SOV - 8K51 / R-5M / SS-3 Shyster

R-5M, 8K51, SS-3 Shyster
Basic data


Start of development: 10 April 1954
Design Office: OKB-1
Manufacturer: plant 586, Dnepropetrovsk
Flight tests: January 1955 - February 1956
Combat duty: 10 May 1956
Entered service: 21 June 1956
Number of stages: 1
Power plant: cryogenic liquid
Launcher: ground, open
Number of warheads and power: 1x300 kt
Combat payload: 1350 kg
Maximum range: 1200 km
Guidance: inertial with radio correction
Accuracy: maximum error 1.5 km laterally, 1.25 km remotely
Length: 20,747 m
Maximum diameter: 1.652 m (fuselage), 3.452 m (wings)
Launch weight: 28.610 t
Fuel mass: 24.760 t (including hydrogen peroxide)
Oxidant: liquid oxygen
Fuel: 92 % ethyl alcohol
Thrust (sea level/vacuum): 432/500 kN
Specific impulse (sea level/vacuum): 2158/2433 m/s
Preparation for launch: 2 hours
Lifetime:


Source: Russian Strategic Nuclear Forces, Pavel Podvig, Oleg Bukharin, MIT Press, Cambridge, 2001
(original: Raketniye vojska strategicheskogo naznachenija)
URL : https://www.valka.cz/SOV-8K51-R-5M-SS-3-Shyster-t21505#82255 Version : 0
The SS-3 missiles used an erector built on the base of a JaAZ-210 truck (left)
The warhead was carried by a modified ZIS-151 (right) .
SOV - 8K51 / R-5M / SS-3 Shyster - (Aviarus-21: Raketnyje komplexy raketnych vojsk strategčeskogo  naznačenija )

(Aviarus-21: Raketnyje komplexy raketnych vojsk strategčeskogo naznačenija )
SOV - 8K51 / R-5M / SS-3 Shyster - (Aviarus-21: Raketnyje komplexy raketnych vojsk strategčeskogo  naznačenija )

(Aviarus-21: Raketnyje komplexy raketnych vojsk strategčeskogo naznačenija )
URL : https://www.valka.cz/SOV-8K51-R-5M-SS-3-Shyster-t21505#82352 Version : 0
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