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Orbit transfer rocket engine technology program: Oxygen materials compatibility testingParticle impact and frictional heating tests of metals in high pressure oxygen, are conducted in support of the design of an advanced rocket engine oxygen turbopump. Materials having a wide range of thermodynamic properties including heat of combustion and thermal diffusivity were compared in their resistance to ignition and sustained burning. Copper, nickel and their alloys were found superior to iron based and stainless steel alloys. Some materials became more difficult to ignite as oxygen pressure was increased from 7 to 21 MPa (1000 to 3000 psia).
Document ID
19890004885
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Schoenman, Leonard (Aerojet TechSystems Co. Sacramento, CA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
REPT-CC0134
NAS 1.26:182195
NASA-CR-182195
Accession Number
89N14256
Funding Number(s)
CONTRACT_GRANT: NAS3-23772
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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