SOVIET GUIDED MISSILES 7 NOVEMBER 1957 MOSCOW PARADE

• Document Type: CREST
• Collection: NGA Records (Formerly NIMA)
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78T05439A000100340081-4
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 19
• Document Creation Date: December 28, 2016
• Document Release Date: June 2, 2000
• Sequence Number: 81
• Publication Date: October 1, 1958
• Content Type: REPORT

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Declassification review by NIMA/DoD
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rr's
TABLE OF CONTENTS
Page
I. Introduction 5
II. Boosted Surface-to-Aix- Missile (SA-1B? 5
- III. 15 N. M. Ballistic Rocket 0 10
IV. Ballistic Missile SS-1 12
V. 35 N. M. Ballistic Rocket 14
VI. Ballistic Missile SS-3 16
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I. INTRODUCTION
This is a joint photographic intelligence report prepared by the Army,
Navy, and CIA, under Army Chairmanship. It is intended to fulfill intel-
ligence community requirements on missiles appearing in the 7 November
1957 parade in Moscow. It utilizes a series of 5 photographs and 11
drawings in presenting dimensional and configurational analyses of the
5 missiles displayed in the parade.
The quality of the photography ranges from good to poor, and the
detail of the analyses varies accordingly. Mensural data for each missile
presented on the drawings may have the following r4nges of error:
Missile Range of Error -
Boosted Surface-to-Air Missile (SA-112,-).
..15 N. M. Ballistic Rocket
Ballistic Missile SS-1
35 N. M. Ballistic Rocket
Ballistic Missile SS-3
II. BOOSTED SURFACE-TO-AIR MISSILE (SA-1B)
25X1 A. General
The missile is
booster engine and
over-all length of
lengths of the
feet.
_ B. Cirafigurational Analysis
a boosted vehicle, with a probable solid propellant
a probable liquid propellant sustainer motor. The
feet places it approximately midway between the
feet, and the
Analysis of the photography indicates
a missile similar in operation
to the The'rnissile consists of two major systems;
the propulsion system and the guidance and control system.
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CPYRGHT
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 booster 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 utili4es a probable liquid propellant rocket sustainer
motor which is located aft of the four steering fins. Four objects 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 booster. Upon
booster burn out, the aerodynamic drag on the booster causes booster
separation, pullhg the actuator arm, initiating action by the actuator,
thereby firing the: missile sustainer motor. There are two possible pro-
pellant loading pcazts located on the missile fuselage between the stabilizer
f' s. The presence of these ports and the actuator assembly support the
eory of the missile propulsion system being a liquid propellant rocket
sustainer motor.
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2. Guidance and Control System
The guidance and control system of the missile consists of a
pitot tube, four probable antennae, -four stabilizer fins, Four steering
fins, and probably two booster fin ailerons.
The pitot tube projecting from the nose of the missile could
provide the missile computer- with stagnation pressure information.
The 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 antenni ae
o
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 series. The operational Soviet B-200 guidance system
25X1 is a command guidance-type _system.
The four stabiliz-:fins provide the lift which assists in attitude
stabilization during the flight ofthe 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 configuration for control as is employed
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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-1B) 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 thc
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a
A
PITOT TUBE
LEFT SIDE VIEW
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PROBABLE ANTENNAE
:PROBABLE CABLE
G ,t CHAN N EL
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STABILIZER FIN
?
'POSSIBLE PROPELLANT
LOADING PORTS
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STEERING FIN
PROBABLE ACTUATOR
THRUST JOINT
PROBABLE ACTUATOR
ARM ASSEMBLY
PROBABLE BOOSTER
FIN AILERON
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cr,
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CPYRGHT
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III. 15 N.M. BALLISTIC ROCKET
A. General
The Soviet "Honest John Type" ballistic 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 divided into four sections: the warhead, the probable solid
propellant missile sustainer- engine, the probable solid propellant booster
engine, and the booster stabilizer fins.
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. Probable Solid Propellant Booster Engine
The booster fuselage has the same characteristics of construc-
tion a? the missile fuselage, and therefore, it utilizes a probable solid
propellant booster engine.
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MISSILE BODY
BOOSTER
- ? 25X2
MISSILE
WARHEAD
0
PROBABLE SOLID
PROPELLANT BOOSTER
ENGINE
BOOSTER
STABILIZER
FIN 25X1
PROBABLE SOLID PROPELLANT
MISSILE SUSTAINER ENGINE
RIGHT SIDE VIEW
4. Booster Stabilizer Fins
en.
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OBJECTS
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The four stabilizer fins appear to be immovable and there do
not appear to be any control ailerons. With this apparent absence of any
movable control surfaces, there seems to be no capability for any guidance
system to influence missile attitude during flight trajectory.
C. Conclusions
Configurational analysis pf the 15 N.M. Ballistic Rocket indicates the
following characteristics.
1. Boosted surface-to-surface ballistic missile
3. Probable free flight trajectory
4. Probable solid propellant rocket engines
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CPYRGHT
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IV. BALLISTIC MISSILE SS-1
A. General.
The missile is a non-boosted vehicle with an estimated range of
75-100 nautical miles. Due to the poor quality, of the photography, the
desired detail in analysis could not be obtained.
The missile control surfaces could not be examined in detail, but
it is believed that control of the ,amissile is probably accomplished by
air vanes and jet vanes. The guidance of the missile is possibly inertial,
for no antennae could be identified.
There are two cylindrical tanks carried on 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.
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MISSILE BODY
WARHEAD
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STABILIZER FIN
POSSIBLE CABLE CHANNEL
LEFT SIDE VIEW
C. Conclusions
The only SS-1 characteristics which ca.n be derived from the available
photography are as follows:
1. Non-boosted surface-to-surface ballistic missile
3. ,Possible liquid propulsion system
4. Possible inertial guidance system
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V. 35 N. M. BALLISTIC ROCKET
A. General
The missile is a probable solid propellant vehicle with an estimated I
range capability of 35 nautical miles.
B. Configurational Analysis
The missile
similar in configuration ro theSoviet 15 N. M. Ballistic
Rocket, but it is ap roxirnately twice as large in diameter,
25X1 longer, and has a greater 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.
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C. Conclusions
The 35 N. M. Ballistic Rocket appears to be similar to the "Honest
John Type" missile but probably has a larger warhead and a greater range
capability.
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25X1 25X1
LEFT' SIDE VIEW
MISSILE BODY
METAL CASING
STABILIZER
FIN
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OBJECTS
fl-
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VI. BALLISTIC MISSILE SS-3
A. General
The "V-2 Type" Soviet missile is a probable liquid propellant,
single-stage missile, with an estimated range capability of 350 nautical
miles.
CPYRGHT
25X2 B. Configurational Analysis
This, the largest missile shown in the parade, appears to be a final
phase in the development of the German Series" and has
A probable propellant loading port' (not shown
on graphic) is located neae- 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 consist of four 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 trajectory.
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PITCH
FIN
MISSILE
FUSELAGE
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EXTERNAL
VANE
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YAW
FN
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PITCH
FIN
4".
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YAW FIN
STERN VIEW
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C. Conclusions
The SS-3 missile has the following characteristics:
1. Probable liquid propellant sustainer motor
2. Possible radio-inertial guidance system
3. Internal and external vanes control systeIn
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011..
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MISSILE BODY
WARHEAD
0
V ?
POSSIB
CABLE
CHANN L
' LEFT SIDE VIEW
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STABILIZER
PIN
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PHOTO DATA-
"Life" magazine photography
Parade). (U)
REFERENCE DATA:
AFM 200-14, Intelligence Collection Guidance Manual. (C)
complete coverage of 7 November 1957
AFM 52-31, Guided Missile Fundamentals. (U)
Summary of Significant Soviet Weapons and Equ*ment, Project NR:
A-1046, DA-ACSI. (S)
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