N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,700/1,700 kg. Thrust 19.60 kN. Briz KM differs from Briz K in having 'compact' components, special payload truss for Globalstar dispenser. The truss is 1.8 m in diameter and has a volume of 8.8 m3.
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Gross mass: 6,700 kg (14,700 lb).
Unfuelled mass: 1,700 kg (3,700 lb).
Height: 2.50 m (8.20 ft).
Diameter: 2.50 m (8.20 ft).
Thrust: 19.60 kN (4,406 lbf).
Burn time: 1,000 s.
Number: 22 .
S5.98M Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and Briz-M upper stages. Isp=325s. Engine system consists of: main engine (2000 kgf, Isp=325.5s) + 4x11D458 (40 kgf, Isp=252s) + 12x17D58E (1.36 kgf, Isp=247s). 8 restarts. First flight 1990. More...
Associated Launch Vehicles
Rokot Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage. More...
Associated Manufacturers and Agencies
Chelomei Russian manufacturer of rockets, spacecraft, and rocket engines. Chelomei Design Bureau, Reutov, 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...
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