Summary of Five Years of Altitude Testing of the Apollo Service Module Engine in Altitude Test Cell (J-3)
Final rept. May 1963-Aug 1968
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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The primary results of the development and qualification testing of the AJ10-137 rocket engine for the Apollo Service Module conducted at the Arnold Engineering Development Center AEDC are summarized. Testing of the AJ10-137, a 20,000 lbf nominal thrust liquid-propellant engine, was conducted at combustion chamber pressures of from 77 to 133 psia and at mixture ratios of the two hypergolic propellants, nitrogen tetroxide and Aerozine-50, from 1.4 to 2.4. Both Block I and Block II engines were tested to determine engine performance and to establish durability and reliability of the basic engine design and subsequent modifications. As a result of these tests, the Block II engine performance was established, and the engine was qualified for the lunar mission.
- Liquid Propellant Rocket Engines
- Manned Spacecraft