對於複材機翼結構，至今已有許多相關文獻探討，其數學模式的建立，包含用實心樑、疊層樑、箱型樑、平板等複材理論來模擬，而本文將以複材夾心疊層板理論為基礎，延續 Moh and Hwu (1997) 之研究，導出具對稱型正交疊層面板之夾心板，一邊為固定端，另三邊為自由端邊界，受x、y方向負載之挫曲強度數值解，並加以考慮翼剖面外型，使用 NACA2412 之翼剖面函數，再使用MATLAB 軟體撰寫成程式，以及有限元素分析軟體 ANSYS 進行挫曲分析，兩者以做驗證與討論。

Several different structural models have been proposed to study composite wing structures such as isotropic beam model,laminated beam model, box model and plate model. By following the study of Moh and Hwu (1997) on composite sandwich plate, in this thesis we use the Rayleigh-Ritz method to attain the buckling load of composite sandwich plates.With the consideration of the airfoil shape, the results were further extended to composite wing structures. Finally a computer program was coded with MATLAB to conduct the buckling analysis,and the results were compared with those obtained by the finite element software ANSYS.

ANSYS 10.0 Documentation : ANSYS Element Reference.
Ansel C. Ugural.,”Stresses in Plates and Shells”, McGraw-Hill, New York,1999.
Chan, H. C. and Foo, O., “Buckling of Multi-Layer Sandwich Plates by the Finite Strip Method, ” International Journal of Mechanical Science, Vol. 19, 1977, pp. 447-456.
Christensen, R. M., “Mechanics of Composite Materials. ” New York : Wiley,c1979.
Darvizeh M., Darvizeh A., Ansari R. and Sharma C.B., “Buckling Analysis of Generally Laminated Composite Plates (Generalized Differential Quadrature Rules Versus Rayleigh-Ritz Method), ” Composite Stuctures, 63 (2004) 69-74.
Gibson, R.F., “Principles of Composites Material Mechanics”, McGraw-Hill, New York, 2007.
Hwu,C. and Gai H.S., “Vibration Analysis of Composite Wing Structures by a Matrix Form Comprehensive Model,” AIAA Journal, Vol. 41, No. 11, 2003,pp. 2261-2273.
Hwu, C. and Hu, J.S.,“Buckling and Postbuckling of Delaminated Composite Sandwich Beams,”AIAA Journal, Vol. 30, No. 7,July 1992, pp. 1901-1909
Hu, J.S. and Hwu, C., “Free Vibration of Delaminated Composite Sandwich Beams,” AIAA Journal, Vol.33, No.9, pp.1-8, 1995.
Hwu, C. and Tasi, “Aeroelastic Divergence of Stiffened Composite Multicell Wing Structures, ” Journal of Aircraft, Vol. 39, No. 2, pp.242-251, 2002.
Moh, J. S., and Hwu, C., “Optimization for Buckling of Composite Sandwich Plates,”AIAA Journal, Vol.35,No. 5,May 1997, pp. 863-868.
Pearce, T. R. A., and Webber, J. P. H., “Buckling of Sandwich Panels with Laminated Face Plate, ” Aeronautical Quarterly, Vol. 23, May 1972, pp. 148-160.
Rao, K. M., “Buckling Analysis of Anisotropic Sandwich Plates Faced with Fiber Reinforced Plastics,”AIAA Journal, Vol.23, Aug. 1985,pp.1247-1253.
Vinson J.R. and Sierakowski R.L., “The Behavior of Stuctures Composed of
Composite Materials. ”
http://www.boeing.com/commercial/aeromagazine/articles/qtr_4_06/article_0
4_2.html ，波音公司.
李雅榮、羅光閔、黃建樺，“小型潛艇壓力殼挫曲強度之研究”， 中國造船暨輪機工程學刊，Vol.22, No.4, pp.191-199, 2003.
楊榮顯，“工程材料學”，1997.
莫兆松，“複合夾心板挫曲強度最佳化之探討”，碩士論文，成功大學，1994。
蔡仁修，“複板機翼結構之氣彈發散分析”，碩士論文，成功大學，1999。
余孟駿，“複材機翼結構之動態分析”，碩士論文，成功大學，2003。
曾竣，“蜂巢複合材料力學性質之數值分析”，碩士論文，成功大學，2007。