Encyclopedia Astronautica

Glushko N2O4/UDMH rocket engine. 881 kN. R-36-0 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD-250 units make RD-251. Isp=301s.

Application: R-36-0 stage 1, Tsyklon 2 stage 1.

Chambers: 2. Engine: 576 kg (1,269 lb). Chamber Pressure: 83.30 bar. Area Ratio: 14.7. Thrust to Weight Ratio: 155.97. Oxidizer to Fuel Ratio: 2.6.

AKA: 8D723.
Status: Out of Production.
Unfuelled mass: 576 kg (1,269 lb).
Height: 1.76 m (5.78 ft).
Thrust: 881.00 kN (198,056 lbf).
Specific impulse: 301 s.
Specific impulse sea level: 269 s.
Burn time: 120 s.
First Launch: 1960-65.

More... - Chronology...

Associated Countries
See also
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...

  • Rakhmanin, V F, Odnazhdy i Navsegda, NPO Energomash, Moscow 1998 via Dietrich Haeseler.

Home - Browse - Contact
© / Conditions for Use