Accession Number:

AD0860478

Title:

Summary of Five Years of Altitude Testing of the Apollo Service Module Engine in Altitude Test Cell (J-3)

Descriptive Note:

Final rept. May 1963-Aug 1968

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Schulz, G. H.

Report Date:

1969-10-01

Pagination or Media Count:

99.0

Abstract:

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.

Descriptors:

• *LIQUID PROPELLANT ROCKET ENGINES
• *MANNED SPACECRAFT
• ABLATION
• CAPTIVE TESTS
• COMBUSTION
• COMBUSTION CHAMBERS
• CUT OFF VALVES
• EROSIVE BURNING
• FILM COOLING
• HYPERGOLIC ROCKET PROPELLANTS
• IGNITION
• INJECTORS
• LEAKAGE(FLUID)
• LUNAR CRAFT
• RELIABILITY
• ROCKET NOZZLES
• TRANSIENTS

Subject Categories:

• Liquid Propellant Rocket Engines
• Manned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE