SIMULATED ALTITUDE TESTING OF THE APOLLO SERVICE MODULE PROPULSION SYSTEM (REPORT 1, PHASE 2 DEVELOPMENT TEST)

The Apollo Service Module SM propulsion system, consisted of the AJ10-137 flight-type rocket engine and a ground test replica of the Apollo SM propellant system and was subjected to simulated altitudes up to 120,000 ft during engine firing operation. The testing reported was conducted with the first three engine assemblies of the Phase II development program and included fifty-four test firings with an accumulated duration of 1561.2 sec. The primary objectives of the test were to check out system operations, 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.