Structural features and approach employed in design of high-performance light aircraft stressed to 8 g limit loads; analytical design exercise shows feasibility of constructing primary airframe from fibrous composite materials; results of minimum weight analyses of fluted core and honeycomb core sandwich panels and their use in selection of final sandwich geometry; curves showing variation in elastic properties with changes in fiber orientation angle for typical basic laminate patterns employed in airframe components.


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    Title :

    Design of aircraft utilizing fiberglass reinforced plastic primary structure


    Additional title:

    J Aircraft


    Contributors:
    Noyes, J.V. (author)

    Published in:

    Publication date :

    1966


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






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