The effort during Phase I of the contract included detailed design of a composite wheel assembly to function structurally and mechanically in a manner identical to the existing metal braked main landing gear wheel for the T-39 aircraft. The design and analysis of the graphite composite landing gear wheel was based on demonstrated material properties. A thermal analysis of the composite structure showed the maximum wheel temperature to be 406 F adjacent to the steel brake keys (inner wheel half) and 223 F on the outer wheel half. Hercules 4397/AS resin system was selected for the inner wheel half and 3501/AS for the outer half. During Phase II, one inner and two outer wheel halves were fabricated. (Author)


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    Title :

    Graphite Composite Aircraft Landing Gear Wheel


    Publication date :

    1976


    Size :

    94 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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