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Hydrogen-oxygen catalytic ignition and thruster investigation. Volume 2: High pressure thruster evaluationsA high pressure thruster effort was conducted with the major objective of demonstrating a duct cooling concept with gaseous propellant in a thruster operating at nominally 300 psia and 1500 lbf. The analytical design methods for the duct cooling were proven in a series of tests with both ambient and reduced temperature propellants. Long duration tests as well as pulse mode tests demonstrated the feasibility of the concept. All tests were conducted with a scaling of the raised post triplet injector design previously demonstrated at 900 lbf in demonstration firings. A series of environmental conditioned firings were also conducted to determine the effects of thermal soaks, atmospheric air and high humidity. This volume presents the results of the high pressure thruster evaluations.
Document ID
19730004132
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Johnson, R. J. (TRW Systems Group Redondo Beach, CA, United States)
Heckert, B. (TRW Systems Group Redondo Beach, CA, United States)
Burge, H. L. (TRW Systems Group Redondo Beach, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
TRW-14549-6001-RO-00-VOL-2
NASA-CR-120870
Accession Number
73N12859
Funding Number(s)
CONTRACT_GRANT: NAS3-14347
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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