The test facility presented herein uses a groundbased rocket combustor to test the durability of new ceramic composite and metallic materials in a rocket engine thermal environment. A gaseous H2/02 rocket combustor (essentially a ground-based rocket engine) is used to generate a high temperature/high heat flux environment to which advanced ceramic and/or metallic materials are exposed. These materials can either be an integral part of the combustor (nozzle, thrust chamber etc) or can be mounted downstream of the combustor in the combustor exhaust plume. The test materials can be uncooled, water cooled or cooled with gaseous hydrogen.


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    Titel :

    A Combustion Research Facility for Testing Advanced Materials for Space Applications


    Beteiligte:

    Kongress:

    AIAA Aerospace Sciences Meeting and Exhibit ; 2003 ; Reno, NV, United States


    Erscheinungsdatum :

    2003-01-06


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    A Combustion Research Facility for Testing Advanced Materials for Space Applications

    Bur, M. J. / AIAA | British Library Conference Proceedings | 2003



    Advanced materials for space applications

    Pater, Ruth H. / Curto, Paul A. | Elsevier | 2007


    Advanced Materials for Space Applications

    R. H. Pater / P. A. Curto | NTIS | 2005


    Advanced Materials for Space Applications

    Pater, Ruth H. / Curto, Paul A. | AIAA | 2005