te lemetryantennasT - 50 mins. launcher i s elevated to launch se t t ing ofT - 4 mins. payload switched t o in te r n a l power85 degreesT - 2 mins. range teleme try record ers "on"T - 30 secs. a l l l i g h t s GREEN on console, confirmT - 0 booster motors i gn i t e

    clearance to L / v

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    T plusT plusT plusT plusT plusT plusT plusT plusT plusT p l u s

    0 secs.18 secs .2 1 secs.28 secs ,33 secs .50 secs.lo3 secs .207 secs .473 secs.918 secs .

    -5-FLIGHT ENENTS

    F i r s t s t a g e ignitionF i r s t stage burnoutSecond stage i g n i t i o nSecond stage burnoutVehicle approachesmax ve loc i tySc ien t i f i c ins t rumenti n i t i a t e dFirs t s tage apogeeF i r s t s tage impactSecond stage apogeeSecond stage andinstrument u n i timpact .

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    60,000 ft.75,000 f t .150,000 ft.(Mach 11)65 miles200 miles200 miles downrange535 m i le s a l t i t u d e280 m i l e s downrange

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    -6 -EXPERIMENT HARDWARE

    I O N CHAKBER DOSIMETERload for measuring the radiation dose rate (See Fig. 1). Eachion chamber dosimeter is identical in mechahical and electricalcharacteristics, with the exception of removable shields overthe ion chambers. One instrument will have no shield; thesecond instrument will have a shield equivalent to the thick-ness of the Lunar Module (LM) structure; and the third dosi-meter's shield will be equivalent to the wall thickness ofthe Command Module crew compartment (CM),

    Each ion chamber contains three sub-assemblies; (SeeFig, 2) ion chamber, electrometer module and filter module.

    There are three ion chamber dosimeters on the SAAP pay-

    Ion Chamber - the ion chamber consists of two hemisphericaldomes separated by a 0.150 inch air gap, with an outer coverwhich is at ground potential (Fig, 3 Cross section sketch).Radiation penetration of the chamber causes ionization of thegas between the two electrodes and a current flow occurs.output current of the ion chamber, converts it to a logerith-mic voltage which is further amplified and produces it as a0 to 5-volt DC level analog output signal,

    Electrometer Module - the electrometer amplifies the linearFilter Module - the filter module is used to filterradio frequency (RF) interference from the voltage supply linesand to prevent the possibility of short circuit to the mainpower buss in the event of a catastrophic failure..

    Specifications Ion Chamber DosimeterWeight 1 poundSizeVolume 19.0 cubic inches

    24 x 3 x 4.5 inches

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    -7-SAAP ARE

    GEIGER TUBE S P E ~ ~ O ~ ~There i s one Geiger tube spectrometer package on the

    Data from th e spectrometer w i l l be used t o defineSAAP payload f o r measuring in te gr al e lec tr on energy l ev el sabove 0.359 1.0, 2.0, 3.5 and 6.0 mil l ion e l ec t ron vo l t s(PEV) .the ele ctr on spectrum i n the anomaly, (See Fig. 4) . Eachspectrometer contains f ive basic sub-assemblies: Geigertube, high voltage power supply, printed wiring boards,mother board, and f i l t e r module (See Fig. 5).

    - The Geiger tube sub-assemblyg makerial, mounting blockshelium and neon for the measurement ofe Geiger tubes are Halogen-quenchedgamma and high energy beta rad ia t ion .

    SUPP t p u t tha t i s required as th eoperat ing vol tage for the f i v e Gelger tubes,e high voltage power

    - Three pr in ted w i r i n gboar nents for voltage regu-l a t o r s and th e count ra te meter c i r c u i t s ,- The mother board, a p r i n t e dw i r i ects and provides a mountingsu r face fo r t h e f i l t e r module, high vol tag e power supply,p r i n t e d w i r i n g boards and Gelger tube sub-assemblies,- The f i l t e 7 module designi s t h used with 'the ion chamberdosimeter, F i l t e r s and fuses are used to maintain e l e c t r i -cably cle ar power l i ne s and prevent po ss ib i l i t ie s of shor tciGcuit t o main power i n t h e event of ca tas t roph ic fa i lu res ,jpe ctromet e r

    Weight 5 poundsSizeVolume

    4.5 x 4 e 5 x 4.5 inches92 cubic inches

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    5 A V Y ION EXPERIMENTThere is one five-channel Reavy Ion Detector on the SAAP.The six-pound experiment package, composed of three separatecomponents, is designed to determine the identity and energyspectrum of low energy particles for which extremely largetotal fluxes have recently been observed.Dr. B. J. O'Brien, Rice University, is co-investigatorf o r this experiment. The Space Physics Division of MSC'sScience and Applications Directorate, in cooperation with Dr.O'Brien, performed experiment conception, design, integrationand analysis.The Heavy Ion Detector is made up of the v e l o c i t y

    selector sensor, electronics package and data processor unit.The total package occupies approximately 140 cubic inches inthe SAAP payload.the heavy ions in the proper direction for measurement.Fig. 6).

    Velocity Selector Sensor - This five-channel device uides?SeeSize 2 x 2 x 7% in.Volume 33 cubic inchesData Processing Unit - This unit processes the data col-

    lected by the selector sensors and puts it into the properform for transmission to ground stations.SizeVolume 67 cubic inches

    65 x 38 x 2 3/4 inches

    Electronic Package - Contains basic high voltage supplyand electronic switching equipment. (See Fig. 7)Size 3 ~ 4 x 3n.Volume 40 cubic inches

    EXPERIMENT BATTERY PACKThere will be one battery pack (See Fig. 8) on the SAAPTheayload for supplying power to all experiment hardware.batteries are dry cell mercury-energized, packaged.in twocylindrical tubes with 12 cells per tube (See Fig. 9) .

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    - 8 ~

    Ffgure 3-more

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    Specifications for Experiment Battery Pack

    SizeVolumeWeightCells per tubeCells per packRated capacity

    Number of stagesOverall lengthGross weight

    LengthDiameterPropellant weightPropellant - solidThrustBurning time

    7 x 5 x 3 inchesl O 5 cubic inches12 pounds122413 amp-hoursBLACK BRANT IV

    Two37 feet 2 inches3,038 pounds

    First Stage210 inches17.2 inches1,760 poundsAmmonium-per-chlorate Poly-urethane-aluminum25,000 pounds13.2 seconds

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    Second Stage154 inches10.2 inches447 poundsAmmonium-perchloratePolyurethane-aluminum10,800 pounds7.5 seconds

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    SPLIT NOSE CONE

    b

    IBILIZER

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    PROJECT OFFICIALS

    Dr. J e r r y L. Modisette Projec t Sc ie nt is t , Chief,Space Physics Division, MannedSp ac ec ra ft Center, Houston,George BrandonW. Dan WomackJohn Lange

    Bristol AerospaceWinnipeg, CanadaHouston Aerospace

    Pro jec t Manager, Space PhysicsDivisionPayload Engineer, SpacePhysics Div.Sounding Rocket Branch,Goddard Space F l i g h t Center,Greenbelt, Md. '

    SAAP CONTRACTORSLimited Black Brant sounding rocketand pref l igh t t r a in ing , t e s tand launch support.Sss e m s Experiment in te g ra ti o n andDiv., Lockheed Missiles andSpace Corp. ground support.

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