本研究主要目標為製造鈦合金/碳纖維/聚醚醚酮(Ti/APC-2)十字疊複材積層板試片，並在側邊切割出不同長度之單邊裂縫，探討不同單邊裂縫長度下的機械性質。複材積層板中間是由一層0.55 mm厚的碳纖維/聚醚醚酮(APC-2)預浸布與外側兩層0.5 mm厚的鈦合金黏結而成。其中的碳纖維/聚醚醚酮(APC-2)疊層是由4層有方向性的APC-2依十字疊[0/90]s疊序堆疊而成。而為了使鈦合金板與APC-2疊層之間有良好的黏結力，必須要先對鈦合金板施以鉻酸陽極處理，之後以修正隔膜成型法配合升溫固化進行熱壓，使三層疊序形成鈦合金/碳纖維/聚醚醚酮(Ti/APC-2)十字疊複材積層板，最後將積層板施以放電加工線切割做出不同長度之單邊裂縫，即1.5 mm、3.0 mm、4.5 mm、6.0 mm。而後續之拉伸與疲勞試驗皆是使用MTS 810萬能動態材料試驗機來進行。
在靜態拉伸測試中可以得到複材試片的極限強度等機械性質，接著依照拉伸實驗數據，繪製出個別裂縫長度下的應力與應變關係圖。而在疲勞實驗中，採用的疲勞負載為拉伸-拉伸，應力比為0.1，頻率為5Hz，從中可以得到積層板之疲勞數據，最後將疲勞數據與所施加的負載繪製出複材積層板在不同裂縫長度下的負載與疲勞振次關係圖。
綜觀所有拉伸與疲勞實驗結果之後可以獲得幾點結論：第一，裂縫越長時，其疲勞擬合曲線越趨近直線，且與純碳纖維/聚醚醚酮(APC-2)的疲勞曲線相似；第二，裂縫最短(1.5mm)之試片其疲勞壽命大致皆劣於其他裂縫長度之試片；第三，裂縫越短時，其殘留強度衰退的越快；裂縫越長時，殘留強度衰退的越慢。

The aim of this thesis is to manufacture the single-edged crack specimens of Ti/APC-2 hybrid composite laminates, and investigate their mechanical properties and fatigue characteristics due to tensile and cyclic tests. The Ti/APC-2 laminates were three-layered laminates with one 0.55 mm thick APC-2 lay-ups covered by two 0.5 mm thick Grand 1 titanium alloy sheets. Chromic acid anodic method was adopted to surface treat titanium. APC-2 was stacked according to cross-ply [0/90]s sequences. The chromic acid anodic method can achieve perfectly bonding between titanium sheets and matrix PEEK. The modified diaphragm curing process is used to fabricate Ti/APC-2 hybrid composite laminates. The single-edged cracks cut by Electrical Discharge Machine were 1.5, 3.0, 4.5 and 6.0 mm. The MTS 810 material testing machine was used to conduct all the static tensile tests and fatigue tests.
From static tensile tests, the mechanical properties of cross-ply composite laminates, such as ultimate tensile strength and stiffness were obtained from the stress-strain diagrams plotted by the testing data. And the load-displacement diagrams were plotted for the corresponding single-edged crack laminates. The constant stress amplitude tension-tension cyclic tests were carried out by using load-control mode at a sinusoidal loading wave with frequency of 5Hz and stress ratio R=0.1. From fatigue tests we obtained laminate’s fatigue resistance and the experimental data of applied load vs. cycles were plotted as S-N diagrams for different single-edged cracks.
From the tensile and fatigue test results, the conclusions were summarized as follows. First, when the crack length was longer, the fatigue S-N curve would be more approaching to straight line, and was similar to pure APC-2 fatigue curve. Second, the fatigue life of the shortest crack length was generally worse than other crack length specimen. Finally, the shorter the cracks, the faster residual strength decline; the longer the cracks, the slower residual strength decline.

目錄
摘要 i
ABSTRACT ii
目錄 iii
圖目錄 v
表目錄 viii
1 第一章 緒論 1
1-1 前言 1
1-2 材料簡介 1
1-2-1 複合材料概述 1
1-2-2 鈦合金 2
1-3 研究方向 3
1-4 文獻回顧 3
2 第二章 研究方法與實驗 5
2-1 實驗材料簡介 5
2-1-1 鈦合金 5
2-1-2 碳纖維/聚醚醚酮預浸布APC-2(AS-4/PEEK) 5
2-2 儀器設備 6
2-3 鈦合金/碳纖維/聚醚醚酮(Ti/APC-2)複材積層板之製程 6
2-3-1 鈦合金之前處理 6
2-3-2 碳纖維/聚醚醚酮APC-2之前處理 7
2-3-3 熱壓製程 7
2-3-4 試片切割 8
2-3-5 切割單邊裂縫 8
2-4 靜態拉伸與疲勞試驗 8
2-4-1 常溫靜態拉伸試驗 9
2-4-2 常溫疲勞試驗 9
2-5 掃描式電子顯微鏡(SEM) 9
3 第三章 實驗結果 21
3-1 鈦合金陽極處理 21
3-2 靜態拉伸實驗 21
3-3 疲勞實驗 22
4 第四章 分析與討論 37
4-1 Ti/APC-2複材積層板機械性能探討 37
4-1-1 與混合理論比較 37
4-1-2 極限強度實驗值與混合理論比較 37
4-2 鈦合金/碳纖維/聚醚醚酮十字疊複材積層板破壞韌性KIC探討 38
4-2-1 破壞力學理論KIC值 38
4-2-2 KIC值與混合理論比較 39
4-2-3 破壞力學理論與混合理論比較 39
4-3 鈦合金/碳纖維/聚醚醚酮十字疊複材積層板J Contour Integral之探討 39
4-4 殘留強度之探討 40
4-4-1 裂縫長度對於極限負載之影響 40
4-4-2 裂縫長度對於抗疲勞性之影響 41
4-4-3 殘留強度與裂縫長度之關係 42
4-5 破壞模式之探討 42
4-5-1 破壞過程 42
4-5-2 拉伸破壞： 43
4-5-3 疲勞破壞： 43
5 第五章 結論 61
6 參考文獻 63

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