In the first part of the paper, the solution of the wing structure of a 250-seat PrandtlPlane aircraft made in Aluminium alloy is discussed. The metallic solution is the result of a first-stage optimization process taking available stress, static aeroelasticity and flutter into account. The second stage of the optimization, consisting into a Finite Element analysis of the previous solution, is performed in order to check the reliability design process and to establish a reliable reference solution to be compared with a new one made in composites. In the second part of the present paper, the resulting wing system is designed using Carbon fibres with a proper sequence of laminae in order to obtain a perfectly isotropic material. The solution in composites is accomplished with an F.E. analysis, and the results are compared with the metal structural solution. Weight and stresses distributions are shown, and a comparison between the metal and the composite solution is performed. The weight saving of the solution made in composites appears to be potentially relevant.


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    Title :

    The Lifting System of a PrandtlPlane, Part 3: Structures Made in Composites


    Additional title:

    Springer Optimization


    Contributors:


    Publication date :

    2012-01-01


    Size :

    20 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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