A new approach in the design of aerospace vehicles was recently introduced by NASA and Boeing researchers to meet the new challenges in aviation. This innovative configuration is called pultruded rod stitched efficient unitized structure, a stitched carbon–epoxy material system that offers the opportunity for designing stiffer, lower weight, and more cost-efficient aircraft by eliminating fasteners and incorporating damage-tolerance concepts. Aside from superior structural performance and low-cost manufacturing methods, this configuration must also demonstrate advanced aeroelastic behavior to be fully implemented in commercial aircraft. A preliminary wing study of a general aviation aircraft that embodies pultruded rod stitched efficient unitized structure technology is presented in this paper, which will be compared with the structural, dynamic, and aeroelastic behavior of the original metallic wing model. The study showed that the presence of pultruded rod stitched efficient unitized structure panels leads to decreased deformations in static and aeroelastic analyses, higher natural frequencies and flutter speeds, and improved crashworthiness. Weight considerations are also presented to substantiate the comparison between pultruded rod stitched efficient unitized structure and metallic configuration.


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    Titel :

    Preliminary Wing Study of General Aviation Aircraft with Stitched Composite Panels



    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Lokalklassifikation TIB:    770/7040



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    Energy Absorption in Stitched Composite Sandwich Panels

    Tomblin, J. S. / Raju, K. S. | SAE Technical Papers | 1998