本文考慮具厚度變化的複合材料夾心板模型以取代機翼結構，並利用Nastran有限元素軟體配合SolidWorks對該模型進行建模，然後採用Nastran空氣彈性模組進行顫振與發散分析。文中探討4疊層之複材疊層板的疊層配置與顫振或發散速度的關係，角度僅考慮90, -45, 45, 0四種角度且可重複，疊層排序則為任意排列組合。文中除了任意排列組合的疊層排序外將新增不同限制條件，如角度不重複、角度至多重複2, 3次、角度必須重複2, 3次等。結果顯示在特定纖維角度下會有較佳的顫振與發散結果。

This paper considers a composite sandwich beam which has variable thickness of cross section to replace complicated wing structure. The model is created by Nastran and SolidWorks and simulated by Nastran’s aeroelasticity module in order to get the flutter and divergence speed. This paper will discuss the relation between flutter or divergence and the composite arrangement which has 4 layers. The fiber angle here only considers 4 angles including 90, -45, 45, 0 which allow angle repeats and the arrangement are arbitrary permutation. The arrangement will apply different constraints like inadmissible repeat angle in order to simply analyze the data. The result show that composite wing has their best or worst fiber arrangement for flutter or divergence.

[1] N. D. Ham, M. I. Young, “Limit cycle torsional motion of helicopter blades due to stall”, Journal of Sound and Vibration, vol 4, Issue 3, pp. 431-432, 1966
[2] Wilmer H. Reed, “Propeller-rotor whirl flutter: A state-of-the-art review”, Journal of Sound and Vibration, vol 4, Issue 3, pp. 526-530, 1966
[3] K. N. Koo, I. Lee, “Aeroelastic behavior of a composite plate wing with structural damping”, Computers & Structures, vol 50, Issue 2, pp. 167-176, 1994
[4] B. V. Vijaya, S. Durvasula, “Supersonic flutter of composite skin panels of repeated-sublaminate layup”, Computers & Structures, vol 41, Issue 2, pp. 121-135, 1998
[5] Hwu, C.; Tsai, Z. S. 2002 “Aeroelastic divergence of stiffened composite multicell wing structures”, Journal of Aircraft, vol.39, no. 2, pp.242-251., 2002
[6] M. Kameyama, H. Fukunaga, “Optimum design of composite plate wings for aeroelastic characteristics using lamination parameters”, Computers and Structures, vol 85, pp.213-224 , 2007
[7] H. Ghiasi, D. Pasini, L. Lessard, “Optimum stacking sequence design of composite materials Part I: Constant stiffness design”, Composite Structures, vol 90, pp.1-11 , 2009
[8] H. Ghiasi, K. Fayazbakhsh, D. Pasini, L. Lessard, “Optimum stacking sequence design of composite materials Part II: Variable stiffness design”, vol 93, pp.1-13 , 2010
[9] H. Haddadpour, Z. Zamani, “Curvilinear fiber optimization tools for aeroelastic design of composite wings”, Journal of Fluids and Structures, vol 33, pp. 180-190, 2012
[10] Z. Wang, Z. Wan, Rainer M.J. Groh, X. Wang, “Aeroelastic and local buckling optimisation of a variable-angle-tow composite wing-box structure”, Composite Structures, vol 258, 2021
[11] “Aeroelastic analysis user’s guide”, MSC. Nastran Version 68, MSC. Software Corporation.
[12] “Quick Reference Guide”, MSC. Nastran, MSC. Software Corporation.
[13] Bryan E., Jose A., Rivera Jr., and Moses G. “An Experimental Study of Tip Shape Effects on the Flutter of Aft-Swept, Flat-Plate Win”, NASA Technical Memorandum 4180, 1990
[14] Hwu C., “Anisotropic elastic plates” Springer, New York, 2010.