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Orbital transfer vehicle 3000 LBF thrust chamber assembly hot fire test programThe Aerojet Orbital Transfer Vehicle (OTV) Thrust Chamber Assembly (TCA) concept consists of a hydrogen cooled chamber, and annular injector, and an oxygen cooled centerbody. The hot fire testing of a heat sink version of the chamber with only the throat section using hydrogen cooling is documented. Hydraulic performance of the injector and cooled throat were verified by water flow testing prior to TCA assembly. The cooled throat was proof tested to 3000 psia to verify the integrity of the codeposited EF nickel-cobalt closeout. The first set of hot fire tests were conducted with a heat sink throat to obtain heat flux information. After demonstration of acceptable heat fluxes, the heat sink throat was replaced with the LH2 cooled throat section. Fourteen tests were conducted with a heat sink chamber and throat at chamber pressures of 85 to 359 psia. The injector face was modified at this time to add more face coolant flow. Ten tests were then conducted at chamber pressures of 197 to 620 psia. Actual heat fluxes at the higher chamber pressure range were 23 percent higher than the average of 10 Btu/in 2 predicted.
Document ID
19880020474
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Schneider, Judy (Aerojet TechSystems Co. Sacramento, CA, United States)
Hayden, Warren R. (Aerojet TechSystems Co. Sacramento, CA, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1988
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:182145
NASA-CR-182145
Accession Number
88N29858
Funding Number(s)
PROJECT: RTOP 506-42-21
CONTRACT_GRANT: NAS3-23772
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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