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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    Titel :

    Application of graphite fiber composites to airframe structures


    Weitere Titelangaben:

    SAE -- Paper


    Beteiligte:
    Dukes, W.H. (Autor:in) / Krivetsky, A. (Autor:in)

    Kongress:

    SAE Meeting ; 1968 Plastics



    Erscheinungsdatum :

    1968


    Format / Umfang :

    12 pages


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    The Application of Graphite Fiber Composites to Airframe Structures

    Krivetsky, Alexander / Dukes, Wilfred H. | SAE Technical Papers | 1968


    Application of advanced composites to helicopter airframe structures

    Rich, M. J. / Ridgley, G. F. / Lowry, D. W. | NTRS | 1974


    Application of Composites to Helicopter Airframe and Landing Gear Structures

    M. J. Rich / G. F. Ridgley / D. W. Lowry | NTIS | 1973


    Application of Composites to Helicopter Airframe and Landing Gear Structures

    M. J. Rich / G. F. Ridgley / D. W. Lowry | NTIS | 1973


    Application of composites to helicopter airframe and landing gear structures

    Rich, M. J. / Ridgley, G. F. / Lowry, D. W. | NTRS | 1973