SOVIET GUIDED MISSILES 7 NOVEMBER 1957 MOSCOW PARADE

• Document Type: CREST
• Collection: NGA Records (Formerly NIMA)
• Document Number (FOIA) /ESDN (CREST): CIA-RDP78T05439A000300100069-6
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 20
• Document Creation Date: December 28, 2016
• Document Release Date: May 26, 2000
• Sequence Number: 69
• Publication Date: October 1, 1958
• Content Type: REPORT

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I. Introduction .. . . ... .. . .... ... . . .... . . . ..... . . 5
II. Boosted Surface-to-Air Missile (SA-1B) . . .. . . . . . ... . 5
III. 15 N. M. Ballistic Rocket ........................ 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 i n Lelligence 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. Estimated range capabilities are
relative to the strength
Missile
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 ranges of error:
Boosted Surface-to-Air Missile (SA-1B)
15 N. M. Ballistic Rocket
Ballistic Missile SS-1
35 N. M. Ballistic Rocket
Ballistic Missile SS-3
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II. BOOSTED SURFACE-TO-AIR MISSILE (SA-1B)
A. General
The missile is a boosted vehicle, with a probable solid propellant
booster engine and a
robable liquid
propellant sustainer motor. The
over-all length of
Configurational Analysis
The missile consists of two major systems;
the propulsion system and the guidance and control system.
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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
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 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, pulling the actuator arm, initiating action by the actuator,
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.
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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 antennae are placed approximately at the same
position on the Soviet missileF F__
and could function in a command guidance system
The operational Soviet B-200 guidance system
skin, and they extend from the probable location of a guidance package to
is a command guidance-type 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
the steering fin mechanism. It is interesting to note that the Soviets
have not employed the canard configuration for control
Th bbl booster fin ailerons could be used for roll
o
t
w
e pro a e
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
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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.
1. Warhead
There are several objects appearing on the skin of the
warhead which could be utilized in its loading and arming.
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-
the missile fuselage, and therefore, it utilizes a probable solid
propellant booster engine.
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4. Booster Stabilizer Fins
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 of 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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IV. BALLISTIC MISSILE SS-i
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
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.
it is believed that control of the missile is probably accomplished by
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C. Conclusions
The only SS-1 characteristics which can 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
A. General
The missile is a probable solid propellant vehicle with an estimated
range capability of 35 nautical n-ii les.
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
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-
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boosted. The visible control surfaces consist of six apparently immovable
stabilizer fins with no apparent ailerons.
C. Conclusions
and has a greater payload capability. This warhead also has objects
. 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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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.
B. Configurational Analysis
This, the largest missile shown in the parade,
hase in the development
A probable propellant loading
ears to be a final
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 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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C. Conclusions
The SS-3 missile has the following characteristics:
1.
2.
3.
Probable liquid propellant sustainer motor.
Possible radio-inertial guidance system
Internal and external vanes control system
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PHOTO DATA:
AiK, Moscow. 8 November 1957 (Photo Attachments). (S)
"Life" magazine photography (complete coverage of 7 November 1957
Parade). (U)
REFERENCE DATA:
AFM 200-14, Intelligence Collection Guidance Manual. (C)
AAA & GM School (Notes), Ft. Bliss, Texas. (C)
AFM 52-31, Guided Missile Fundamentals. (U)
Summary of Significant Soviet Weapons and Equipment, Proj ect NR:
A-1o46, DA-ACSI. (S)
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SOVIET GUIDED MISSILES
7 November 1957 Moscow Parade
PIC/R-1/58
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