RD-0131
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/LH2 rocket engine. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.
Engine: 350 kg (770 lb). Chamber Pressure: 123.00 bar. Thrust to Weight Ratio: 28.57. Oxidizer to Fuel Ratio: 6.
Subtopics
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-.
Related
- Country
- Russia
- Propellants
- Lox/LH2
- Agency
- Kosberg bureau
- Bibliography
- 342