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Flutter Analysis of a supersonic composite AirFoil skin by using the Differential Quadrature Method

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Mechanics of Composite Materials Aims and scope

The differential quadrature method is extended to deal with an aeroelastic problem. A structural model is presented based on Hamilton’s principle, and the piston theory is used for modeling supersonic aerodynamic loads. A solution for the flutter of a composite wing skin is obtained by using the differential quadrature method. The validity of this method is confirmed by comparing its results with FEM solutions for the natural frequencies and flutter speed. Then, a detailed parametric study is carried out to examine the influence of the thickness, area, ply-angle, and aspect ratio of composite wings skins on their supersonic flutter behavior. It is shown that the flutter speed of a composite wing skin strongly depends on the area, thickness, ply angle, and aspect ratio of the structure.

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Acknowledgments

The authors are grateful for the support from the graduate student scientific innovation foundation of the National University of Defense Technology (No. B120107).

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Authors and Affiliations

  1. College of Aerospace and Material Engineering, National University of Defense Technology, Changsha, Hunan, P. R. China, 410073

    Yaobin Niu, Zhongwei Wang & Weihua Zhang

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  1. Yaobin Niu
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  2. Zhongwei Wang
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  3. Weihua Zhang
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Correspondence to Yaobin Niu.

Additional information

Russian translation published in Mekhanika Kompozitnykh Materialov, Vol. 48, No. 5, pp. 793-806 , September-October, 2012.

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Niu, Y., Wang, Z. & Zhang, W. Flutter Analysis of a supersonic composite AirFoil skin by using the Differential Quadrature Method. Mech Compos Mater 48, 547–558 (2012). https://doi.org/10.1007/s11029-012-9299-x

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  • DOI: https://doi.org/10.1007/s11029-012-9299-x

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