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RD-0131
Status: Design concept 1996-. Date: 1996-. Thrust: 98.00 kN (22,031 lbf). Unfuelled mass: 350 kg (770 lb). Specific impulse: 467 s. Height: 2.20 m (7.20 ft).
Engine: 350 kg (770 lb). Chamber Pressure: 123.00 bar. Thrust to Weight Ratio: 28.57. Oxidizer to Fuel Ratio: 6.
 | RD-0126A Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. |
| RD-0128 Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps. |
| RD-0132 Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump. |
| RD-0133 Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump. |
| RD-0132M Kosberg LOx/LNG rocket engine. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash. |
 | RD-0146 Kosberg LOx/LH2 rocket engine. Centaur upper stage (Atlas); high performance upper stages for Onega, Proton, Angara launch vehicles. Design concept 1998-. |
Country: Russia. Propellants: Lox/LH2. Agency: Kosberg bureau. Bibliography: 342.
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