In order to enhance the aeroelastic stability of a tiltrotor aircraft, a structural optimization framework is developed by applying a multi-level optimization approach. Each optimization level is designed to achieve a different purpose; therefore, relevant optimization schemes are selected for each level. Enhancement of the aeroelastic stability is selected as an objective in the upper-level optimization. This is achieved by seeking the optimal structural properties of a composite wing, including its mass, vertical, chordwise, and torsional stiffness. In the upper-level optimization, the response surface method (RSM), is selected. On the other hand, lower-level optimization seeks to determine the local detailed cross-sectional parameters, such as the ply orientation angles and ply thickness, which are relevant to the wing structural properties obtained at the upper-level. To avoid manufacturing difficulties, only a few discrete ply orientation angles and an integral number of plies are considered as constraints. A genetic algorithm is selected as the optimizer at the lower-level. Use of the upper-level optimization causes a 13-18% increase in the flutter speed when compared to the baseline configuration. In the lower-level optimization, the optimization results were obtained considering the resulting failure margin and the location of the shear center.


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    Titel :

    Structural design optimization of a tiltrotor aircraft composite wing to enhance whirl flutter stability


    Weitere Titelangaben:

    Konstruktive Gestaltungsoptimierung eines Kipprotorflügels aus Verbundwerkstoff zur verbesserten Flatterstabilität


    Beteiligte:
    Kim, Taeseong (Autor:in) / Lim, Jaehoon (Autor:in) / Shin, SangJoon (Autor:in) / Kim, Do-Hyung (Autor:in)

    Erschienen in:

    Composite Structures ; 95 ; 283-294


    Erscheinungsdatum :

    2013


    Format / Umfang :

    12 Seiten, 10 Bilder, 11 Tabellen, 35 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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