Russian space tug. Study 2004. Upper stage / space tug - in development 2004. Launched by Angara launch vehicle family.. 8 restarts. Propellant ration 2.0:1.
High performance storable liquid engine. Engine system consisted of: main engine (2000 kgf, Isp=325.5 s) + 4 11D458 (40 kgf, Isp=252 s) + 12 17D58E (1.36 kgf, Isp=247 s). Main engine: Derivative of S5.92. Capable of 8 restarts. Total deliverable impulse 2,000,000 kgf-s. Minimum impulse 2500 kg-s. Maximum burn time 1000 seconds; minimum time 1 second. Time between burns between 15 seconds and 5 hours. Vernier engines: 4 x 40 kgf. Specific impulse 275 sec. Total summary impulse 14,112 kg-s. Minimum impulse 4 kg-s. Orientation engines: 12 x 1.3 kgf. Specific impulse 270 sec. Minimum impulse 0.068 kg-s.
Gross mass: 6,565 kg (14,473 lb).
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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.
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...
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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