Abstract
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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Frediani, A., Quattrone, F., Contini, F. (2012). The Lifting System of a PrandtlPlane, Part 3: Structures Made in Composites. In: Buttazzo, G., Frediani, A. (eds) Variational Analysis and Aerospace Engineering: Mathematical Challenges for Aerospace Design. Springer Optimization and Its Applications(), vol 66. Springer, Boston, MA. https://doi.org/10.1007/978-1-4614-2435-2_11
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DOI: https://doi.org/10.1007/978-1-4614-2435-2_11
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