| MR-510 |
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Engine Model: MR-510. Designer: Aerojet Redmond. Propellants: Hydrazine. Thrust(vac): 0.25 N (0.06 lbf). Isp: 600 sec. Burn time: 6,228,000 sec. Mass Engine: 1.58 kg (3.48 lb). Diameter: 0.0430 m (0.1410 ft). Length: 0.25 m (0.82 ft). Chambers: 1. Country: USA. Status: In Production. Arcjet system. 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. |
