Examination of data on weight of various structural elements fabricated in graphite composites, and application of this data to study of weight of X-22A V/STOL aircraft; it is shown that over 30% of weight of current aluminum structure could be saved, resulting in 100% increase in payload; studies include such elements as tension members, stiffened and unstiffened compression panels, shear panels, sandwich panels, columns, beams, torque tubes, etc; potential failure modes such as buckling, fiber tensile strength, resin shear strength, fiber resin bond strength, and resin strain limitations are considered.


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    Title :

    Application of graphite fiber composites to airframe structures


    Additional title:

    SAE -- Paper


    Contributors:
    Dukes, W.H. (author) / Krivetsky, A. (author)

    Conference:

    SAE Meeting ; 1968 Plastics



    Publication date :

    1968


    Size :

    12 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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