Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100, UR-100K stage 1. Out of Production. Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991. Isp=313s.
Application: UR-100, UR-100K / RS-10 (SS-11) stage 1.
Chamber Pressure: 147.00 bar.
More... - Chronology...
Status: Out of Production.
Thrust: 219.00 kN (49,233 lbf).
Specific impulse: 313 s.
First Launch: 1963-66.
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
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...
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: here.
8S816 N2O4/UDMH propellant rocket stage. Loaded/empty mass 32,799/3,000 kg. Thrust 868.80 kN. Vacuum specific impulse 310 seconds. Orevo has sectioned hardware. Total mass, sea level thrust accurate; Isp, empty mass and burn time estimated. Source: Placard, Orevo. More...
Home - Browse - Contact
© / Conditions for Use