The problem of metal-composite wing structural optimization is discussed and a strategy is presented. Topology optimization method is applied to provide load transferring path of structure for concept design. Size, shape and other optimization method are used to provide detailed design for individual components. A three-phase optimization method is discussed for fiber reinforced composite laminate skin. Optimal parameters include ply angle, percentage, thickness, layer shape and sequence. The design of laminate for ease of manufacture is based on a set of manufacturing constraints. This paper deals with a total optimal design solution for aileron structure of an aircraft. The result satisfies all the requirements of strength and stability, and has obvious effect of weight loss.


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    Title :

    Structural Optimization Design of an Aircraft Metal-Composite Wing


    Contributors:


    Publication date :

    2013


    Size :

    5 Seiten




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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