This page no longer updated from 31 October 2001.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

astronautix.com HM-10


Designer: SEP. Propellants: Lox/LH2 Thrust(vac): 6,300 kgf. Thrust(vac): 61.80 kN. Isp: 443 sec. Mass Engine: 145 kg. Diameter: 1.0 m. Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 61.00. Thrust to Weight Ratio: 43.45. Country: France. Status: Developed 1990's. Comments: Engine for potential Ariane 5 upper stage.
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 .