This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Manufacturer Name: AJ10-137. Designer: Aerojet. Application: Apollo SPS. Used on spacecraft: Apollo CSM, Apollo CSM + RM. Propellants: N2O4/Aerozine-50 Thrust(vac): 9,900 kgf. Thrust(vac): 97.50 kN. Isp: 312 sec. Burn time: 585 sec. Chambers: 1. Chamber Pressure: 6.90 bar. Oxidizer to Fuel Ratio: 1.60. Country: USA. Status: Out of Production. References: 225 . Comments: Pressure-fed engine. Used as Apollo SM engine.
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 .