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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    Title :

    Analysis of the Shuttle Orbiter reinforced carbon-carbon oxidation protection system


    Contributors:

    Publication date :

    1994-06-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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