飛行器的重量是決定起降距離的關鍵，對於戰鬥機而言，具備短場起降的能力，是評斷優劣的指標之一；且重量的減輕，亦可減少燃油的消耗，降低使用成本。另近年事逢新型高級教練機之研發，如火如荼的進行。而約占飛機重量3~6%的起落架系，要如何在維持結構強度的條件下，達到輕量化的目的是必成為一重要的課題。本研究的目的，在考量利用複合材料具高強度、高剛性、抗腐蝕及輕重量比的特性，以AT-3自強號高級教練機主輪之減震支柱為例，利用包覆的方式將複合材料附加於減震支柱上，以達到輕量化的目的。藉由CAD軟體Inventor執行建模，及有限元素軟體ANSYS Workbench軟體，參考進場時參數，以進行CAE分析。在嘗試多種變量後，利用最大等效應力及蔡-吳破壞準則(Tsai-Wu)，探討破壞情況，並判斷整體設計是否合乎需求。最終發現以0.25mm厚的UD碳纖維布，以[〖45〗^°/〖-45〗^°/0^°/-〖45〗^°/〖90〗^°/〖45〗^°/0^°/├ 〖-45〗^° ]_4 ┤的鋪層方式，結合鋁合金，在不影響強度的條件下，可達到減重需求。

The weight of an aircraft is a key parameter that affects the flight distance between the takeoff and landing. For a fighter, the ability to take off and land in the short field becomes one of the indicators for judging the merits and demerits. In addition, the weight reduction can also reduce the fuel consumption, which further decreases the operation cost. In recent years, the development of new advanced trainer aircraft is in full swing. The landing gear system, which accounts for 3 to 6% weight of the aircraft, is an important issue in terms of maintaining the structural strength and achieving lightweight. Since the composite materials have high strength, rigidity, corrosion resistance, and light weight characteristics, the purpose of this study is to use the cladding method to employ the composite for the shock absorber of the main wheel on the AT-3 advanced trainer. A composite material skin layer is attached to the shock struts with reduced thickness, and the analysis is performed by the CAD software Inventor and the finite element software ANSYS Workbench software by using the approximated external loads. The maximum equivalent stress and Tsai-Wu failure criteria were used to determine whether the overall design meets the requirements for various combinations of composite layups. The design with UD carbon fiber prepregs in a thickness of 0.25 mm and laid up in [〖45〗^°/〖-45〗^°/0^°/-〖45〗^°/〖90〗^°/〖45〗^°/0^°/├ 〖-45〗^° ]_4 ┤ sequence can meet the demand by reducing the total weight while preserving the original strength.

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