| Aerojet 62 |
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Engine Model: Aerojet 62. Designer: Aerojet. Propellants: N2O4/MMH. Thrust(vac): 62 N (13 lbf). Isp: 287 sec. Mass Engine: 1.13 kg (2.49 lb). Chambers: 1. Area Ratio: 150.00. Thrust to Weight Ratio: 5.59. Country: USA. Status: In Production. Mixture Ratio(O/F): 1.65. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted. | |