複合材料在無人飛行載具（UAV）設計中具有重要作用，提供理想的強度和輕量化特性，從而推動飛機在性能和經濟性方面的顯著進展。
本論文旨在評估竹纖維複合材料在機翼蒙皮材料中的適用性，以提升UAV性能的潛在機會，本研究使用Creo Parametric軟體建立由蒙皮、泡沫芯材組成的機翼結構有限元素模型，並利用ANSYS軟體設定蒙皮材質分別為竹纖維複合材料（ALK-BF/Epoxy）、碳纖維複合材料（CRFP）和玻璃纖維複合材料（GRFP），機翼芯材材質設定為硬質泡沫芯材，複材疊層按照[0°/0°/0°]、[0°/45°/0°]、[0°/90°/0°] 的角度堆疊，並於機翼上設定適當的飛行負載，分析三種複材機翼在變形量和最大主應力的表現後，其結果顯示竹纖維複材在重量、總變形量及最大主應力方面均在合理範圍內，因此驗證了竹纖維複材可運用於小型UAV機翼，並在結構性能方面表現出良好的潛力，具有作為高性能材料的應用前景。

Composites play an important role in the design of unmanned aerial vehicles (UAVs), providing desirable strength and lightweight properties that drive significant advances in aircraft performance and economics.
This paper aims to evaluate the applicability of bamboo fiber composite materials in wing skin materials to improve the potential opportunities of UAV performance. This study uses Creo Parametric software to build a composite structure consisting of skin and foam core layers. Finite element model of the wing structure, and use ANSYS software to set the skin material to bamboo fiber composite material (ALK-BF/Epoxy), carbon fiber composite material (CRFP) and glass fiber composite material (GRFP), and the wing core material is set to rigid foam core material. The composite laminates are stacked at the angles of [0°/0°/0°], [0°/45°/0°], [0°/90°/0°] and appropriate angles are set on the wing. Flight load. After analyzing the performance of three types of composite wings in terms of deformation and maximum principal stress, the results show that the weight, total deformation and maximum principal stress of bamboo fiber composites are all within a reasonable range. Therefore, it is verified that bamboo fiber composite materials can be applied to small UAV wings, show good potential in terms of structural performance, and have application prospects as high-performance materials.

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