| HiPAT |
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Engine Model: HiPAT. Designer: Aerojet Redmond. Propellants: N2O4/MMH. Thrust(vac): 445 N (100 lbf). Isp: 323 sec. Burn time: 3,600 sec. Mass Engine: 5.20 kg (11.40 lb). Diameter: 0.36 m (1.19 ft). Length: 0.72 m (2.36 ft). Chambers: 1. Chamber Pressure: 9.40 bar. Area Ratio: 375.00. Country: USA. Status: In Production. High performance liquid apogee thruster. 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. |
