Reusable, oxidation-protected reinforced carbon-carbon (RCC) has been successfully flown on all Shuttle Orbiter flights. Thermal testing of the silicon carbide-coated RCC to determine its oxidation characteristics has been performed in convective (plasma Arc-Jet) heating facilities. Surface sealant mass loss was characterized as a function of temperature and pressure. High-temperature testing was performed to develop coating recession correlations for predicting performance at the over-temperature flight conditions associated with abort trajectories. Methods for using these test data to establish multi-mission re-use (i.e., mission life) and single mission limits are presented.


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    Titel :

    Analysis of the Shuttle Orbiter Reinforced Carbon-Carbon Oxidation Protection System


    Beteiligte:
    S. D. Williams (Autor:in) / D. M. Curry (Autor:in) / D. Chao (Autor:in) / V. T. Pham (Autor:in)

    Erscheinungsdatum :

    1994


    Format / Umfang :

    67 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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