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A€-Rf.O ..,Au-Rt. E; Тtwts.On LTV a€-rF.o ..,Au-rt. e; òtwts.oN P O. BOX øZøt, oÅtLAs,22' TEXAs &v ^ TABLE OF COIYTEI\TTS Page INTRODUCTION... 1- 1 MANAGEMENT,... T- 2 MISSIONS 1- 3 THE SCOUT VEHICLE 2- L THE SCOUT SYSTEMS 3_ 1 THE SCOUT PAYLOAD 4- I LAUNCH SITES AND GROUND SUPPORT EQUIPMENT. 5. 1 THE.SCOUT PERFORMANCE. 6- 1 ADVANCED SCoUT PERFoRMANCE 7- L lÊ Notn, This section identified by orange stripe on edge of pages. II\TTRODIICTIOI\T E :'lii:ilì -jr'ìr,l LTV Astronautics has been participating in 'it I production and launching of ü:l the development, the Scout solid propellant vehicle for over , t:i four years. During this time, Scout vehicles have been utilized in probe, re-entry and ì ,ti orbital missions including the launching of Explorer IX, the first satellite put in orbit Er¡Ë by a solid propellant booster vehicle. .J h, This is the second revision of a report which :il was prepared to familiarize users and po- -:x performance r.1., tential users of the Scout and its þ-:l capabilities, It hâs been "up-dated" to reflect :l the improved performance ofthe Scoutvehicle of a new fourth stage motor' il through the use -T the ABL X-258. This report is intended tobe t used for planning purposes only' Complete detailed information relating to the inte- \rìl gration of a specific payload with the Scout .:l vehicle is available upon request. Information in this report is current as of rl 1. DECEMBER 1963 i-l Ll lt. .,.'l i¡l:l 'rJ¿ F:;:'.1 l.;r i !,U iÊ- ¡ ;í, j "-!¡ ;:!'r'rl iJ -ü ï-. ¡ ''i"U "t F::, _J MANAGEMENTT q h TheLTVAstronauticsDivisionistheprimevehiclecontractor Fr to NASA for the Scout launch vehicle. In this capacity, LTV Astronautics is responsible for the fabrication of aII interstage structure, including guidance and control systems, instrumen' L tation, heat shield and payload separation devices' Aerospaee' g.orrrrâ équipment, including electronic checkout gear as- w511. a1 F; fabricated sìi itre -ecnãnrcal handling gear and launchers, has been underthisprimevehiclecontractforbothinplantuseandlarrn^cþ site operations. LTV Astronautics is responsibte to NASA,fo! e_ as""*tly, checkout and countdown at the WaIIops Island Station" Included in the services that are provided are payload integration to insure compatibility between the payload and the launch vehicle, EI In general, -q flight planning and vehicle data reduction and analysis' ,.{ ¡' '! Scðut vehicles for the Department of Defense are procured by Command ffir the Space Systems Division of the Air Force Systems Sra. tnrouþtr NRSa. By this method, NASA maintains centralized fr technical direction of configuration, procedures, and checkout which results in over-all efficiency in vehicle production, sche- dules, payload coordination and operation. LTV Astronautics welcomes inquiries on the technical aspects of the Scout vehicle and would be pleased to discuss the potential of Scout launch vèhicles in providing an economical booster for many payload requirements. Inquiries should be directed tol Mr. Fred lM. Randall, Jr. Director - Launch Vehicles Of -ìiiiÊ:i.;È Mr. Milton-E--- Green Program Manager - Scout LTV ASTRONAUTICS DIVISION P. O. Box 626? Dallas 22, Texas t-2 g MISSIOI\TS The purpose cf Scout vehicles is to boost payloads for orbital, probe and re-entry missions at a lower vehicle cost than is possible by any other means. This goal has been met through the use of proven and tested concepts, components, and procedures. Design simplicity keyed around the solid propellant motors and a modular concept result in short, simple count- downs and lends flexibility to launch operations. Complete suþporting systems ernbodying the same principles are avail- able with the vehicles. Launch sites at Wallops Island and the Pacific Missile Range are now available. I: !x tt;J :l ç TrrE scorrT vEr{rcLE I ,Å The basic Scoutspace researchvehicle is afour- stage guided booster utilizing solid propellant ; :;rl;r,i: rocket motors capable of boosting payloads of ;'rli[ vaxying sizes in orbital, probe and re-entry :1..l missions, The inboard profile, weight break- 4 down, systems, payload capabilities, and per- t formance are detailed on the following pages. PAYLOAD * ß -34.0" t.lrljll SEPARATION SY ST EM ìr,, HEAT SHIELD ALTAIR :ì1¡, SPIN UP MOTORS .n MOTOR -)/ \\\\\\\\\\\\\\\\\\\ SP IN B EARING I \ \ \\\\\\\\\. GU IDAN C E _il 30" i ANTARES jn MOTOR TRANSITION SECTION "D" '\\\\\\\\\\\\\\ \ '.'... \ \ \ \ .¡ \\ \ \ \ \ HzOz --t \ \\\ \ \ ATTITUDE CONÍROL ,t 3t" I SEPARATION CASTOR DIAPHRAGM i:.' MOTO R !Á APPROX. _ï 72. Fr. .: TRANSITION SECTION "C'' \d tl{l \\\\\\\\\\\:r\ \ \ \ \ \ \ \ \\\\\\\\\\ Hzo. î ATTITUDE CONTROL :- i -1 SEPARATION ,.t UJ 40" DIAPHRAGM rl:.- . ALGOL TRANSITION SECTION "B'' MOTOR t,t ,i,!J ill J HY DRAUL IC CONTROLS J ET VAN ES \\ \ \\ \\\ \ \\ -\\1\1\r\s-1\\Ì i_'',_, FINS "-i ,tlúJ TIP CONTROLS BASE SECTION "A" r:,Ìì 2-l .t -.¡ wErGr{T TA'BLE çt TY PI CAL STAGE WEIGHT Payload Fourth Stage - Inert ____19.1J_ Fourth Stage Burnout 79.71 Fourth Stage - Consumed 509.20 Fourth Stage Ignition 588.91 Third Stage - Inert (Includes Spin Motor Grain) 751.7L Third Stage Burnout 1346.62 Third Stage - Consumed 2590.00 Third Stage lgnition 3936.62 Second Stage - Inert (Includes Nose Cone 34" - 25") 22L6.80 Second Stage Burnout -TlffiAz Second Stage - Consumed 7528.00 Second Stage Ignition f36Sr-4--t First Stage - Inert 3234.90 First Stage Burnout 16916.38 '. First Stage - Consumed 2145ri.O0 First Stage Ignition ----g¿sr¡,;Bs-l i:).iiijlriilr,ti:ii,l;ì ì; :: !''.1 i::iì::il,r:tilltiilriì :.:. r .::;ì 'Eí TIIE BASIC SCOI'T \¡ErIICLE Ffi 'ì, : i ''.i,1 !,' .1 " !i{ FLi t '|' '** --*' "::sj¡:1ìiH::TL::ì ! i ¡1 I ,!l -'l --1 rrsñ'irùMl i.* ,"i'ìi,1i*',ìtj *r****, ;å,ì .'-¡¡.-\" !./ "1'-i:¡' fiTCIII'fi.¿l': , - .','' .L^nocs crsvs SII,L è :. '..: l''r'l'i ,.,:,11''.ìl¡,1-.ri, . ,t ',ri : ,.rr;jll l ltt: .ìr. ' , . .. ...... r ,:ìr ri . Ì -r.,; ¡:r'r,.,/ll|, I 'I :, ì : irr1. ri;rIr ;,,1.::,-ì, ¡,,.1,_ .. ì ì . i ir,..r.r "ì,ìììitrr ¡.,ì.i. -;i|.::. ì.. l. r tr'..f'. ,:,ll ltr . , I l q TI{E SCOIIT MOTORS A'I\TD SYSTEMS a MoroRS. Motor data are presented for each of the scout motors including nominal dimensional and performance characte ristics. a GUIÐANCE AND CONTROL. The systems are designed to have â capability guidance in and control for performing orbitaì, probe and r e - entry missions. STAGE SEPARATION. Stage separation is positive, clean, and offers no major disturbances. a PowER AND IGNITION. Dualized ignition systems are employed to achieve high retiability. o DESTRUCT SYSTEM. command and automatic destruct capabilities provide positive thrust termination of vehÍcle motors. a INSTRUMENTATION. Performance of vehicle subsystems can be monitored during pre-launch, checkout, countdown and flight, MOTOR D.A.TA. The summary chart below lists the solid propellant rocket motors utilized in the Scout Launch Vehicle. sfAGÊ MAKERS MAKERS uNtl NAME NAME NO. NO, NO. 1 AÌgol II A Aerojet Gen. 2 Castor I XM-75 Thiokol XM-3385 27KS- 55,000 3 Ant¿res Allegany _A.B L-X259 - 38DS- i9,000 IIA BatÌ. Lab. .43 4 A-ltair XM-69 .4.1ì egany x-258-Bt Ball- t-ah- 3-1 f i. MOTOR DA'TA çt I The ALGOL II-A Scout first stage propulsion unit is being produced by the ) Aerojet General Corporation, Sacramento, California. : iI -f l 33.66 f'- __t i, l. L; ATGOL IIA ', I t, Iiill 't" ft*E Total Impulse - Lb. - ìif Vacuum 5,469,094 tr Éi Specific Impulse - Lb. Sec./Lb. Vacuum 258.29 Burning Time. - Total Sec, 68.2 T .j Thrust - Avg. - Web - Lbs. - S.L. L04,5L7 I L Weight-Total-Lbs. 23,6L0 Weight-FueI-Lbs. rl 2L,174 n. MassRatio-w,/w. Ë',.i p't ilt Nozzle Ëi: Expansion Ratio 7.32 üt! Weight Consumed - Lbs. 2I,457 ff- W ':ìi È- ,l å11:r: Ër5 tÈ EftI,- $ir! % 3-2 'ir¡ ø-..iil g¡..$:'¿l 4; Ll tliJ ALGOL IIA l PERFORMANCE - VACUUM å1 Ì *i JT .i i{ i 'll J^ ;, 24 L- T ,lð T o , ,.ji- I x x20 ,, l0 I o z, zc¡ Þ if f o o- l,- Rro t8 L_ I 3 () ul t lrl , i = Jo ¡.-.1 =12¿ l, tu llJ É, I ,J. Jo Íi, rA it l +å e. f, ]L - I l- ìiÍ!-¿ Tn l$t'dfl. 60 64 68 Ir¡- 16 20 24 28 32 36 40 41 48 52 56 i1 TIME-SECONDS t f4- lt1L ,fl . ii' ,.1 " J-, ï I l J tr fiia¡ MOTOR DA'TA. çt ft'! I l" I The CASTOR rocket motor, present secoud stage Scout propulsion unit, is manufactured by Thiokot chemical corporation, Redstone Division, Huntsville, 't_[, AIabama. $.. L_ f. Ê-t ñ ,fi- ü't :: cAsïoR r m €.-P;;ri Castor I-E5 tr i"d-_.; : Total Impulse - Lb. - Sec. '+¡ç Vacuum 2,oo2,o7r Specific Impulse - Lb. - Sec. / Lb. Í- ß Vacuum 2'73.2 E"q llÌL Burning Time - Total - Sec. 42.49 d. Thrust - Avg. - Web - Lbs. -Vac. 62,175 L ri$ Weight - Total - Lbs. 8,869 $r: Weight-Fuel-Lbs. 7,328 ho't il.:.Ìl.rl MassRatio-W,/W pt .826 F.:\ r i firiì;; Nozzle Expansion Ratio 15.8 ,rr,rl Weight Consumed - Lbs. 7,434 ffi.'.E ,i.4 &ii.ìlrçti 1 3-4 Fii -þ]ß,1 l t.:." r . kF-¡ä Ì"i-s _lrdJ i.. {l ü CASTOR I PERFORMANCE - VACUUM jJ lt,. :q .:s rÉ :îfr' 3 "E ']Ð ï$ d $ I ¡ r{ r< X t, X5 (A v) o -"î t-.1 z it z Þ ¡': o t{ A I rlil ,4 -$ '¡.''¡:' z z ïn O >3 \ E{ 4 d (n .: r'l"l H< .cl Ð Ftz F u "J ii,j t-:i r't ,t i:l i ."lc t2 16 20 24 28 32 36 40 i-, "1 TIME - SECONDS .ï 3-5 -i x MOTOR DA'TA g The ANTARES rocket motor (X259), was designed especialiy for the NASA Scout third stage by Allegany Ballistics Laboratory (ABL), a U.Sr.Navry BuOrd facility operated by Hercules Powder Company, Cumberland, Mary-Iandr, The ANTARES X259 is an improved version of the X254.
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