Kosberg tri-propellant (lox/lh2/kerosene) rocket engine. 1317 kN. Developed 1990's. Isp=419 / 452s. Experimental version of the RD-0120 engine. Tested by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests.
Application: experimental tri-propellant.
Throttled thrust(vac): 775.000 kN (174,226 lbf). Area Ratio: 85.7. Oxidizer to Fuel Ratio: 4.13.
Status: Developed 1990's.
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Height: 4.55 m (14.92 ft).
Diameter: 2.42 m (7.93 ft).
Thrust: 1,317.00 kN (296,073 lbf).
Specific impulse: 419 s.
Specific impulse sea level: 295 s.
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
Lox/Kerosene/LH2 Tripropellant motors use high-density kerosene for the boost phase, then low-density, high-performance liquid hydrogen for the later stages of ascent. However the propellants are stored in separate tanks. The fuel density indicated is the average for the MAKS design, which burned 17,850 kg LH2 and 18,698 Kerosene to reach orbit using 175,758 kg of liquid oxygen oxidiser. More...
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