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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    Williams, S. D. (Autor:in) / Curry, Donald M. (Autor:in) / Chao, Dennis (Autor:in) / Pham, Vuong T. (Autor:in)

    Erscheinungsdatum :

    1994-06-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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

    S. D. Williams / D. M. Curry / D. Chao et al. | NTIS | 1994


    Ablation analysis of the Shuttle Orbiter oxidation protected reinforced carbon-carbon

    Williams, S. D. / Curry, Donald M. / Chao, Dennis C. et al. | AIAA | 1995


    Ablation analysis of the Shuttle Orbiter oxidation protected reinforced carbon-carbon

    Williams, S. / Curry, Donald / Pham, Vuong et al. | AIAA | 1994


    Space shuttle orbiter carbon-carbon oxidation performance

    Curry, D.M. / Yuen, E.H. / Chao, D.C. et al. | Tema Archiv | 1991


    Emittance measurements of Space Shuttle Orbiter Reinforced Carbon-Carbon

    Caram, Jose M. / Bouslog, Stanley A. / Cunnington, George R., Jr. | NTRS | 1993