Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Modification of RD-0233 including tank pressurization system. Isp=310s. First flight 1974.
Application: UR-100N / RS-18 (SS-19) stage 1.
Chamber Pressure: 205.00 bar.
Status: Out of Production.
More... - Chronology...
Thrust: 520.00 kN (116,900 lbf).
Specific impulse: 310 s.
Specific impulse sea level: 285 s.
Burn time: 121 s.
First Launch: 1969-74.
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...
Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.
Pavutniskiy, Yu M; Mazarchenko, V A; Shilenkov, M V; Gerasimov, A B, Otechestvennye Rakety-Nos 1 and 2, St.Peterburg (State Marine-Technol. Univ.), 1996 via Dietrich Haeseler.
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
ROCKOT Users Guide, Issue 2, Rev. 0, Eurockot Launch Services, Bremen 1998. via Dietrich Haeseler.
UR-100N Stage 1N N2O4/UDMH propellant rocket stage. Loaded/empty mass 77,150/5,695 kg. Thrust 1,778.66 kN. Vacuum specific impulse 310 seconds. More...
Home - Browse - Contact
© / Conditions for Use