臺灣博碩士論文加值系統

複合材料結構具備重量輕、強度高等優點廣泛於工業中應用，因此許多金屬產品漸漸轉向複合材料發展，但由於其昂貴的成本，因此為最大程度的發揮其優勢，結構外型的設計與開發流程顯得極為重要。因此，本篇論文將建立一套完整的複合材料零件設計流程，解決複合材料零件設計和製造挑戰，並運用拓樸學重新設計定翼無人機機翼內部碳纖維管件之形狀，找出在不同受力狀況下之管件最佳形狀，以解決機翼震盪問題，最後將比較三種異形碳纖維管件，抗彎曲與扭矩的能力。透複合材料等效性質轉換公式，得出類均質疊層之複材在承受不同力量時，其轉換後之性質接近鋁合金，使用電腦輔助分析軟體ANSYS進行鋁合金零件的形狀拓樸分析，找出最佳化之管件形狀，修模軟體為Spaceclaim，後續將鋁合金管件轉換成複合材料進行疊層設計，比較其剛性是否符合需求，並針對零件的外型、製造的可行性以及成本來做為考量，選擇適合之成型方法來製造，透過複合材料疊層設計軟體進行疊層厚度、角度、最佳化等設計，最後使用CATIA將複合材料疊層展開進行零件製造。本篇論文所設計出之流程，可用於複合材料零件設計時的基礎，可有效降低產品開發時間與成本；並由拓樸最佳化分析得出，當管件承受扭矩與彎矩時，最佳形狀為不等厚異形橢圓管件，且其重量比、剛性比以及安全係數皆優於等厚圓管及不等厚異型圓管可作為無人機機翼最佳化之管件型狀之依據。

Composite structures are widely used in industry due to their light weight and high strength. Therefore, many metal products are gradually turned to composite materials for development. However, due to its high cost, in order to maximize its advantages, the design and development process of the structural appearance is extremely important. Therefore, this paper will establish a complete composite part design process to solve the design and manufacturing challenges of composite parts, and use topology to redesign the shape of the carbon fiber tube inside the wing of a fixed-wing UAV to find out the composite part design and manufacturing challenges. Optimal shape addresses airfoil vibration by deflecting the tubes under stress. Finally, the bending and torsion capabilities of three special-shaped carbon fiber pipe fittings are compared. Through the equivalent performance conversion formula of composite materials, it is concluded that the performance of composite materials with similar homogeneous laminates is close to that of aluminum alloy when subjected to different forces. The shape and topology of aluminum alloy parts are analyzed by computer aided analysis software ANSYS. Find the best shape of the pipe fittings, use Spaceclaim as the modeling software, then convert the aluminum alloy pipe fittings to composite materials for laminated design, compare whether the rigidity meets the requirements, and make adjustments based on appearance, manufacturing feasibility and performance. Considering the cost of the part, choose the appropriate molding method for manufacturing, use the composite material laminate design software to design the thickness, angle, optimization, etc. of the laminate, and finally use CATIA to develop the composite material laminate manufacturing of the part. The process designed in this paper can be used as the basis for the design of composite parts, which can effectively reduce product development time and cost; topology optimization analysis shows that when the pipeline is subjected to torque and bending moment, the best shape is a special-shaped oval tube with different thickness, and its weight ratio , Stiffness ratio and safety factor are good. It is superior to equal-thickness round pipes and unequal-thickness special-shaped round pipes. It can be used as the basis for UAV wing tube shape optimization.

摘要..........i
Abstract ..........ii
誌謝.......... iv
目錄.......... v
表目錄 ..........viii
圖目錄 ..........ix
第一章 緒論.......... 1
1.1 研究背景.......... 1
1.2 研究目的.......... 2
1.3 研究方法 ..........3
第二章 文獻回顧 ..........4
2.1 拓樸優化基礎理論.......... 4
2.1.1 拓樸優化方法.......... 6
2.1.2 均質化法(HM) ..........6
2.1.3 密度變量法(SIMP).......... 7
2.1.4 漸進結構最佳化法(ESO).......... 8
2.2 拓樸最佳化 ..........8
2.2.1 等效應力(Equivalent Stress).......... 9
2.2.2 應力移除準則.......... 9
2.2.3 應變能準則.......... 10
2.3 等效性質轉換 ..........12
2.4 複合材料成型技術 ..........15
2.5 Tsai-Hill 破壞理論.......... 21
第三章 研究方法.......... 23
3.1 零件設計流程 ..........23
3.2 幾何模型 ..........24
3.3 電腦輔助工程模擬分析 ..........25
3.3.1 材料性質 ..........26
3.3.2 邊界條件設定.......... 28
3.3.3 修建網格模型 ..........32
3.4 金屬結構轉換複合材料設計概念 ..........37
3.4.1 纖維連續 ..........37
3.4.2 疊層對稱與平衡 ..........37
3.4.3 纖維布的展開 ..........39
3.5 疊層設計.......... 40
3.6 疊層角度最佳化.......... 42
3.7 疊層展開方法 ..........43
3.8 不同形狀之管件 ..........44
第四章 結果與討論 ..........46
4.1 第一次拓樸最佳化 ..........46
4.1.1 CASE 1_結構受扭力後第一次拓樸 ..........46
4.1.2 CASE 2_結構受彎矩後第一次拓樸 ..........48
4.1.3 CASE 3_結構受扭力與彎矩後第一次拓樸.......... 49
4.2 第二次拓樸最佳化 ..........51
4.2.1 CASE 1_結構受扭力後第二次拓樸.......... 51
4.2.2 CASE 2_結構受彎矩後第二次拓樸 ..........53
4.2.3 CASE 3_結構受扭力與彎矩後第二次拓樸.......... 54
4.3 鋁合金結構分析 ..........56
4.3.1 CASE 1_鋁合金結構受扭力後結構分析 ..........56
4.3.2 CASE 2_鋁合金結構受彎矩後結構分析 ..........57
4.3.3 CASE 3_鋁合金結構受扭力與彎矩後結構分析 ..........58
4.4 碳纖維結構分析 ..........59
4.4.1 CASE 1_碳纖維結構受扭力後結構分析.......... 59
4.4.2 CASE 2_碳纖維結構受彎矩後結構分析 ..........62
4.4.3 CASE 3_碳纖維結構受扭力與彎矩後結構分析 ..........64
4.5 結構輕量化比較.......... 66
4.5.1 CASE 1_零件拓樸後轉換碳纖維 ..........66
4.5.2 CASE 2_零件拓樸後轉換碳纖維 ..........67
4.5.3 CASE 3_零件拓樸後轉換碳纖維.......... 68
4.6 疊層角度最佳化 ..........69
4.6.1 CASE 1_等厚中空圓管角度最佳化.......... 69
4.6.2 CASE 2_不等厚中空工型管角度最佳化.......... 69
4.6.3 CASE 3_不等厚異形橢圓管角度最佳化.......... 70
4.7 碳纖維布展開 ..........71
4.7.1 CASE 1_等厚中空圓管纖維布展開 ..........71
4.7.2 CASE 2_不等厚中空工型管纖維布展開.......... 71
4.7.3 CASE 3_不等厚異形橢圓管纖維布展開.......... 72
4.8 不同形狀管件之受力.......... 72
4.8.1 Model 1_碳纖維等厚圓管.......... 72
4.8.2 Model 2_碳纖維不等厚異型橢圓管 ..........74
4.8.3 Model 3_碳纖維不等厚異型圓管 ..........76
4.8.4 拓樸最佳化之管件形狀驗證 ..........77
第五章 結論與未來展望.......... 78
5.1 結論 ..........78
5.2 未來展望.......... 79
參考文獻.......... 80
Extended Abstract.......... 82
Abstract.......... 82

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