拓撲最佳化發展至今已行之有年，許多商用有限元素軟體(如：ANSYS)也發展出相關的模組供使用者模擬分析，但目前並非所有元素皆有支援，如：薄殼元素並不適用於此模組，因此欲利用薄殼元素拓撲最佳化複合材料疊層板問題時，商用軟體將不予以進行分析。為了擴展拓撲最佳化的適用範圍，本文前半部份是從師門發展之機翼數學模型出發，並於正向性材料的勁度矩陣中加入兩個設計變數：元素材料密度、疊層纖維排向，考慮數個疊層板加工製造的限制條件，計算出模型剛度矩陣，並以此剛度矩陣所求解之位移量作為目標值進行複材機翼拓撲最佳化設計。
本文後半部份為說明兩種商用軟體應用之方法，目的在於後續驗證及比較複材機翼最佳化之結果，包含：（1） MATLAB最佳化與ANSYS APDL之結合、（2）MATLAB類神經網路與最佳化之結合。並於第五章考慮三種疊層板鋪排方式的數值範例，探討複材機翼拓撲最佳化後，其蒙皮的材料分布情形。

Topology Optimization has been developed for many years. Many commercial finite element software (such as ANSYS) have also developed related modules for users to simulate and analysis, but not all elements are currently supported, such as: shell elements are not suitable for this module. Therefore, commercial software cannot simulate the topology-optimized composite laminate problem through the shell element. In order to expand the scope of application of topology optimization, the first half of this article starts from the mathematical model of the wing developed by our laboratory. Adding two design variables to the stiffness matrix of the Orthotropic Material: I. Topology Design variables, II. Angle design variables, considering constraints of laminated manufacturing, then calculate the model stiffness matrix, and use the displacement calculated by the stiffness matrix as the target to optimize this problem.
The second half of this article will explain the application methods of these two commercial software, including: I. Combination of MATLAB optimization and ANSYS APDL, II. Combination of MATLAB neural network and optimization. The purpose is to verify and compare the results of composite wing optimization. In Chapter 5, numerical examples considering three laminate layout methods, and the material distribution of the skin of the composite wing is discussed.

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