|
RD-0131
|
|
Manufacturer Name: RD-0131. Designer: Kosberg. Developed in: 1996-. Application: upper stage. Propellants: Lox/LH2. Thrust(vac): 98.000 kN (22,031 lbf). Isp: 467 sec. Mass Engine: 350 kg (770 lb). Length: 2.20 m (7.20 ft). Chambers: 1. Chamber Pressure: 123.00 bar. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 28.57. Country: Russia. Status: Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.
Bibliography and Further Reading - Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|