A 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.


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    Titel :

    Testing of Wrought Iridium/Chemical Vapor Deposition Rhenium Rocket


    Beteiligte:

    Kongress:

    1996 Propulsion and Joint Subcommittee Meetings ; 1996 ; Albuquerque, NM, United States


    Erscheinungsdatum :

    1996-12-09


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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