Analytical methods used to investigate entry gap heating in the Shuttle orbiter thermal protection system are described. Analytical results are given for a fuselage lower-surface location and a wing lower-surface location. These are locations where excessive gap heating occurred on the first flight of the Shuttle. The results of a study to determine the effectiveness of a half-height ceramic fiber gap filler in preventing hot-gas flow in the tile gaps are also given.


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    Title :

    Analysis of gap heating due to stepped tiles in the shuttle thermal protection system


    Contributors:

    Publication date :

    1983-08-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English