N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,565/1,600 kg. Thrust 19.60 kN. Vacuum specific impulse 325.5 seconds. Version proposed as Angara upper stage. 8 restarts. Propellant ration 2.0:1.
Status: In development.
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Gross mass: 6,565 kg (14,473 lb).
Unfuelled mass: 1,600 kg (3,500 lb).
Height: 2.61 m (8.56 ft).
Diameter: 2.50 m (8.20 ft).
Span: 2.50 m (8.20 ft).
Thrust: 19.60 kN (4,406 lbf).
Specific impulse: 326 s.
Burn time: 1,000 s.
Number: 2 .
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
Angara 1.1 Russian orbital launch vehicle. The initial flight version would be the Angara 1.1, featuring a single URM core module with the existing Briz upper stage. Payload would be 2.0 tonnes to a 200 km / 63 deg orbit). Other vehicle variants were numbered according to the number of URM's. 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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