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S'l.IENTIFIC AND TECHNICAL INFORMATIONCAMERON STATION AIEXANORIA. VIRGINIA

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OPERATION ARGUS *

SA4TELLITE LAUNCING from AIRCAFT(U

Weapons Development Department '-U.S. Naval Ordnance Test StationChina Lake, California

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AsSTracTIn the fall of 195? tow Naval Ordnance Teat Stationa 0N .) was studlying the feasilllty of launch-ing an observation television sattallite from an aircraft. In the spring of !M5, when plans forthe Argue experiments were being developed, it was proposed and accepted that the air-launchedvehlcle under development at NOTS be utilized to place a scuWWllatlon counter in polar orbit.Tis payload was to be used to detect and measure trapped electrons from the nucliar detona-

tions thatl were to be employed to test the Chrlstoitlos theory. The primary iaarvimentatlon W.rthe expiertments was carried in Raplorer W., and the NOTS satellite payload was to be uwd asadditional, back-up Instrumentation.

The vehicle was to br launched at high altitude in a loft maneuver from an lntere-r- air-craft The vehicle conalasted of-a five-stage. unguided, solid-foeled ballistic rocket weighingapproximately 3,150 pounds. Ignitioet of the rocket motorn was staged by electronic timers,eacepit for the third stage, which was to be fired at a giv* n angle to the horizon as measuredby an infrared telescope. The first two s.ages of the vehicle were fi n-stabilixed. and the lastthree were spin-stabtllsed. The filth-stage rtotr was retro-mowuted. The spinning fifth stage.which was to carry the payload, would have acted as a gyroscope and thus sialatalned orientationin Inertia space while cossting around to approlmntely the antipodal point; at this point the filth-stage motor. oriented properly with the velocity vector, would have beo fired, Placing the pay-load into the desired orbit.

Wthdn the span of 6 monills the satellite vehicle and payload were designed, developed, and, .tested, andl six complete systems were marsdactured and Launched from an F4D-l aircraft overthe ftacillc Missile RaWg. Three orbital attempts employing diagnostic payload& were made inlate July ad early August 1958. and three final attempts to place the payloada in isrhit were mad.on 25, 36, and 24 Aumus 1"#.

All firings. except the one on 22 August, malfunctioned during firist-xAa:# propgai,ln. Crvs.tal control of the diagnostic payload transmitter frequency was lost :ust prior to laui.. h on the22 August firing. Three ossible passes were rec.'rd, but a complete review of the data couldnot justily an orbital claim.

A world-wide network of microlock stations was buailt for inatraimentatlon. These stationswere located in New Ze&aand the Azores. Alaska. Greenland. aKId Cluna Lake, California.These stations were used to gather International Gercohysial Yeal (KGY) data itno to monitor the ~ .,

Explorer IV instrumentation. and were ready to receive if the pilot satellite had been s~ucers.stul.Although NOTSs efforts on this project were not completely successful, much valuable inlor-

mation was obtaineit that should be applicable tON reLAted projects uf the future. In addition tothose accompllahnenast aLreadv mentioned, the following are par-truarly significart:

1. The fly-up aircraft satellite-taunch ti-lque was successfully demonstrated. This in-eluded outfitting &Ad calibrating two F4D- I aircraft for launiching vehicles and training fourpilots in launching technuiques. The Launching conditions for all full.-Neale firings were withintolerances, thuas the aircraft maneuver reliability and reproducibility were successfully demon-strat-I

2. The 121 structure weight of the vehicle was limited to 5 Percent of the overall vehicleweight. This required the development of three new rocket motors with high performance index.

3. An igniter was developed and testted under %imulatted 180.00-foot &ltitude.4. An ITIM Program for computing - thicle Performance, misile tolerances, and ephemerides

for satellites from doppler data hits beet% developed. This method af comnrpultiig ephovmer,.des hasbeen applied to doppler 'tita rtceivtd from Explorer rV. A six-detrees-af-f reedoni programstudy has also been completed for deterinat ion of orbital trajectories concurrently with stabt.MlY studies.

4

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5. In the development, matiuaacture, and operation of the mlcrolock grourd receivir sta-tions an improved capabtdty for .,d frequency *can tus been obtained, and these poa table

stations can now be shipped a nwriere in the world and be set into operation within 3 to 4 hoursafter arrival at the chosen locatton. The data obtained by the NOTS stations are reported tobe among the most useful data that were obtained for IGY and Operation Argus.

6. A 2.3-pound radiation counter and a diagnostic payload of the same weight have been dc-signed, developed, and manulactured. The radiation-counter payloads were used in the lastthree orbital attempts.

The report documents the development ard testing of the aircralt-lainched satellite-vehiclesystem and discusses major component d&velopments and tests.

It Is believed that in addition to the contribution made to OperAtior. Argus. the exeriencegained in this program greatly enhanced the Nation's capabilities in space research and develup-mert, and that many of the components developed will find a recurrinc app.ication in thib coun.try's spAce program.

. - 7

CONTENTSABSTRACT -- - - - - - - - - - - - - - - - - - - - - - - - - - 4

VEHICLE AND ORBITAL CONCZPr ------------------

GROUND LAUNCHING OF STRUCTURAL TEST VEHICLES. ----------- 1

AIRFRAME DEVELOPMENT ANrL AIRCRAFT COMPATI]BILITY -- ------- 1

Aerodyn~amics ......................... IsAeciodYnamie Heating ............ .......... 15Load Criteria .............. ............ 1Aircraft Compatibility and L.Aunchi~ng ................. 19 f

SCINTILLATION COUNTER PAYLOAD .. ............... 20

Instrumentation .. . . . . . . . . . . . . . . . . . . . . . . 24Transmitter ................... ...... 25Si.licarrter Generators ....................... 1ModulIation System . . . . . . . . . . . . . . . . . . . . . .. 26Antenna System ......... ............... 26Weight Limitations .............. ......... 30Packaging . . . . . . . . . . . . . . . . . . . . . . . . .. 303ource of Por.................. r....... 31Other ConswderatIons .. . . . . . . . . . . . . . . . . . . . . 31Trakng......................... . ... 2

PROGRAMMING SYSTEM ...................... 32

HORtIZON-SCANNER TESTS ..................... 32

CONCLUSIONS.................................................... 39

TABLES

1 Physical Characteristics of Stages I throuith 5 of the Vehicles ............ .. 142 Summary of NOTS Project Field Tr~t Work............................ 203 Weight Table for Typical Pavi~ad................................... 254 SimmarY CA NOTS I Test Results................................... 3

FIGURES

I Air-launched satellite and Afrpjs project team........................... 102 Air-launched vehicle. concept......................................10o3 Air-lAuticned vehicie............................................I

47

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4 Loading vehicle on aircraft -- - - - - - - - - -- - - - - - - - - I I5First-stage flight of vehile 1 2

6 HOITROC stAg motoi- -.. . ............... 127 Third-stag motor (ABL 241)........................................- -- - - --- -12U Foutrth- and fifth-stag motor With satellite payload........................ - --- -139 Propellant machinin 8.0-inch extrnaded charge...........................1310 FLfth-staC retro-rocket moo ........................ 16I I Stall.: testing of first- and seonid-stage motor cluster.....................1612 Satelte vehicle on ground !Aucher with land-line telemetering equipment...--1713 &tic-load testing of airframe structure...............................1714 Ailrobaillistic Laboratory models - - - - - - - - - - - - - - - - - 115 Satellite vehicle airframe srurae..................................1616 Vehicle flutter-f n test on B-4 tr'ack..................................1217 Tinat inspection of vehicle....................................... 2118 Complete payload packag --------------------------------------.. 2114 Piaotomultplier-swctttlator complrl.............................. 220 Pulse-height discriminator and scary............................... 2221 Power-supply inverter...........................................2322 Transmitter and subearrier oscillators................................2323 Fourth. and I iftb-stage timer being assembled in nose of veh~icle .............. 2424 Sceomatic of the scintillator counter ................................. 2625 Circuit diagram of the RF transmitter &M4 modulator..................... 2726 Cross-sectional1 view of noe cone and pal.......................... 292's End view ofnow cone and payload.................................. 2918 Antenna- element assembly....................................... 2929 Antenna elements............................................. 303O Payload case anld antenna........................................ 3131 Horizon scanner in vehicle assembly................................ 3332 Scanner test veldele on ground launcher.............................. 3333 htlcrolock grouid-receiver station.................334 Locations of mici olock ground. receiver ntations........................ 3535 hllrrolock station equipment in shipping packages........................ 3536 bllcroloc, site in Aliaka........................................ 3637 Microlock site in New Zealand.................................... 3636 Doppler frequency ahaft versus time .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. .. 3739 Equations for linear and square-law detection. .. .. .. .. .. .. .. .. .. .. .. .. 37

SAELLITE LAUAtW/MA frMM A/A CRA4FTVEHICL1 AND ORBrrTAL CONCEPT

For- certain applications and for L~achin a relatively small payload. a satelltv, vehiclelaunched from an aircraft has. many adviatagets because U- its Ase. relatively low cost. versa-tity, aid general utility. lRudls undert.aken prior to Oiperation Arguis indicated that a vehicleCould be designed wnti:h woul1d be inherently simple to maonuacture. transport. asjirmble. checkout. and Liunch. 'The estimated cost was low, a&M reliability was believed to be hlich. since theVehile would use simple controls and reliable solid-propellanit boosters and could be providedlwith redlundiart firing circuits.

Figure I Illustrates the skrcrait-launched vehicle as originally conceived amd the Argus prol-cl team during the early stages of the program.

Table I shows the physical characteristics of Stages I through 5 of the vehicle.Figure ? illustraies the launching concept and the sequence of various stagies from aircraft

launch to orbit.The satellite vehicle was to be launched at high altitude inS aloft maneuver by an F413-1 Iinter-

ceptor aircraft. Tlie vehicle was designed to place a 2.3-pound payloadl in a 1,000-mite orbit. -

It was a five-s-ile, unguided. solid-fuel, bealit rocke-t which weighed Approximately 2,150pounds. Ignition of the rocket motors was to he staged byy meiting time with electronic devicesexcept for the third stage. which was fired on an angtle to the horizon aa measured by an infraredscanner. AUl stages wert to be separated from the previnsa expended stage by thrusti forces atign~ition, except for the ftfth stage (which was to be disconnected by a small separation chwrcei.The first two propulsion stages were fin-stabilized and the last thre were sinutsabized. Thefifth-Atage motor was retro- mooned. i.er. . its nozzle pointied oipposie to the other noexirs.The first lout stages of propulsion were to give the fifth stage a horiontal velocity greater thanthat required for orbiting at the altitude of buirnout tapproximately 50 milesi of the fourth 515ev.The spinntng fifth stage wouild act as a aroc(pe and, therefore. minutailn a fixed orientAtion,n inertial space while coasitig around to approhimati .y the antipodal point; at this point the .

filth-stage motor, oriented properly with the velocity vector, was to he fired, placing the pay-.load into desired orbit.

Figure 3 is a ptitocraph of a complete vehicle aibi~mbly. Ftgure 4 shows the vehicle being ~mouunted on the- launching aircraft, a&M Figure 5 is a photograph of the vehicle during the firststage tA flight.

Duiring 'he development of the satelllto-ehicle system. numerous facilities and skills avail.able at the Naval Ordnance Test Station (NOTSI were brougt to bear on the program. practi-cally all compocnents were designec, fabricated, and tCWstoi the research and dervelopmewntlaboratories and thei en.~tneering shops. Figures 6 through 10 show a number 4f the hardwarecomponents of the propulsion system.

F~lturr 6 is a picture of the metal parts for tine of Mt.. four motors in the first- an seorld-stAge cluster. This is the HOTROC motor. Fikure -. is a photograph of the third-btagte molvor,which was procured froct in. Alleghany flallistic Laboratory. This motor. designated ARtL 241.

* .s R " pe..-..!Ant charge. Figure 8 is a photograph of the fourth-stage 4.0-int-h imotor andthe payload into which is mounted the filth-stagle retre rocket. Figure 9 s11ws the machiningoperation developed for processing the 8.0- Inch extruded prolpellant charge for thas motor. Thepropellant is jPN. Figure 10 is a photograph (if iii fith stage 3.0-inch-diameter retro rocket.This Motor employs extrudedJ double-tase X. 14 prrpollant, which is subsequently machined to

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TABLE I PHYSICAL CHARACTEISTICS OF STAGES 1 THROUGH 3 OF THE VCI4ICL&Z

Itaw Weight StAV Sa Ttl.uan 7%" Hostie~ c~be.u

Weight Weight lmow"s Ti. Tru i A,lII lb Ilb lb-sec Sac lb Iih

lot Sup~:Motor meta perts 142Propiellant $43 2.154.03 I.1.03 140.500 3.47 40.430 13 .133 se level

Motor metal perts 142Propellant 443

fadrisg. Umr. 100 3512.09 Af4.09 140.500 3.7 440 ? 21OdIco

Motor metal parts 54Fairing t0 482.09 305.09 9A'08 !6 2.724 Vae :60.1 fAlt)

44&0CPropellant 27.5Fairing ead timier 1.24 .19.09 I 3.59 7,0120 S 1.404 vac 255 WAl

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CONFIDENTIAL

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a spherical stape to mate with the motor chamber. Figure I1I shows the static test facility forthe cluster of HCYTROC firs- andl second-stage motors.

GROUND LAUNCHING OF STRUCTURAL TEST VEHICLES

Four structural test vehicles wetre ground launched from the NOTS G-2 range to evaluate the

integrity of the vehicle design. Two of these vehicles were instrumented with land-line telem- -.-

etering equipment. Figure 12 shows the vehicle on the ground launcher. Prior to the assembly

frame. Figure 13 shows the static-load test bet-up for evaluating the bird-cage section of theairframe.

All ground- launching tests were made in July and August of 195R. These tests employed li~-first-stage motors. In the first test, camera recordet showed that one of the first-btage IIOTHOCmotors ruptured 0.7 second after !aunch. Examination o4 the misbile after firing indicated a rup-tured motor case, which was attributed to a marginai dlesign or cracked propcllant charge. Twoadditional structural test vehiicles were launched on 16 and 1'. Auicubt. Ground-camre'rA reir(!showed that bcth vehicles failed at approuimiaitel 3 secontis after launch near tne end Wf burning.of the first-stage motors. These were believ~ed to be propulsion fjiiureb. The stabilizing fin.also failed to withstand the air loads imposed by firing the round on the gcroiund: however, thisproblem would not be present in the normal aircraft launching of the missile.

In the fina~l ground-tiring test, tne lurst- Stage motor blew up on the launcher at ignition. AtIs believed that a faulty propellant charge was the cause of this failure.

Since all four attempts at ground launchings were unsuccessful %nd attributable to first-stage Ppropiulsioun problems, every effort was madc: to Increase the quality control in the Manufactureof the pro~pellant charges. The design of the propulsion system was known to be Marginal, buttime was rmssig out to meet the deadline,. hence, it was necessary to seite for quality controlmeasures in lieu of a rtessign of the first-stage propulsion unit.

AIRFRAME DEVELOPMENT A"D AIRCRAFT COMPATIBILITY

Aerodynamics. The specifications for the externs' geometry of the vehicle were determinedafter wuwa-tunnel tests and a series ol scale-motiel firings in the Aerobsilistics Laboratory.Figure 14 shows the scale model& for these tests along with the sabos for use in firing themodels from a S-inch guna.

The static aerodynamic stability and dynamic stability of all the rigid-body modes of motionwere investigated. A quasi-steady analysis of the stability of the vehicle snd Its various stageswas worked out and stability criteria established. Figure 1S reveals the airframe, structure orbird-cage portion ad the vehicle,

A complete six- degrees- of -freedom simulation and program has been mechanized for theIBM 704, making it possible to examine stability concurrently with the determination of orbitaltrajectories.

Studies of the aerodynamic coefficientb of the final vehicle were made at the Naval Ordnance A

Laboratory, White Oak, Maryland. This data was used by the Naval Proving Ground, [~hlgren,

Development Center computer facility.

Aerodynamic Heating, Aerodynaine heating was studied with a racilant-hest facility to deter-mine the so11tty oi the nose cone, payload, and iirst-sage stabilisina finst, including most of theexternal structure of the vehicle, to stand the predicted environment,

Load Criteria, Loads on the vehicle were examined both as an airtxorve store and as a free-flight vehicle,

The fin structure was tested for ttrengKth and flutter over a limited range, )f conditions oy afull-scale tests on the HOTS DBaler-4 track. Figure lb shows the veh-elo on the track awaiting

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Aircrait Compatibility and Launching. A compatible iz.allatiun of the vehicle %xi the F4D-laircraft WaU ac:Ueved. The aircraft performance was investigated relative to the detertnatIonuf the cptimum pull-up trajectory (or Launching by the Duglas Aircraft Company (DAC). AaOa limited wnd-tunnel program was condicted with 114C to investigate the release, launch. andseparation of the vehicle from tho aircraft.

Instrumented dummy sto; es were flown on the aircraft to determine aircraft and missileloads during aUl phases -it the airborne flight from takeoffI to missile release. Also, after theLASS gear was calibrated, the maneuver wasn practiced for consistency without dropping the,

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rigure 16 Vehicle flutter fin test on B-4 track.

store. On each run, internal aircraft instrumentation as well as external camera coveragerecorded the aircraft performance.

Four preliminarv test flights were made to 4etermine if the F41) aircraft could perform therequired maneuver for launching the satellite vete W ItWAS learned that the !'9.degree pull-up ,'could be achieved. TWO flight$ were then sueCteSal'Y Made at a 511-dogree pull-up as an aero- RIballistic shape simulating the vehicle was dropped.

List rumentatiton of the six attempted aunchings for oroit revealed the boilowin results: .

Desired Launch Average for Six Firiiigs Minimum Mauimum

Speed, 700 !, sec 689 670 750Angle of taunt lu 39 deg 58 5". 60Altitude. 35.NOO It r'no5 35.800 3 7.5 10

Tihie- 2 is a summary of the irhlm'narv tets carried out to evaluate ttv vehicle design.Figure 17t shows a compt e'hicle structure rerivmn final inspection in the vi141neering ,

shop prior to hempg loaded In,' subst-4uent evaluation. -

The purpoie of the srintilation counter was to measure beta radiation In a poilar-orbiting

satellite in conjunction with the Argus experiments

CONFIDENTIAL

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Operational specticatioas and circuiLry for the instrumentation were provided by James VanAllon, of the State University of Iowa. Physical design and constructiom systems compatibilitystudies, testing, and calibration were accomplisheo by Personnel of NMT.

The completed payload was to measure beta radiation that exceeded I.' Mew energy level,with the informaition telemetered back to earth via an Flf-FM system. modulated by the output

CABLE 2 SUMMARY OF NOTS PROJECT FIELD TEST WORK

Tests colductad at China Lake. California. STV- Struclural Test Vehicle.aisTpe t~e.NfumberNo. P 9 Type )I 1I of P rocesaii

Inatruments

9 Jun I G-1 F41 AMicraft .W pull-up 22 24 hirIGI Jun 2 G-I F40 Aircraft 55" pull-up and drop .2 No data13 Jun 3 G-1 F40 Aircraft SS' pull-up and droo 22 365r .13 Jun 4 G-1 4D Aircraft SS' pull-up and drop 2.. .V1 hr

f Jun I G-I Ground launch horaton scanner 9 * ak13 Jun 2 G-1 Ground launch horsin stcanner 9 I rk

28 Jun 3 (;-I Ground lasinch ihariton bcanmwr 4 2k IJ41 4 G-I Ground 1aunch horston scanner 1.4 k "

14 Jul I U-I F4) A rerad S 4 p4 Il-up. no drop 2 1 .k.I9 Jul 2 G-1 4 Aircraft SK pul-op. n.. drop "2 I ak19 Jul 3 G-I F41) Aircraft 51' pull-up. n drop 22 24 hr

"3 Jul 4 G-I N4U Aircraft S I puill-up. an Vd 2 I ak23 Jul S G-1 Y40 Aircraft U6' pull-up Rod drop .: 4 h.r23 Jul 6 G-1 F4 Aircraft 5n pull-up. no drop 22 I wk23 Jul 7 (-1 F40 Aircraft S' pull-up and drop 22 A4 h.

IA Jul I G-1 H4rio0 scamr Ianchaid from 9 M atF3D Aircraft

20 Jul 2 G-I Haerlu scasr laftcr d from 9 -

r7D Aircraft20 Aug I G-I Preliminary launch of STV from 21 24 hr

F40 Airreft4 Jul I 0-2 Grmumr la cah STV so % hr

20 Jul I G-2 Ground launch .TV $1 \.. coverq.

I Aug I G-2 Grmand Isunv. 5l V 4 .4 hr17 Aut 2 G-2 Ground launch S-V 54 .4 hr

4 R-4 Fn-rFlutter Tel - - aA Jun I 11-4 A¢celerati n 3 '.- proceaa.a

IS Aug - - rysa Hahesraal 14 . -

'lime requir d after firing for dat primiteria

of two scalers, which were scaling 64 and 4,096 times. The payload Wus to I.avt, e inlnimum

radiated power of 2S ow. nominally. operating at 108.00 Mr. ani with an expected life of 2weeks. Tao standard subcarrers %tt 960 and 1.300 cyrles median frequency were spectllea. I.

Figure 18 shows a complete paylned packare. Figures 19 through 22 show compoments of thepayload. Figure 23 shows the timer for the two last-sta,'r motors being assemled in the ntipe'if the vehicle.

A severe maximum weight limitation of 2.3 pounli for the complete parkage preaented sev-eral difitcult problems In design and miniaturization to be solved by the personnel of NOTS. Aweight table for a completed payload IS given in Table 3. t

The payload development Includil desgn of a miniaturized RF transmitter using only tran-ststors. iraii.-ormerles. subcrrier generators using a temperature stabilized R-C type of "

frequency control system, and tranaformerless FM modulating system for the RF transmitter.

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These included m tiL- preamplfier for adjustmet of the modaion idices. with all modit-

.aintl circuits optratift from the same batteries as the Rr transtrl'.ter.Amxthe- atifltcilt problem in design was the ameflm system. Rt load two modes of opersttm:

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lLitrumenta Iionf. The sintllIA11i11n COtnIrr rna.Aedl of a plaii %cintilfator cemented to theface of W t;6~i9 phoitomulliplier tube. ih a pure-aluminum alitiirer to limit th, mpa,.ure.mw-nt'. to %ullictentlih O nrrg lw-tel. And a special aluminujm collimatoir tare Fiivure 191. ftalxn l.ad a rulmt *hrichlt tit-criminat',r to1 -it the entircv lw-l for c-onting at LS5 Mre or above.ith tcaler c4-itjerA -LI 64 And 4.0%~ times and emmtr-ollowtr noputs for keying the aubrar-

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.is.< Ela

tnclucked with the instrumentation sect ion was design and construction of a regulated high-voltage sciuece. utiliin a translsia t coler system is"~ tLgurc 24).

Transmitter. The tranasmitter operated at 101.00 Mc nominally, with the frequency coestrolled ~Vto close tolerance by means of a third-overtone crystal. The oscil~tor, utilizing a Type 'N300transistor, operated at 54.00 Mc. driving a doubler-asmpl ifier that utilized two Type 224500 tran-sistors in a parallel-grounded base configuration. The FMA transmitter delivered 30 mv to theAntenna system, the output level being adjusted to the desired amnt by proper selection of ablas-resistance. limiting-emnitter current in the oscillator. Th~s adjustmet was made priorto potting in the completed payload.

Frequency modulation of the tranmitter was accomplished by varying the voltage applied tothe oscillator, in accordance with the combined subcarrier nxdtawatc signal, v-a the special

TABLE 3 Wr.IGtIT TABLE FORi TYPICAL PAYLOAL)

NOlTS Pro)tect Psvoed. T'pe A I~"l

Items AiltI'Grams

1, Ilije? ase amd cocer 2 *e

3.Turnstile antienna, cupsa 5d5 covers 134. Prlling cmiund 115S, B~atteries ifor --44 "or ,nirraioei 44. High Nviu s p *UfotIV eOr'Citr 552~

iMagneei' siel~d io-. Phioomuipteer tube 1ICA *i''

Colliemaor I'.1-1. Adapter4it. Plastic ' sieid

iPuiso-hagcit discrimeir-iM Stcsirs (thre %,I-. ull turae'..

modulating swithrn. The indext oi modulation as Adiuied t1% .ettit the levels. of the indvi dualsubcarrior -icntals. FI'mure 2Sc i ihe -'ircuit di~iirain .' the RI' tra-%miiierrid moicdlatr

Suibcarrier Genet Alors, l~c'cause -if the ive'lcN limitations, it xat. ne'ce',sarv it, deVCiopnew tramsiormeriess tvpe 4i suhcrarrier cgencrator The hi-neralors were drsigcird to operatein the standlard suicarrier channels (it 9f() Aicci 4.30) CV cc' median frequiency. Their were .,Ithe FMt tvpe. Deit deviatel tx-%ien # 5ia-reent limits by the ,ff-con tvpe siecnrias 1mm theemitier-follower outpots (it the 11CAlers.

The subearrzer ge'ne-afors %"re of new design with a low Power requiremeint. using temper.ature- stabilized RC trr'quencv conta ot circuits, And wcere stabtced btween - 10 C and * 60Cj*iThe eegree cif :,o.eation with a gi~en signal, se'rsus temperature. was not linearited. This wasnet thought to tie necessarv. tca.ie ot the nature of the modulation, so tong as tlip frequencydid not drit outside ot the channel Itmits. Therefore. ad me divergence of the excursion limits.with an increase in temperature, was ignor< 1

Se'. oral types ot alternate dtesign were tried, buit all rod sertous adverse effects. Since,.%ce'it limitatioins did Pcit perit .,r ! rocn-corr indicciancea, ci normal dimensions, an attempt\&as made to u..e LDct ,.ouicnce transformers As inductances, as well as other 11hesintature de- i f!

CONFIDENTIAL

/4

Theae methods all proved uiaal'a~actory. as they were highly sensitive to, changs it bothsupply voltage and temperature. Proper dcvlation of their frequency was difficult: the outputwave form was very poor, changing radicai with deviation of the frequency and with slightchinge in supply voltage.

Modulation System. Since no Iron-core devices couldl be used. a modul.ating circuit for theRY transmitter was diesigned using a Type WN transistor, operating in a comma.' collectorconfiguration. This modulator varied the voltagte aplied to the RF oscllator in accordanceL

K Regulator

PMTube -4 P14j0 Scolers

Collimator

Absrer Fll F II, o

Figur 24 Schematic of the scuillator counter.

with the modulatlon signal. This circuit had unit voltage pain, there"y applying an Identicalsignal, to CI* oscillator circuit as that o1 the combined moduLation signal. It had a still biscircuit to prevent distortion of the modulation signal with temperature risies. with a secondarypurpose of bypasoig part of the necessary oscillator curreni around ith modulating trAtisiato0r.

A modulation pre-amp mixer stage was used to enable proper adjustment of niodulation levelsuAd proper combining of the two subcarrier signas into a single, complex modulation siginal.

Antenna Systiem. A unique system was designed for this application. havingt s:oo impedance-maf"h.riv characteristics andi radiation elfficiency at all times.

In the primary frndw oi -sw,1'ion. tv means of ihe turnstile configuration, f.r"l to the firstelemenia was accomplished by equal of 01 .nature ifl.nhm coaxtial . .. 111rlii..These elements we're npaced oppopite calth other on the payload. fed by Ii.iiduai coupling roikq.180 electrical degrees apart. The '.cond recnients, also opposite each other. bti 90 dlegrpe%from the first. Lcr- fed frcm the first elements We rness of quarter- wave- r" %in% section-,I'ach Plement was fed 90 degtrees from its rreso,',itvr firs.t elem".. This restulted in a qvAdra-

I ,c '"U~kuration. with each element locaied physiczlit 90 degrees from any adjacent one andexcited 90 degrees lrcm any ad~acent one. Field-hirenvth measuremntrs showed lt pattern tobe itarly a sphere of radiated stignal, with the antenna actually radiating.

Radiation in the secondary mode of operation was by means of the modifie dipole. IoAIedIn the nose cone of the misialp. This mode w31s fur purposes of tracking during the timr thatthe missile was borne by the launching r'aiue and duringt firing of the first and second rocketphases (it propulsion. Upon firing tif the third rocket phase, mode changeoa to the primary one.

Since no pro:.terancirs could he tolerated, the dipole antenna for iterim radiation was nec-saariv installed within the fiberglass nlote cone (Figures ia6 and 27). It was necersmary to *~

tend the elements along the length of the nose cone, the required length of the elements beingaipproimately 26 inches. This fact prepented a problem in avoiding Cancellation of signal dueto 'he nearly parallel llacement of the elemeri~s. This problem was solved by extending the etc.

36

CONFIDENTIAL

_6- rR I 017FI. R

it

IL

~JJ 3 ~ 5 ~LT

~~17

CONFIENTIA

£ t

Monte only a short distance from tse points of okneJ feed is a parallel mawker. Zach elementW#A6 them spiraled at a 43-de~re angle with respect to the longitudial aiead the nome cone.This Can be vi"Inlad bv tmatniai ame to loolift through the isoe cone. At soim particularpoint. where the .l~mets are spiraled, they wouild appear to be at rigid antes with each other.

This modif led dipole was fed 160 eietrical degmee apart at the position uW the first eleomenaof the turnstile, throug codled and shoried turnstile elements. The second set td elements ofith turnstile were also cotded and shored ou.

Good lampedwne match to the transmitter was obtaised durring both modes od operatio. withvacellent loading. Actual (iold strength pattern mesureuents were not made of the interimmade of operatic., however.

Unique design was employed tn providng the requieltea for both modes of operation. I wasnocesary to provide: (1) turnstiie configuration for the primary mode of operaticos. (3) dipoleconltguratios during Interim operation,. (3) retaining cups Iii the payload itts for carrying theturnstile eiements duritng dipole operation, with conunectton awhore at the center poin ad thepayload sidewall, in each case: (4) ardesma cup covers. upon which the coiled turnstile elemsentsare supported until such time as they are required to be extended for use-. (5) a roean of short-Ing out each turnstile element, during dipole operation, to prevent tnteraction wtth the trans-tattler. due to Indtancwe changes resulting from vibration and &hock; 16) a means of feedig IPto the modified dipole antennas during interim operation, from the dlisabled turnstile elements.and (7) a sure means of forcing payout ol thve turnstile elements. at such tCme an they are re-quired, In such a mannr that they would not tangle during their eatendiing.

Antenna cups, approsimateiy '/,.Inch deep and I Inch In diameter were secured Into holes itothe sidewali of the payload, with connecting anhors located at the center point of the can aide-wall and bottom of each cup. These were for connection o4 each foed line Internally and eachturnstile element eaternaily (see Figure 18).

Covers for each cup were used, upon which were supported ihe coiled turnstile tielee.Through each cover was a stranded wire. for external connection in the dtpole viemevic at tw,;positions. and two jerk wires at the other positions. We tenly, the strande wir ws L.-Ai.dLMd trimmed to three strands, two strands being connectotl directly to the balled uuter end adeach turnstile element, This was to pull the end of the wire outard at awch time an the coverwas pulledt awy. At time of saeb.the single ostisid was connected~togtither with the turn.stilt element, into th. connecting Anchor. This yoke provided the means of forcing paer" 4the turnstile element as ihe cover was ripped away at separction ofl thve payload from the missile.ft also priovied the necessary shorting of the coiled turneile element dasring dipole operation,

The sequence 04 doing thies S follows;M Kach cover was overild wi the inner surface witha *Iacky won".* upon which was spiraled the turnstile element, starting at the outer edom andcoilinog toward the center. The turnstile elements were of grld-pisied. annealed, brsaded copperwire. AMtyr spiraling of the C *.n '4. a sort of retainingt basket was tssluonevj by use of a singtl%strand af wire around the eovet , rossini the spiraled eteenert in ech direction. The wax wasnext dissolved out by inears of a sderresoer, and the connection yoke installed in,, Yilture it).

U~pon assembly of the payioad In the mnisall-, the previously prepared antennis element wasInsalletl It, es, h cup. first placing a small plug W4 fiberglass wool within the cup. This was tobear against the coiled antenna element to hold live spiral in place, sfier removal (if thve fineirand basket. The byasket was refmved at the time of asavsembly. The cover was then hed .n

11W;-. by a piece of tape only untit the payload was secure in the noset cone CA the Missile..%ftre patia Insertion of the pay oad into the nose cone. ctw'nciion was msade to the elements 4

)I the moxdfed dipole and the ivn) jerk wires At each W se ar onts, the no"e cone had beenprepared with a larger piece of tiivvqlass minij. which foliled double as the payload was Ineerled.This provided considerable pressuti saanst each cup cover to txold it in piace until separationfrom the missile.

Therefore, as the payload moved out of the ... zz rone, the Interim dipole elemeonts and theJerk wire$ would lift away the cover fronm each antenna cup. The double strand In each Tokewould start to pull the Ire,. end of each elenr out of the cup. Simultaneously, the single strad

384

CONFIDENTIAL

-Flo

(Folded Fiberglaill Pad(PNes., Cover In piece,

CvrNote Come ,.'.

(A~mww~ Cioop)

Figure 26 Croza-e.~cional vievo W nose cone andl payload.

NamCe"-etIs2~ Ra'-

Fixurt, 2' i i oli .... ... ibi Ai .1 ,md.

Feeq~ol Pluqr A 4

0,de, M5

FigJr( 28 Antena m renn asemhlv

CONFIDENTIAL

I F 7F W 1 _M- -.

at the yk would break at the conctime anchor. removing the short from the turnsitile element.Extending of each eleimnt would continue. whether or act t yoke broke away from the end (4

the element, due to centrifugal force (rotation Ias5 cps). The dual strand of the yoke would ripsay from the end of each emses. in Ay event, at the end of payout.

Wegt LMaitaticeii. h the entire payload. componwe were Cteem special attention regard-1z4 their ruggedie" and temperature stability, and the lightest type was selected where therewMaI a choice. &abuaee iose were 01 priateod-circult dsign to 5breduction of weight with-

I PV

VTV

4 * 4

V4~

Figure 29 Antena elemnents.

out sacrificing dependbbilMt 'wrever possible. The RFr transmitter was made on a chassis of ;.bra"~ shim stock. &Wrt, iately crimped and siffened to make an extremely light assembly.using air -core coils still *ned with epoxy resin.

The subcarrier generator boards wer* mounted on each side ti the RF transmitter, effectivelyshielding the uncoupled radiation of the transmitter. without extra shielding. This resulted in acomplete trantsmitter. subcarrier and modulator assembly weighiti only 43 grams$.

packaging. The completed payload was in the form of a doughnut, 7's 'ohee in diameter a&MI".2", inches high, with a 3- Incht center hujb. in~to which was insalled the rncket motor for the fineal;hsse of propulion.[*

Rigidity for the entire assembly was atforded by use of a foam potting compound. Tis wasused for prevention of adverse effects from vib~ration, shock, and accelerations. After insist..

CONFIDENTIAL

iVr

latlit of the coAxial transmission line aM antenna retaining cupo, M&gh jumper terminal boardand feed-though insulatorsa, the entire container was flive a preliminary poat. Ti was heat-cured for added strengMh The compound was tkm' channeled ot to permit lawtallatdas of the var-taus subassemblies and batteries, illustrated in Figure 30.

The suhassamblles and batteries were carefully placed in the clianl, so as to give good ap-proximton oS balance. Conntections wer* then ade to all compomeiss. All item were placed

Figure 30 Payload case and antennai.

with their gravity centers at the midpoint of the channel, an nearly as posibe, for "oA ytiamicbalance. Good balance was then accomplished by use of a ball-bearing gnimbatl mounted in the hub,bupported from the ceiling by a string. Compensations were then made and the fimal potting done.Bl~aance was then again trimmed by slight cutting away of poiting material or inserting small cop-per wire at the periphery of the package. when necessary.

Source of Power. A moat important consideration was the power source. From the start. itas borne in mind that the protect couli be successful only if aestgn was in such a manner thAt

the various subassemblies &Mi devices required low power consuimptions. Excessive power re -quirements precluded Ohe use of commercially available assemblies. Mercury baitries werechosen for their good characteristics under chanes 1.1 tenperAture. ability to eperate In vacuumInd for their .icceptable power- versusa-weight characteristics. Their dimvbsions and cool isura-tion also were good, -4 th-it packaging was less difficult.

Other Considerations. Printed-circuit flight jumper boards were installed In the skin of thepayload so that external power sources couild be used for all testing and adlusient. leaving theinzernal Dower sources for actual payioad use. This permiitti- actuation Mf the payload at thelast momenta beore taiwof .

ft was weessary that the payload prov-de titierv power for operation of a aqitb firing timerassembly and that squib leads be carried through the payload. This was accoasplIshed by usingcommon batteries for the high voltage inverler internallh and the timer inverter externally.Connections were made via feed-through insulators installed In the package s.

31

CONFIDENTIAL

LEE oil

'_ X,. ' A ~ '.-*

ft was necessary to provide a means of increasing RF radiation at an elevation sufficiently Z

high for fUWa check with the microlock station. just prior to takeoff of the launching plane. Thiswas aecomplished by shock exciting a dipole, elevated on a pole, by tapig a short section ofeach end of the transmission line directly over the interim dipole radiator.

It was found that It? radiation nsisr the scitilator or pliotomulttplies caused a change incount when a voltage was permitted to develop in that proximity. This was overcome by Wat-ing one of the secondary turnstile elements approximately midpoknt of the complete scintillationassembly. With the current node and voltage null located in this manner, no adverie effect wascausin.

Another important Consideration was the returning of all bsttery sources to a common pointat the RF transmitter. By permitting no sources of common coupling, spurious effects werenot produced.

At the time of a o' embly, a piece of cotton was purposely contaminated with a radioactive iso-Ptope (pA; half life 14.3 days) and placed In the collimator of the scintillation counter for the pur-pose of providing a standiardizing background :ount. Conitinued correct operation of the Payloadwas determined in this manner. Tis method also served to calibrate and adjust the pulse-heightdiscriminator to the correct energy level of 1.5 Mfew.

Tracking. That this system operated efficiently was attested by the fact Ih4t the NOTS micrri-lock station was able to track the missile on the aircraft from iakeoff until missile launch, atwich time function was terminated due to missile failure. This was at a distance of approxt.mately 150 miles with the missile going approximately 5 degrees below tine of sight, due tointervening mountain ranges.

PROGRAMMD* SYSTEM

One of the most-critical components in the system is believed to have been the horizon trinier.ft "a a telescope with a narrow field of view, and had an Infrared sensitive cell at its focus, Its

c~xical axis was at a 12-degre angie with the vehicle axis. Figuare 31 shows the horizon scannerIbeing installed in the vehicle. When the spinning vehicle, with its apcnt first- and second-stagemotors, achieved an aittitucle of 31 degrees with respect to the, local horizontal, IER radiation from 1the Par h's surface was detected by the Dl cell. The cell generated a pulse, which was amplifiedby transistor circuitry until it saturated the output transistor. The saturated output pulse wasintegrated such that the secondl-stage motor was to be fired when the earth's horizon had beenscanned for at least four times. The purpose oi the horizon trigger was to determine the all-Important v-hicle attitude at perigee so that tW second- and third-stage velocity vectars wouldbe addeJ in the enr'ect direction. The horizon trir~pr would offer a me~ns of nullifying errorsIn nitt %I trajectory resultitlg from first-stage mass asymmetries. thrust mallignment. a'Iideviaitio. ~r t-rcralt azimuth an vehicle release angtle.

Before the tint-stage booster was fired, a sWe %wparation distance of about 500 feet beWeenaircraft and vehicle was assured with a S-secondl delay timer. As previously exlained, theweond-siage booster was fired at the end of a coast period by action of the horizoi trigger.

The firing system providied an enabling timrr to prevent premature operation of the horizontrigger from the sun or other' wi-Jrces of 1R onergy. Fourth- And fifthstage boosters atid theexiosive charge to separate thtse stagtes ser,' to be firedi by acdditivsnal eie-tronic timers.

IIORIZON-SCAN'NER TESTS

Four horizon-scanner ground launchingst wt-re made from the X. ii launcher to determine theperformance of this c-omponent Test conditions called for launichirg the scanner on an HPAGrocket motor at an angle of 55 degrees above the .torizon. This AikA diowed the sUanner togo above the horizon And come to a varallel ijsition relative to the 1round at which time It was'Auppot-ed to fire a spotting charge Indicating proper iunct~onlng of iii' samtner.

Figure 32 shows the scanner test vehicle on the grcund launcher prior to firing. The teatre!Aults from theti firings and two aircraft firings were not conclusive. In these tests, the

32

CONFIDENTIAL

.-- ".~ - --4.. ..- ,-.

: ": ... . . .'- . .". 1;

7,7,-

. , :IFF-r- FT .

* -.

ItI

-. .. :2 . ,4-.-l - ,

• * _ --- ~.-- -,

33

CONFIDE[NTIAL

prema~ture trt~erin of thozo lse hot o~q i sn glints inicated the need for an enebil~ntimer to gat the period of operation.

GROUND RICRIVM4 STATION3

Work on reeivin stations was initiated with the Implorer satelite program. A microlockstation was builit at NMOT and operated in Connection With A atiab.r of the early satellite Pro- ij;iframa. The uniqueP featur, of the NOTS Stations is their Improved capability for rapid frequency&can. For Opieration Argue. four aulditlonel portabl, stations were operated to record doppler

0

Vill ~~.6 77

-t row-

'~, ZiAiV

*424 .41.5~0=-

~ ~?Y . ~ ,

Fi~ir 33Mcookgon-eevriainand~ ~ ~ ~ tereeigdt rmEpoe .Fgr 3 hw yia irl rudrcie

stto.Unt ihthi euatdpwr upywrearIeghe y MT1oNw rliiAl~tts.Grenlad. he Ators, nd awai, werethe wee oeratd b NOS prsonel

Figur J4 isampsoigwrdwd oettadlctoso rudrc~t ttos

Flu~ 3 sos pckgd alto riii nNwZaad.adFgrs3 n 7so h

Tlgir 33 icrolock svtmi eige orcvr ton revpes Ifr ~atin. s*iple frqec

and teipmettering. dat rmechiue, called 3 ow a t ypicg ite ada lier eol grud eiotnation. Unts ith teir euae pwrsplywr i.Ivg.eIb AStvNwZaad

The asi G breeld the res, aind Hwa ii. al wher the were opredio b NOeTin hers nIeresec 4 0 aa ti s oig wolhwie m easre andho welo theo ble is brou n soleve sa ed.

F u~ 3 sow apckge satonariint n ewZelnd ad igre 6 nd3?s3w4h

sittn its n lsk ad ew COlNd.FIDE rNI30Asscxicr Vwr eet

Van lle at11wL'iiverityof owa Ttae ialins aveconistntl piced p al0.wIsgna

Figure 34 Locations al mcrolock growul-rec.ver "10M

J..

t~~~~ I. OMR@ W W 169 ..

A~

714e. 36 Mkcroloek site la 4iasc.

Z;*

~~ItM.

A l Z .-

6 ife

Fg re irookstinNwZand

the sigm.l-to-ote ratio (SIN), where 8 is the stigal power a.id N Is the solott power, the niag-nitudeod wicht is directly proportional to the required audio bandidtil. The too ad the track-tag filter as &bows in Figure 38 illustrates the principle. The carrier frequescy of a saleUtto,as sea at the receiing station. experiences a sitift due to dopplor ot approsisshtely 8 kc (as

F hmede am" ftsits,aui amCr- 5how ft.4.q Spefm Am" S~i

POOOMe OWe~sm

Fiur 3LDplr r~e shtLt versus time.

deemne yreceiving station location. obtlprmesadtransmitter trequencyl. With

S ___ S

S14oLW S0N 14IS+N

aP~It RAUo Output Ratio

S2SZS S 4 I

2

Figure 39 Equations for linear and square-law detection.

reducticni in noise potter with an equivalent increau4 in S N ratio. The increase to obviouslyproportional to the reduiction in hiandwiuti. or 8,000 to 10.

rints detection also works ttc prtserve a high sign~a-to-noise ratio. With this methodi. afterhaving once acquired a trtasmitted signal (by manual search across the expected frequency re *

37

T It !1I:!

'.4tLIL 4 SLWKhNV Or74WIT11I 1111441 Rl~tf.

elisos 4W 04. 0M L"b top low. WVT*%4 iol . b)- fu.ft .9-I4 wilolo R' towPA I *4 14 44 1. . .. .. " 4 1. 4 4 0 ?4 W 4 _ . *4 - 44 co l . @, -a I s4d 4 44 4f

0

PShM4 1 . .444 W 6.4..44. too 30 mo4441m Coir, 44MPU 4o.-0 Wisol. 4- . 1- r. 44

d.4* "I# Ow". 4 14"Of b-dr

pv,,h~~~~~~~~s-4~ boss. to J.,114 _b " Wis1 _ pcmso.4.1 - 1 4

L4.1.. "Is -%14--1..0~ 66 4 o 4P4. M-44

0,444.4 ~ ~ ~ ~ ~ ~ ~ ~ ~ ,ommlo "assis 1. .01 J.4,- W54 C~.4 o4* ~ 444.1 0 440 7444w441

ft., I. or., IsI .

fl*4.0I4 s-M 4.%d

P..4.9 wM P.4 I 4 I. A4 914 C. . 4 044 ..0 ~ 1..h--t4 1- s 6 04*1 - .4 ~

*1., - ,W 1"r4 144 440 466444 W_ 44 &W b ."- I. -il ..- .I. I..".444 4

W-. W-1-SUVI h Mul. 'A4,4 w...4,. .,. do . 4 p..014 ... .. t1 & *.- .-

T4 Is.,IV 44.1. dw - Mr-1

014 It, 110 .. a .I041 0" U .lot 10 W= -1111 11 .- as4 o: -I ' J. 1,1

T01. _.444.444W. - -'f4 woo14

4.144 4 .. -A. * 444

444. Iw 4 1141tl

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.0,4,

gion), a lcal circuit generates a good app-OXIm...tin Wf the tocoming itr.1i and the "methematic.of the deti'-tion process. as inicated in F~igure 39s, demonstrates that the siWWa-to-rois.' ratiois prey -:-ved. T.,.s can be contrasted to F..jre 391t, were the detection process reduces thesignail-to-noise ratio, especially at I )w signal It. .els.

At the completton of Operation Argua, the ground receiver statilons sere returned to NOTSand work, has continued on increasing their portability and readiness. Duaring one of the Atlisirings, a receiver station wab put into operation within less than 4 hours after aircraft delivery

of the station to the st'ected sites.gITo support the receiver station network, HOTS1 used Its IM computing center to 4Jtermute

ephemerides for Explorer IV from tIe doppler data taken from the five receiving stations. et

OR~BITAL ATTEMPTS

Three orbits! attempts employing vehicles with diagnostic pAylmads were made osi 25 July,12 August, and 22 August. Oni 25, 26, and 28 August 1958, three additiona attempts were madewith the scintillation counter payload aboard. Alt firings except the 22 August event mauw-tioned during the first stage as the result of propulsion diff icult ies or altitude tgnition problems.Oni the 22 August launching. crystal control of the payload itanamitter frequency wait lost justprior te Launch. Three possible pasbca were reroeded but a complete review of the data coui'inot justify an orhital clim.

Table 4 summarizes the major test results in the program and recapitulates the analysis ofresults obtained in the s orbital attempts.

CONCLUSIONS

The difficult task of develo, . g a com~plete aircraft -launched satellite-vehicle system andmanufacturing and launching% ides %ith pAyloads for fC ratlin Argub was accomplishedwithin the short span of 8 months. This included! the development of three new rocket motors.high-altitudet Igniters. an inlfrared -sent ing horizon tripper, and special electronic timers. Thetotal structural wPIgit of this vehicle was limited to 5 percent of the overall total vehic*.%. weight.

The technique of safely launching satellite' veh'icles from aircraft at high alitudes in a tllmaneuve-r was successiully d. %tonstrated. Acceptable and reprodtucible initt" aircraft launchconditions were obtained by tt.i' sever.l pilots whii acre trained.

A world-wide network ot highly successful polrt; life microlock ground-receiver stations %isbuilt. dkipioyed. anid uaed to obtain valuable IGY 3nd Emqlorer IV data. Some 310 telemetpringrecords obtained by these stationi while monitoring lFsplort-r IV for a period of approximatelyY)l days were forwarded to the akate University of Iojw4. It has Ivenrepored that these datawere among tn., 'nst useful obtained on Exploirer IV

The NOTS-develop--i mations have An improved capability for rapid frequency scan and canite in operation in 3 to 4 hours froin the time they are recttird at any given location.

An 1BM program for computing satellite vehicle tierformance. musaile tolerances, andephemneridevi for satellites irom doppler d.2.i has been developed and Applied to Ithe data re-vvived from Explor!,r IV. A six-dogrces-44-freedlom progr.-n study has also hee, completedfor determination i4 orbital trajectories concurrenty with stability studies.

It is belevrtd that the- experience pained in this program greatly enhanced the NAtion's capti-bilities in space rerearch andi development arid that mane' -%I the components developied will fandA recurring applicatiomn in this courfreirvs vpace program.

This program provia ihe feabiility and eer-.aiiiiv (if aircraft -launched satellite vehicles.it as believed that with the experien. 4 gained in this prigram. a ligtkaeighi, Inexpensive.

bighly reliable matelliti' %rhicir % tofrnAnce quality could i1e designed and niarAifacturfd On ashort timne scale

39-40

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117,171 vui'A

77~~- ~ -

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