This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Manufacturer Name: RD-0215. Designer: Kosberg. Developed in: 1962-65. Application: Planned heavy launcher (UR-700 ?) stage 1. Used on stages: UR-100 Stage 1. Used on launch vehicles: UR-100. Propellants: N2O4/UDMH Thrust(vac): 250,000 kgf. Thrust(vac): 2,450.00 kN. Isp: 310 sec. Isp (sea level): 280 sec. Burn time: 102 sec. Diameter: 2.0 m. Chambers: ?. Country: Russia. Status: Developed 1962-65. First Flight: 1966. References: 309 . Comments: Engine unit (DU) consisting of 1 RD-0217 for tank pressurization and three RD-0216. Intended for stage 1 of heavy launcher by Chelomei. Development stopped, hardware not hot-tested. Staged combustion cycle with ox.-rich gas generator.
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 .