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Testing of Wrought Iridium/Chemical Vapor Deposition Rhenium RocketA 22-N class, iridium/rhenium (Ir/Re) rocket chamber, composed of a thick (418 miocrometer) wrought iridium (Ir) liner and a rhenium substrate deposited via chemical vapor deposition, was tested over an extended period on gaseous oxygen/gaseous hydrogen (GO2/GH2) propellants. The test conditions were designed to produce species concentrations similar to those expected in an Earth-storable propellant combustion environment. Temperatures attained in testing were significantly higher than those expected with Earth-storable propellants, both because of the inherently higher combustion temperature of GO2/GH2 propellants and because the exterior surface of the rocket was not treated with a high-emissivity coating that would be applied to flight class rockets. Thus the test conditions were thought to represent a more severe case than for typical operational applications. The chamber successfully completed testing (over 11 hr accumulated in 44 firings), and post-test inspections showed little degradation of the Ir liner. The results indicate that use of a thick, wrought Ir liner is a viable alternative to the Ir coatings currently used for Ir/Re rockets.
Document ID
Document Type
Reprint (Version printed in journal)
Reed, Brian D.
(NASA Lewis Research Center Cleveland, OH United States)
Schneider, Steven J.
(NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
August 17, 2013
Publication Date
December 9, 1996
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:107452
Meeting Information
1996 Propulsion and Joint Subcommittee Meetings(Albuquerque, NM)
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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