This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com

astronautix.com RD-862


Manufacturer Name: RD-862. Government Designation: 15D169. Designer: Yangel. Developed in: 1969-72. Application: MR-UR-100 / RS-16 (SS-17) stage 2. Propellants: N2O4/UDMH Thrust(vac): 14,544 kgf. Thrust(vac): 142.63 kN. Isp: 331 sec. Burn time: 195 sec. Mass Engine: 192 kg. Diameter: 0.9 m. Length: 1.7 m. Chambers: 1. Chamber Pressure: 132.40 bar. Oxidizer to Fuel Ratio: 2.55. Country: Ukraine. Status: Out of Production. References: 348 . Comments: Based on RD-857. Thrust vector control by secondary gas injection into nozzle.
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 .