| MR-120 |
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Engine Model: MR-120. Designer: Aerojet Redmond. Application: Small ICBM. Propellants: Hydrazine. Thrust(vac): 90 N (20 lbf). Isp: 229 sec. Burn time: 150 sec. Mass Engine: 0.41 kg (0.90 lb). Diameter: 0.0420 m (0.1370 ft). Length: 0.15 m (0.49 ft). Chambers: 1. Chamber Pressure: 12.40 bar. Area Ratio: 15.00. Country: USA. Status: In Production. Developed as an attitude control thruster for the small ICBM. 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. |
