Altitude Testing of the Aerojet AJ10-179 Liquid Rocket Engine.

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Abstract:

Three flightweight Aerojet AJ10-179 engine assemblies were tested under vacuum conditions. The testing had two objectives. First was demonstration that the engine could meet the requirements of a Ballistic Missile Post Boost Propulsion System with N2O4-N2H4 as the propellants. The second was measurement and evaluation of the engines capability to perform pulsing missions, such as a space maneuvering mission, using N2O4-MMH as the propellants. Injector erosion was encountered in 3 of 5 tests using MMH. Higher gas temperatures, less cooling capability and possible combustion roughness caused higher heat loads which produced the erosion. Modified author abstract

Author(s):
Jamieson, Robert A.
Author Organization(s):
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF
Descriptive Note:
Final rept. Jul 70-Jun 72,
Pagination:
0105

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFRPL-TR-72-128
Project Number(s):
AF-305911RD
 Subject Terms
Joint Capability Areas:
JCA_3_Force Application; JCA_3.1.1_Maneuver to Engage; JCA_3.1_Maneuver; JCA_3.2_Engagement; JCA_3.2.1_Kinetic Means
Communities of Interest:
Weapons Technologies
Descriptor(s):
*SURFACE TO SURFACE MISSILES, CAPTIVE TESTS, LIQUID PROPELLANT ROCKET ENGINES, NITROGEN OXIDES, HYDRAZINES, COMBUSTION CHAMBERS, INJECTORS, VALVES, PROPELLANT CONTROL, SPECIFIC IMPULSE, BIPROPELLANTS
Field(s)/Group(s):
Surface-Launched Guided Missiles, Liquid Propellant Rocket Engines
Keyword(s):
AJ 10 ENGINES, PBPS(POST BOOST PROPULSION SYSTEMS), POST BOOST PROPULSION SYSTEMS
Report Date:
1973 Mar 01