This page no longer updated from 31 October 2001. Latest version can be found at AJ10-118K

Manufacturer Name: AJ10-118K. Designer: Aerojet. Used on stages: Delta K. Used on launch vehicles: Delta 3925, Delta 4920, Delta 5920, Delta 6925, Delta 7925, Delta IV Small. Propellants: N2O4/Aerozine-50 Thrust(vac): 4,425 kgf. Thrust(vac): 43.40 kN. Isp: 321 sec. Isp (sea level): 120 sec. Burn time: 444 sec. Mass Engine: 98 kg. Diameter: 1.7 m. Chambers: 1. Chamber Pressure: 8.84 bar. Area Ratio: 65.00. Thrust to Weight Ratio: 43.70. Country: USA. Status: In Production. First Flight: 1982. Last Flight: 1999. Flown: 98. References: 225 .

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.

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Last update 12 March 2001.
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