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a single AJ10-190 engine, based on the Apollo Service Module's Service Propulsion System engine, which produces of thrust with a specific impulse (I_sp) of 316 seconds. The oxidizer-to-fuel ratio is 1.65-to-1, The expansion ratio of the nozzle exit to the throat is 55-to-1, and the chamber pressure of the engine is 8.6 bar. The dry weight of each engine is 118kg (260lb). Each engine could be reused for 100

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