8 Approved For Release ZOD1IOQID1 SECRET cow JOINT PHOTOGRAPHIC INTELLIGENCE REPORT SOVIET GUIDED MISSILES 7 NOVEMBER I957 MOSCOW PARADE HTAUWIJIAT FILE THJSISAIECGRD can THIS REPORT nor 1 0 CEO BE 1958 Will 3 03-33 23 THE I mureuscmm HEEN n moren 3 I i - Coordinurad Published and Disseminated by CENTRAL INTELLIGENCE AGENCY PHOTOGRAPHIC INTELLIGENCE CENTER Declass Review by DOD Approved For Release 2001IOBI01 RE vm-W Approved For Release 2001100101 This material contains Information a 'ecting the National Defense of the United States within the meaning of the espionage laws Title 18 USC Sec-s 5193 and 1'94 the trans- mission or revelation of which in any manner to an unauthorized person is pruhibiied by law Approved For Release CIA-RDP78T04751ADOOTOOMUDM-T 25X1A Approved For Release 2001IDSIO1 Approved For Release 2001 09101 SECRET Approved For Release 2001IDBID1 SOVIET GUIDED MISSILES 7 November 1957' Moscow Parade 1 58 Oatober 1958 Approved For Release 2001IDSIO1 SECRET SECRET Approved For Release 2001109101 TABLE OF CONTENTS I II Boo-ted Surface-to-Air Missile SA-IEBulliatic Rocket IV Ballistic Missile V 35 N M Ballistic Rocket VLBI isticMiee eSS-S 3 Approved For Release 2001IDQI01 SECRET 14 16 25X1D SECRET Approved For Release 2001IOSIO1 I INFRODUCTION 'd This is a joint photographic intelligence report prepared by the Army 1 Navy and CIA under Army Chairmanship It is intended to Fulfill intel ligence community requirements on missiles appearing in the 7 Novemberr 1957 parade in Moscow It utilizes a series ofSphotographs and 11 drawings in presenting dimensional and configurational analyses of the 5 missiles displayed in the parade Estimated range capabilities are relative to the strength of present United States missile ro ellants X6 Other available information on United States 25 missile systems has been utilized in the configurational analysis The quality of the photography ranges From good to poor and the detail of the analyses varies accordingly Mensaral data for each missile presented on the drawings may have the following ranges of error Missile Range of Error Boosted Surface-to-Air Missile 15 N M Ballistic Rocket Ballistic Missile 55-1 35 N M Ballistic Rocket Ballistic Missile 55-3 25x18 II BOOSTED MISSILE SA-18 A General The missile is a boosted vehicle with a probable solid propellant booster engine and a probable liquid propellant sustainer motor The over all length of 37 4 feet places it a roximatel midwa between Feet B Configurational Analysis Analysis of the photOgraphy indicates a missile similar in operation to the Themissile consists of two major systems the pr0pu lsion system and the guidance and control system 25MB - 5 Approved For Release 2001l09f01 SECRET SECRET Approved For Release 2001 09 01 1 Propulsion System The propulsion system of the missile body appears to utilize a solid propellant booster rocket engine and a liquid propellant missile rocket sustainer motor The external configuration of the boosrer is very simple com parable in appearance to the -booster configuration The absence of any propellant loading ports indicates the booster is a probable solid propellant rocket engine The missile utilizes a probable liquid propellant rocket sustainer motor which is located aft of the four steering fins Four are positioned on the thrust joint Just aft of the steering fins is the prob- able actuator and actuator arm assembly which joins with the boomer Upon booster burn out the aerodynamic drag on the booster causes booster separation pulling the actuator arm initiating action by the aetuator thereby firing the missile sustainer motor There are two possible pro- pellant loading ports located on the missile fuselage between the Stabilizer fins The presence of these ports and the actuator assembly support the theory of the missile propulsion system being a liquid propellant rocket sustainer motor b Approved For Release 2001f09101 SECRET 25K1D SECRET Approved For Release 2001 09f01 -7- Approved For Release SECRET 25x10 25X1D Approved For Release 2001 09f3 F 2 Guidance and Control System The guidance and- control system of the missile consists oi a pitot tube Four probable antennae four stabilizer fins four steering tins and probably two booster fin ailerons l'he pitot tube projecting from the nose of the missile could provide the missile computer with stagnation pressure information he stagnation pressure includes both static altitude and dynamic velocity pressure This information could influence the order limiting strength of commands sent from the missile computer to the steering mechanism The four probable antennae are placed approximately at the same position on the Soviet missile as the four antennae on the and could function in a command guidance system similar to that utilized For the is a command guidance-type svstem The operational Soviet 13-200 guidance system The four stabilizer fins provide the lift which assists in attitude stabilization during the flight of the missile Aft of the stabilizer fins are the four steering fins These fins are probably connected to a missile guidance package by cables which could be placed in the probable cable channels These cable channels could be provided by the elongated blisters on the surface of the missile skin and they extend from the probable location of a guidance package to the steering Fin mechanism It is interesting to note that the Soviets have not employed the canard cenfiguration for control as is empIOYed by the The probable two booster fin ailerons could be used for roll stabilization or missile orientation C Conclusions Configurational analysis of the BooSted Surface to-Air Missile SA-113 indicates the Following characteristics 1 Boosted surface-to air guided missile 2 Probable solid propellant booster rocket engine 3 Probable liquid propellant missile sustainer motor 4 Probable command guidance system 5 Probable capabilities similar to the 3 - Approved For Release 2001f09l01 SECRET 25X1D 25x1 CRET Approve 2 20011031101 -7 LEFT SIDE VIEW PROBABLE AN TENNAE PROBABLE CABLE CHANNELS 1 STABI mmsma F1 LZER Fm aopv 53' i _ PosmaLE PROPELLANT 1_ LOAWNG PORTS - FIN I k- - PROBABLE ACTUATOR 7 umNT ACTUATOR ARM PROBABLE BOOSTER FIN AILERON 9 - Approved For Release 2001 091 114 SECRET Approved For Release 5 MM BALLISTIC sooner A General The Soviet Honest John Type ballisnc missile is a probable solid propellant boosted vehicle with an estimated range capability of 15 nautical miles B Configurational Analysis The boosted vehicle consists of the missile and its booster which have been arbitrarily r divided into four sections the warhead the probable solid propellant missile sustainer engine the probable solid propellant booster engine and the booster stabilizer fins 25x2 2 Probable Solid Propellant Missile Sustainer Engine The missile sustainer engine is located in the aft end of the second stage The uniformity of diameter and the simplicity of the missile skin construction indicates that the missile probably utilizes a solid propellant sustainer engine 3 'Probablc FS_o_lid Prepellant Booster Engine The booster fuselage has the same characteristics of construc- tion as the missile Fuselage and therefore it utilizes a probable solid propellant booster engine -10 Approved For Release 2001 09 01 SECRET Approved For Release 2001 119 111 Ga Jig-E a 37 a iv 390$ g 054a 4hr- 5 Dan 6 5 3T HE - M if 111 gig kw-H The - 0'33er Is 1-35 - Approved For Release SECRET Approved For Release zoouosm 1V BALLISTIC MISSILE 55-1 A general The missile is a non-boosted vehicle with an estimated range of 5-100 nautical miles Due to the poor quality of the phorography the desired detail in analysis could not be obtained 25x2 missile control surfaces could not be examined in detail but it is believed that control of the missile is probably accomplished by air vanes and jet vanes The guidance of the missile is possiblyr inertial for no antennae cauld be identified There are two cylindrical tanks carriedon the side of the prime mover which could be pre-metered propellant containers This indicates that the missile has a possible liquid propulsion system rather than a solid pro- pulsion system 12 Approved For Release 2001l09l01 SECRET SECRET Approved For Release 2001 09 01 MISSILE BODY 3306- I STABILIZER FIN WARHEAD 2T Elf 41 if POSSIBLE CABLE CHANNEL Ii i-rz 2 LEFT SIDE VIEW 25x2 -13 Approved For Release SECRET SECRET Approved For Release 2001 09101 V 35 N M BALLISTIC ROCKET A general The missile is a probable solid propellant vehicle with an estimated range capability of 35 nautical miles 241 IPJIEH Hill 4-H B Configurational Analysis The missile is similar in configuration to the Soviet 15 N M Ballistic Rocket but it is approximately twice as large in diameter seven feet longer and has agreater payload capability This warhead also has objects on its surface similar to those found on the 15 N M Ballistic Rocket The missile is partially encased by a ribbed metal casing that may incorporate a heating element to prevent cold-weather damage to the solid propellant of the engine The main exhaust exits through a cluster of seven apertures at the rear but additional canted nozzles are probably provided to impart slow spin for accuracy Because of the metal casing it could not be determined from the photography whether the missile is boosted or non boostecl The visible control surfaces consist of six apparently immovable stabilizer fins with no apparent ailerons C Conclusions Thefilhti N M Ballistic Rocket appears to be similar to the Honest John Type missile but probably has alarger warhead and a greater range capability 14 Approved For Release SECRET SECRET Approved For Release 2001 09 01 LEF 7 SIDE VIEW - I METAL anyms STABHJIER FIN - - - 4 5- f 1 i OBJECTS HEAR VIEW 15 - Approved For Release 2001 09101 SECRET 25KB SECREI Approved For Release 2001 09101 VI BALLISTIC MISSILE 38-3 A general The Type Soviet missile is a probable liquid propellant single-stage missile with an estimated range capability of 350 nautical miles x B Configurational Analysis 25x9 This the largest missile shown in the parade appears to be a final phase in the develo merit of the German Series and has a- A probable propellant loading port not shown on graphic is located near the forward end of the missile indicating the probable utilizatiOn of a liquid propulsion system The guidance system is undetermined from the present photography but it is thought to be a radio-inertial type guidance system The control surfaces of the missile consistoffour external vanes located on the missile stabilizer fins and four internal probable carbon vanes located within the exhaust channel The four internal vanes appear to be mechanically connected to the Four external vanes and they probably operate in con junction with each other to influence missile attitude during flight trajecmry - 16 Approved For Release 2001IOSJM SECRET SECRET Approved For Release 2001109 01 YAW FIN I EXTERNAL 35 VANE a I MISSILE FUSELAGE l5 PLUG EXHAUST CHANNEL 2 r52 U4 my Fm I STERN VIEW - - Approved For Release 20011091111 SECRET Approved For Release C Ericlusions The 35-3 missile hae the following characteristics 1 Probable liquid propellant susramcr meter 2 Possible radio-inertiai guidanm system 3 Internal an externai van-lea contrm system 1 a5 Approved For Release SECREI SECRET Approved For Release 2001mm POSSIBLE CHANNEL LEFT SIDE quw MISSILE BODY 610' STABILIZER 44 FIN H 3 oL - Approved For Release 2001 09 01 SECRET Approved For Release A000T0001 0001 Pf DATA 25x1 REFERENCE DATA AFM 200-14 Intelhgence Collection Guidance Manual C at GM School Notes Ft Bliss Texas C 52 31 Guided Missile Fundamentals U Summary of Signi cant Soviet Weapons and Equipment Project NR A4046 DA-ACSI 1 3 EU Approved For Release 2001f09l'01 REI 5 3 I Approved For Release ZOD gg q H- Approved For Release zuo1rosxo1 SECRET NATIONAL SECURITY ARCHIVE This document is from the holdings of The National Security Archive Suite 701 Gelman Library The George Washington University 2130 Street NW Washington DC 2003 Phone 202 994-7000 Fax 202 994-7005 nsarchiv@gwu edu This document is from the holdings of The National Security Archive Suite 701 Gelman Library The George Washington University 2130 H Street NW Washington D C 20037 Phone 202 994-7000 Fax 202 994-7005 nsarchiv@gwu edu