Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. Isp=343s.
Engine: 229 kg (504 lb). Chamber Pressure: 153.00 bar. Thrust to Weight Ratio: 43.68.
Status: Design concept 1998-.
More... - Chronology...
Unfuelled mass: 229 kg (504 lb).
Height: 2.34 m (7.67 ft).
Diameter: 1.25 m (4.10 ft).
Thrust: 98.10 kN (22,054 lbf).
Specific impulse: 343 s.
Burn time: 600 s.
First Launch: 1998-.
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...
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