The nonlinear stability analysis of the short box, the long box and the whole wing structure were compared by MARC2003 nonlinear finite element calculation software. The results indicated they were not appropriate to substitute the important part for the whole structure and use the node displacements of the linear calculation as the boundary conditions of the nonlinear analysis. This technique should not be used for the stability design. By comparing the differences of the deflection and the torsion angle between the linear and nonlinear analysis, it was concluded that the nonlinearity seldom influenced the deflection whereas it could remarkably influence the torsion angle. In conclusion, the nonlinear impact must be considered in the torsion stiffness and aeroelastic designs of the wing.
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References
An Y. (2007).Research of design optimization and stability analysis of composite shell structure. Xi'an, Northwestern Polytechnical University: 1–86 [in Chinese].
Barski M. (2006). Optimal design of shells against buckling subjected to combined loadings. Structural and Multidisciplinary Optimization, (31): 146–154.
Chen G. (2004). The foundation of aeroelastic design. Beijing: Beihang University Press, 1–200 [in Chinese].
Crisfield M.A. (1997). Nonlinear finite element analysis of solids and structures. Advanced topics, Vol. 2. UK, Wiley: 1–150.
Ling D. and Xu X. (2004). Nonlinear FEM and program. Hangzhou, Press of ZJU: 1–5 [in Chinese].
Satoru S. and Minsu J. (2008). Evaluation of short-term stability for sea-wall structure at Kobe Airport. (12): 26–31.
Shao X., Yue Z., Zhou L., et al. (2006). Study of stability of moderately thick composite laminates under axial compression loading and shear loading. Journal of Mechanical Strength, 28(5): 716–720 [in Chinese].
Teters G. (2007). Multicriteria optimization of a rectangular composite plate subjected to longitudinal thermal stresses and buckling in shear loading. Mechanics of Composite Materials, (1): 45–51.
Zhou C. (1997). Elastoplastic and stability theory of the thin shell. Beijing: National Defence Industry Press: 1–152 [in Chinese].
Zhao X., Liu G. R. and Dai K. Y. (2008). Geometric nonlinear analysis of plates and cylindrical shells via a linearly conforming radial point interpolation method. Computational Mechanics, (4): 41–49.
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Liang, K., Sun, Q. (2009). Research on the Difference between the Linear and Nonlinear Analysis of a Wing Structure. In: Yuan, Y., Cui, J., Mang, H.A. (eds) Computational Structural Engineering. Springer, Dordrecht. https://doi.org/10.1007/978-90-481-2822-8_18
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DOI: https://doi.org/10.1007/978-90-481-2822-8_18
Publisher Name: Springer, Dordrecht
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