本研究對含有上下面板之鋁合金蜂巢板，利用四點彎矩實驗研究不同面板厚度、蜂巢高度、蜂巢內徑等參數對蜂巢結構靜態強度及疲勞壽命之影響；並藉由與實驗結果比對找出最適合之疲勞壽命預測模型。本研究首先對不同參數試片進行靜態彎矩實驗，觀察其在承受靜態負載時之破壞型式，得到其靜態極限負荷並記錄局部之變形/應變數據，作為建立比對有限元素模型正確性之依據。由靜態實驗結果顯示蜂巢結構相對密度越高時、蜂巢結構厚度越大時，蜂巢板靜態強度越高；而面板厚度對蜂巢板靜態強度沒有顯著的影響。疲勞實驗將設定六個負荷階進行試驗，負荷階之大小分別為其靜態極限強度之40%、35%、30%、25%、20%及15%。透過疲勞實驗將可得到各不同參數試片之負荷-壽命曲線，並藉此獲得七種參數蜂巢板在承受彎矩負載下之疲勞性質。由疲勞實驗結果顯示：蜂巢結構高度越高、相對密度越大時，蜂巢板的疲勞強度越高；而面板厚度對於蜂巢板強度並無顯著之影響。本研究在疲勞壽命預測部分利用外力負載參數及有限元素分析對蜂巢板的疲勞強度及破壞起始位置進行評估。本研究分別利用全域模型及局部模型對於蜂巢板試片之疲勞壽命進行預測。由比對結果顯示，全域模型參數中考量正規化之外力負荷對於壽命預測有較好之結果。局部參數中考量最大剝離應力參數對於蜂巢板試片的壽命及破壞起始位置預測有較好之結果。

The static and fatigue strength for Aluminum honeycomb sandwich plates under four-point bending were experimentally analyzed in the research. The thickness of face sheet; the height and the size of honeycomb cell were considered as the study parameters in the experimental program. Totally seven different kinds of specimens were designed to study the effect of these parameters on the strength of honeycomb sandwich plates. In the static tests, the ultimate strength, local out-of-plane deformation, and in-plane strain on the face sheet of specimens were measured and recorded. Furthermore, the failure mode and was also observed during the tests. The experimental results of deformation and strain was used to evaluate the accuracy of finite element simulation. The experimental results of static strength was compared with the analytical solutions. In the fatigue tests, five loading levels were chosen as the 40%, 35 %, 30%, 25%, 20% and 15% of the static ultimate strength for each specimens. The loading-life curve were established from the fatigue tests to study the effect of these parameters on the fatigue strength of honeycomb sandwich plates. Global Parameters; such as bending stress, shear stress and normalized load drops were used to predict the fatigue life of all type specimens. The predicted results show that the normalized load drops provide better evaluation than the two parameters do. The local von Mises stress, peeling stress, shear stress and the combination of peeling stress and shear stress were used as the prediction parameters to evaluate the bending fatigue life of honeycomb sandwich plates. The prediction parameter of peeling stress is found to give better prediction results of crack initiation locations and fatigue life than the other parameters do. Finite element analysis was employed to obtain the critical positions for crack initiation and the local stress/strain behavior under cyclic bending loading was used to predict the fatigue life.

中文摘要 I
英文摘要 II
目 錄 IV
表目錄 VI
圖目錄 VII
符號說明 XI
第一章 序論 1
1-1 引言 1
1-2 研究內容 2
1-3 本文架構 3
第二章 文獻回顧 4
第三章 實驗內容與程序 8
3-1 研究對象 8
3-2 儀器介紹 9
3-3 實驗步驟與內容 11
3-3-1四點彎矩靜態實驗 11
3-3-2四點彎矩疲勞實驗 12
第四章 鋁合金蜂巢板之靜態強度與疲勞壽命預測理論分析 23
4-1 蜂巢結構靜態極限強度之理論分析 23
4-2 蜂巢結構疲勞壽命預測理論 23
4-2-1 利用鋁合金蜂巢板之全域參數預測疲勞壽命 24
4-2-2 利用鋁合金蜂巢板之局部參數預測疲勞壽命 27
第五章 有限元素分析 33
5-1 有限元素模型介紹 33
5-1-1 材料性質 34
5-1-2 邊界條件與負載條件 35
第六章 結果與討論 48
6-1 鋁合金蜂巢板之靜態實驗及強度預測結果 48
6-2 蜂巢板試片之疲勞實驗及預測結果 49
6-2-1 外力負載對疲勞壽命之影響 50
6-2-2 全域參數之疲勞壽命預測結果 50
6-2-3 局部參數之疲勞壽命預測結果 52
6-2-4 局部參數之破壞起始位置預測結果 53
第七章 結 論 109
參考文獻 111

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