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Extended temperature range ACPS thruster investigationThe successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydrogen/liquid oxygen attitude control propulsion system thruster is described. The test was the result of research to develop a simple, lightweight, and high performance reaction control system without the traditional requirements for extensive periods of engine thermal conditioning, or the use of complex equipment to convert both liquid propellants to gas prior to delivery to the engine. Significant departures from conventional injector design practice were employed to achieve an operable design. The work discussed includes thermal and injector manifold priming analyses, subscale injector chilldown tests, and 168 full scale and 550 N (1250 lbF) rocket engine tests. Ignition experiments, at propellant temperatures ranging from cryogenic to ambient, led to the generation of a universal spark ignition system which can reliably ignite an engine when supplied with liquid, two phase, or gaseous propellants. Electrical power requirements for spark igniter are very low.
Document ID
19740023164
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Blubaugh, A. L. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Schoenman, L. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-134655
Accession Number
74N31277
Funding Number(s)
CONTRACT_GRANT: NAS3-16775
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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