Encyclopedia Astronautica

Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Isp=335s. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%.

Adaptation to western market . 15 ignitions tested with one single engine.

Engine: 185 kg (407 lb). Chamber Pressure: 153.00 bar. Thrust to Weight Ratio: 54.07.

Status: Design concept 1998-.
Unfuelled mass: 185 kg (407 lb).
Height: 1.60 m (5.24 ft).
Diameter: 0.80 m (2.62 ft).
Thrust: 98.10 kN (22,054 lbf).
Specific impulse: 336 s.
Burn time: 600 s.
First Launch: 1998-.

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...

Associated Propellants
  • 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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