本論文主要目的為探討鈦合金/碳纖維/聚醚醚酮(Ti/APC-2)複材積層板在室溫下承受衝擊後機械性質之變化。
實驗中所使用之試片分別為五層試片[Ti/(0/90)2/Ti]s，以及九層試片[Ti/(0/90)2/Ti /(0/90)2/ Ti]s，其中APC-2之疊序為十字疊(Cross-ply) ，而為了使鈦合金與APC-2疊層之間有良好的黏結力，必須要先對鈦合金施以鉻酸陽極處理，之後以修正隔膜成型法配合升溫固化進行熱壓。實驗採用落重試衝擊試驗，將一沖頭以自由落體之方式衝擊試片，衝擊高度有0.7 m、0.75 m及0.8 m三種，衝擊重量有22公斤及30公斤兩種，衝擊後再經靜態拉伸試驗測量衝擊後積層板的機械性質。
經由實驗結果之分析，APC-2相較於延展性好的鈦合金更容易因衝擊造成斷裂，代表著APC-2其抗衝擊能力較差，也使得纖維在複合材料中扮演加強材、提高材料之強度的能力下降，故造成其抗拉強度下降。而由拉伸試驗數據得知，未承受衝擊之Ti/APC-2複合材料試片其強度皆比受衝擊後之試片來的高，且衝擊效應會造成複合材料之極限強度及彈性模數大幅度的下降，最明顯的衰退分別為五層複材積層板的極限強度下降至未衝擊的29%及九層試片的26%。積層板在經過衝擊後彈性模數皆有大幅度的下降，但五層積層板的殘留性質皆優於九層積層板，意味著並非越厚的積層板經衝擊過後殘留強度越高。

This thesis aims to study the mechanical properties of Ti/APC-2 composite laminates after low velocity impact. Five layers composite laminates [Ti/(0/90)2/Ti]s and nine layers composites laminate [Ti/(0/90)2/Ti]s were tested. APC-2 was stacked according to cross-ply [0/90]2 sequences. To improve the bonding capability between Ti sheets and APC-2, we adopted the chromic acid anodic method after that the modified diaphragm curing process was used to fabricate Ti/APC-2 hybrid composite laminates.
Experimental results were obtained by using drop-weight test with 1mm diameter hemispherical nosed projectile. Three different hights-0.7 m, 0.75 m, 0.8 m and two weights-22 kg, 30 kg were adopted. After impact testing, we used static tensile test to measure the ultimate strengths and elastic modulus.
From the sample after low velocity impact knows that APC-2 is easy to be fracture than Ti, it means APC-2 have worst ability to resist the impact. In addition, the fiber of the reinforcements fracture, causing the mechanical properties of the composite decrease. By studying the tensile test data, we find out that non-impact composite samples has better mechanical properties than samples after impact. Also, impact cause significantly reduce of the mechanical properties, five layers composite sample reduce to 29% of the non-impact sample and nine layers sample reduce to 26%. Although nine layers sample present better ultimate strength without impact than five layers composite, the residual stiffness modulus of nine layers composite is lower than five layers composite after low-velocity impact. The result shows composite materials are not the thicker the better after impact.

目錄
摘要 i
ABSTRACT ii
圖目錄 v
表目錄 vii
1 第一章 緒論 1
1-1 前言 1
1-2 複合材料簡介 1
1-3 研究方向 1
1-4 文獻回顧 2
2 第二章 實驗方法及程序 4
2-1 實驗材料簡介 4
2-1-1 鈦合金 4
2-1-2 碳纖維/聚醚醚酮APC-2(AS-4/PEEK) 4
2-2 實驗流程圖 5
2-3 儀器設備 6
2-4 鈦合金/碳纖維/聚醚醚酮(Ti/APC-2)複材積層板之製程 6
2-4-1 鈦合金處理 6
2-4-2 碳纖維/聚醚醚酮(APC-2)之前處理 7
2-4-3 熱壓製程 7
2-4-4 試片製作與分類 8
2-5 低速衝擊實驗 8
2-6 靜態拉伸實驗 9
2-7 掃描式電子顯微鏡(SEM) 9
3 第三章 實驗結果 20
3-1 鈦合金陽極處理 20
3-2 低速衝擊實驗 20
3-3 靜態拉伸實驗 21
4 第四章 分析與討論 42
4-1 1 複合材料積層板能量吸收理論 42
4-2 複合材料之混和理論 42
4-3 複合材料積層板承受衝擊後之拉伸實驗 43
4-3-1 不同衝擊高度之比較 43
4-3-2 試片觀察與分析 45
5 第五章 結論 51
6 參考文獻 52

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