This page no longer updated from 31 October 2001. Latest version can be found at RD-0132

Manufacturer Name: RD-0132. Designer: Kosberg. Developed in: 1996-. Application: upper stage. Propellants: Lox/LH2 Thrust(vac): 10,000 kgf. Thrust(vac): 98.00 kN. Isp: 469 sec. Mass Engine: 370 kg. Length: 1.4 m. Chambers: 4. Chamber Pressure: 98.00 bar. Oxidizer to Fuel Ratio: 5.90. Country: Russia. Status: Design concept 1996-. References: 342 . Comments: Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .