Simulated Altitude Testing of the Apollo Service Module Propulsion System (Report I, Phase II Development Test)

Summary

The Apollo Service Module (S/M) propulsion system, tested at AEDC, consisted of the Aerojet-General Corporation AJ10-137 flight type rocket engine and a North American Aviation ground test replica of the Apollo S/M propellant system and was subjected to simulated altitudes up to 120,000 ft during engine firing operation. The testing reported herein was conducted with the first three engines assemblies of the AEDC Phase II development program and included 74 test firings with an accumulated duration of 1561.2 seconds. The primary objectives of the test were to check out system operation, define propulsion system altitude performance, and prove engine structural endurance over ranges of propellant mixture ratio and combustion chamber pressure. Engine gimbaling operations were performed during certain firings. Ballistic performance of the three engine assemblies tested is presented. Engine temperature data, the effect of ablation on the thrust vector, and a discussion of engine gimbal operation are also presented.

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Contact(s): Cape Canaveral Space Force Station CRM Manager

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