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AJ10-118K
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Manufacturer Name: AJ10-118K. Designer: Aerojet. Propellants: N2O4/Aerozine-50. Thrust(vac): 43.400 kN (9,757 lbf). Isp: 321 sec. Burn time: 444 sec. Mass Engine: 98 kg (216 lb). Diameter: 1.70 m (5.50 ft). Chambers: 1. Chamber Pressure: 8.96 bar. Area Ratio: 65.00. Thrust to Weight Ratio: 43.70. Country: USA. First Flight: 1989. Last Flight: 2006. Flown: 127. A pressure-fed engine, optimized for altitude operation. First Flown: August 1982, Delta 164. Mounting: fixed. Engine Cycle: pressure-fed. Oxidizer: nitrogen tetroxide at 9.1 kg/sec. Fuel: Aerozine-50 at 4.76 kg/sec. Mixture Ratio: 1.9:1. Thrust: 43.38 kN vacuum. Isp: 320.5 sec vacuum. Expansion Rate: 65:1. Combustion Chamber Pressure: 8.84 atm. Cooling Method: ablative chamber, radiative skirt. Burn Time: qualified up to 500 sec (unlimited starts). The engine produced approx. 212-213 seconds of Isp when tested with a 1:1 nozzle at sea level for acceptance testing. The engine is not regeneratively cooled. It uses an ablative made from rubber modified silica phenolic at the combustion flame front.
AJ10-118K used on Rocket Stages
Bibliography and Further Reading - Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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