RD-0120TD

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RD-0120TD

Part of RD-0120

Kosberg tri-propellant (LOx/LH2/kerosene) rocket engine. Developed 1990's. 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.

Status: Developed 1990's. Thrust: 1,317.00 kN (296,073 lbf). Specific impulse: 419 s. Specific impulse sea level: 295 s. Height: 4.55 m (14.92 ft). Diameter: 2.42 m (7.93 ft).

Throttled thrust(vac): 775.000 kN (174,226 lbf). Area Ratio: 85.7. Oxidizer to Fuel Ratio: 4.13.

Country: Russia. Propellants: Lox/Kerosene/LH2, Lox/LH2. Agency: Kosberg bureau.

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