| MRM-106 |
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Engine Model: MRM-106. Designer: Aerojet Redmond. Propellants: Hydrazine. Thrust(vac): 27 N (6 lbf). Isp: 231 sec. Burn time: 2,991 sec. Mass Engine: 0.94 kg (2.07 lb). Diameter: 0.0310 m (0.1010 ft). Length: 0.17 m (0.56 ft). Chambers: 1. Country: USA. Status: In Production. Steady-state thrust 9 N. 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. |
