Encyclopedia Astronautica
RD-252



rd252.jpg
RD-252
NPO Enerogmash Museum, November 1992
Credit: © Dietrich Haeseler
Glushko N2O4/UDMH rocket engine. 940.5 kN. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965.

Application: R-36-0 stage 2; Tsyklon 2 stage 2.

Chambers: 2. Engine: 715 kg (1,576 lb). Chamber Pressure: 89.50 bar. Area Ratio: 46.1. Thrust to Weight Ratio: 134.12. Oxidizer to Fuel Ratio: 2.6.

Status: In production.
Unfuelled mass: 715 kg (1,576 lb).
Height: 2.19 m (7.17 ft).
Diameter: 2.59 m (8.49 ft).
Thrust: 940.50 kN (211,433 lbf).
Specific impulse: 317 s.
Burn time: 160 s.
First Launch: 1961-66.
Number: 131 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • R-36-O Ukrainian orbital missile. The R-36-O was the only orbiting military nuclear weapon ever deployed, although in order to remain legal under international treaties it was a 'fractional orbital' weapon. Although American infrared early warning satellites invalidated the 'surprise attack' component of the concept, 18 missiles were operational from 1969 to 1983. More...
  • Tsiklon-2 Ukrainian orbital launch vehicle. A government decree of 24 August 1965 ordered development by Yangel of a version of his R-36 rocket to orbit Chelomei's IS (Istrebitel Sputnik) ASAT and US (Upravlenniye Sputnik) naval intelligence satellites. The Tyklon 2 definitive operational version replaced the 11K67 launch vehicle from 1969 and was an adaptation of the 8K69 (SS-9) two stage ICBM. The IS and US Raketoplan-derived payloads had their own engines for insertion into final orbit. More...

Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...

Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...

Bibliography
  • Haeseler, Dietrich, Information from NPO Energomash museum exhibit, Nov. 1992 via Dietrich Haeseler.
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
  • GKB Yuzhnoe "Yangel", Data sheets Paris Airshow 1997 via Dietrich Haeseler.

Associated Stages
  • R-36-0-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 48,000/5,000 kg. Thrust 955.99 kN. Vacuum specific impulse 317 seconds. More...
  • R-36-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 49,300/3,700 kg. Thrust 940.40 kN. Vacuum specific impulse 317 seconds. Verniers 4 x RD-69M, 54.3 kN, maximum 50 degree gimbal angle. More...
  • Tsyklon 2-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 49,300/3,700 kg. Thrust 940.40 kN. Vacuum specific impulse 317 seconds. More...

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