This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Other Designations: S5.3M. Designer: Isayev. Developed in: 1959-60, 1958-60. Application: R-9 (SS-8) missile stage 1. Propellants: Nitric acid/Amine Thrust(vac): 40,452 kgf. Thrust(vac): 396.70 kN. Isp (sea level): 241 sec. Mass Engine: 433 kg. Chambers: 4. Chamber Pressure: 66.00 bar. Area Ratio: 9.55. Oxidizer to Fuel Ratio: 3.60. Country: Russia. Status: Out of Production. References: 320 , 343 . Comments: Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level.
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 .