摘 要
碳纖維(AS-4)加強材與聚二醚酮(PEEK)基材之熱塑性APC-2複合材料。其具有高勁度比、高強度比、質量輕、疲勞壽命長之優點，抗濕度強、成形的時間短、耐高溫等特性。本文即針對此一材料，中央鑽孔後模擬於高溫模態下承受拉力-拉力之疲勞測試，探討其機械性質與破壞機制。
選用十字疊層 、類似均向疊層 、角疊 參種疊序試片。及APC-2複合材料之Tg溫度為143℃，所以中央鑽孔後溫度參數分別探討於25℃、75℃、100℃、125℃、150℃五種環境溫度下之抗拉實驗及疲勞實驗，求得彈性模數、極限強度、疲勞強度及振次壽命，並建立應力與疲勞振次曲線(S-LogN Curve)，探討複合材料中央鑽孔後在溫度效應下之疲勞特性及破壞機制。
實驗之結果得知，於相同溫度下，極限強度、彈性模數、疲勞強度方面以十字疊之強度值最大，類似均向疊次之，角疊最小。然而角疊之大變形量已超越彈性範圍非為本實驗所預估，必須重新規劃量測儀器再行專門探討。中央鑽孔後，破壞皆產生鑽孔處，並降低複合材料極限強度與疲勞強度值。隨著溫度之提高，極限強度、疲勞強度值及彈性模數值均呈降低之現象。在接近Tg甚而高於Tg溫度時，基材聚二醚酮軟化，使極限強度、彈性模數、疲勞強度降低差距較為明顯。碳纖維與聚二醚酮之間的黏結優劣及結晶程度，均影響APC-2複材之機械性質。

ABSTRACT
PEEK matrix reinforced by carbon fibers as one thermoplastic composite material is studied. Thermoplastic composites have the advantages of high specific stiffness and strength, longer fatigue life, good resistance to moisture absorption and high temperature condition. The thesis is aimed to investigate the mechanical properties and fracture mechanism of the centrally notched AS-4/PEEK composite laminates subjected to tension-tension fatigue loading at elevated temperature.
We use three common types of laminates, such as cross-ply , quasi-isotropic and angle-ply . After centrally notched, we first obtain the base-line data of mechanical properties by tensile tests at five different temperatures, such as 25℃、75℃、100℃、125℃、150℃. Then, the fatigue tests are conducted, we receive the fatigue strength and life and establish the stress-life curves. The fatigue characteristics and fracture mechanism of a centrally notched composite laminate at elevated temperature are also recorded and observed.
The empirical results can be concluded as follows. At the same temperature, the laminate of cross-ply possesses the largest ultimate strength and fatigue strength, quasi-isotropic the second angle-ply the smallest. As for the elastic modulus, the laminate of cross-ply is larger than that of quasi-isotropic. However, the large strain of angle-ply is within the plastic range that is out of the limit of the study. Thus, a further investigation is needed for angle-ply laminates alone. After centrally notched, the net area is reduced of the specimen, and then the elastic modulus is raised and the ultimate strength and fatigue strength of composite materials are lower. As the temperature increasing, the ultimate strength, fatigue strength and elastic modulus are all decreasing.

目 錄

目錄 ……………………………………………………… I
表目錄…………………………………………………… III
圖目錄…………………………………………………… V
摘要……………………………………………………… IX
英文摘要………………………………………………… X
第一章 …………………………………………………… 1
1-1 前言 ……………………………………………… 1
1-2 複合材料概述 ……………………………………… 1
1-3 研究方向 …………………………………………… 2
1-4 文獻回顧 …………………………………………… 3
1-5 組織與章節 ………………………………………… 5
第二章 實驗部分………………………………………… 7
2-1 材料之機械性質 …………………………………… 7
2-2 儀器設備 …………………………………………… 8
2-3 試片製作與分組 …………………………………… 8
2-4 實驗過程與步驟 …………………………………… 11
第三章 實驗結果………………………………………… 21
3-1 拉力實驗 …………………………………………… 21
3-2 疲勞實驗 …………………………………………… 22
3-3 破壞模式 …………………………………………… 27
第四章 分析與討論……………………………………… 52
4-1 複合材料鑽孔後對強度影響 ……………………… 52
4-1.1在極限強度方面 ………………………………… 52
4-1.2在疲勞強度方面 ………………………………… 53
4-2 複材鑽孔後彈性模數之影響 ……………………… 55
4-3 破壞模式之探討 …………………………………… 57
第五章 結論與建議 …………………………………… 59
5-1 結論 ………………………………………………… 59
5-2 建議 ………………………………………………… 59
5-3 未來發展 …………………………………………… 60
參考文獻 ………………………………………………… 62

表 目 錄

表1-1複合材料單向疊層之主要材料性質 ……………… 6
表3-1複材中央鑽孔4mmψ十字疊、類似均向疊不同溫度中之拉伸實驗值 …………………………………………… 29
表3-2複材無鑽孔十字疊、類似均向疊於不同溫度中之拉伸實驗值 ………………………………………………. 29
表3-3複材中央鑽孔4mmψ疲勞實驗前測得之彈性模數(GPa) … 29
表3-4複材無鑽孔疲勞實驗前測得之彈性模數(GPa) … 29
表3-5常溫下中央鑽孔4mmψ十字疊與類似均向疊試片施加應力與疲勞振次實驗值 ………………………………. 32
表3-6常溫下無鑽孔十字疊與類似均向疊試片施加應力與疲勞振次實驗值 ………………………………………. 32
表3-7中央鑽孔4mmψ十字疊試片施加應力與疲勞振次實驗值…33
表3-8無鑽孔十字疊試片施加應力與疲勞振次實驗值 …34
表3-9中央鑽孔4mmψ類似均向疊試片施加應力與疲勞振次實驗值 …………………………………………………. 35
表3-10無鑽孔類似均向疊試片施加應力與疲勞振次實驗值 …. 36
表3-11複材中央鑽孔4mmψ疲勞實驗後之應用統計曲線擬合之結果 ………………………………………………… 37
表3-12中央鑽孔4mmψ之十字疊及類似均向疊之疲勞強度與極限強度之比值 ……………………………………… 37
表3-13無鑽孔之十字疊及類似均向疊之疲勞強度與極限強度之比值 ………………………………………………… 37

圖 目 錄

圖2-1將積層板與銅板置於在熱壓機之上下模間 …… 13
圖2-2切割試片用之水冷式鑽石切割機 ……………… 13
圖2-3直立式高速鑽孔機 ……………………………… 14
圖2-4 MTS-810材料試驗機及高溫爐設備 …………… 14
圖2-5 MTS-651高溫爐 ………………………………… 15
圖2-6 MTS-634.11F-25高溫應變指示計 ……………… 15
圖2-7十字疊 積層板各層分解圖 …………………. 16
圖2-8類似均向疊 積層板各層分解圖 ………. 16
圖2-9 角疊積層板各層分解圖 ………………………… 16
圖2-10將Polyimide玻璃紙置於熱壓機上下模之間 …. 17
圖2-11熱壓機上下模閉合時之情形 …………………. 17
圖2-12(a)積層板成形之溫度與時間之關係圖 ……… 18
圖2-12(b)積層板成形氮氣加壓與時間之關係圖 …… 18
圖2-13(a)高溫壓製成形後之積層板 ………………… 19
圖2-13(b)積層板之尺寸 ……………………………… 19
圖2-14複合材料試片圖 ………………………………. 20
圖2-15複合材料試片之尺寸 …………………………. 20
圖3-1複材中央鑽孔4mmψ及無鑽孔十字疊之極限應力與溫度關係圖 ………………………………………………. 30
圖3-2複材中央鑽孔4mmψ及無鑽孔類似均向疊之極限應力與溫度關係圖 …………………………………………. 30
圖3-3複材中央鑽孔4mmψ及無鑽孔十字疊之彈性模數與溫度關係圖 ………………………………………………… 31
圖3-4複材中央鑽孔4mmψ及無鑽孔類似均向疊之彈性模數與溫度關係圖 …………………………………………… 31
圖3-5中央鑽孔4mmψ十字疊於溫度75℃之S-log N曲線擬合圖 ……………………………………………………… 38
圖3-6中央鑽孔4mmψ十字疊於溫度100℃之S-log N曲線擬合圖 ……………………………………………………… 38
圖3-7中央鑽孔4mmψ十字疊於溫度125℃之S-log N曲線擬合圖 ……………………………………………………… 39
圖3-8中央鑽孔4mmψ十字疊於溫度150℃之S-log N曲線擬合圖 ……………………………………………………… 39
圖3-9中央鑽孔十字疊分別於25℃、75℃、100℃、125℃
、150℃中之S-log N曲線圖 …………………………… 40
圖3-10無鑽孔十字疊分別於25℃、75℃、100℃、125℃、150℃中之S-log N曲線圖 …………………………… 40
圖3-11中央鑽孔十字疊分別於25℃、75℃、100℃、125℃
、150℃中之Stress Level-log N曲線圖 …………… 41
圖3-12無鑽孔十字疊分別於25℃、75℃、100℃、125℃、150℃中之Stress Level-log N曲線圖 ……………… 41
圖3-13中央鑽孔4mmψ類似均向疊試片於溫度75℃之S-log N曲線擬合圖 ……………………………………… 42
圖3-14中央鑽孔4mmψ類似均向疊試片於溫度100℃之S-log N曲線擬合圖 ……………………………………… 42
圖3-15中央鑽孔4mmψ類似均向疊試片於溫度125℃之S-log N曲線擬合圖 ……………………………………… 43
圖3-16中央鑽孔4mmψ類似均向疊試片於溫度150℃之S-log N曲線擬合圖 ……………………………………… 43
圖3-17中央鑽孔類似均向疊分別於25℃、75℃、100℃、125℃、150℃中之S-log N曲線圖 …………………… 44
圖3-18無鑽孔類似均向疊分別於25℃、75℃、100℃、125℃、150℃中之S-log N曲線圖 …………………… 44
圖3-19中央鑽孔類似均向疊分別於25℃、75℃、100℃、125℃、150℃中之Stress Level-log N曲線圖 ……… 45
圖3-20無鑽孔類似均向疊分別於25℃、75℃、100℃、125
℃、150℃中之Stress Level-log N曲線圖 ………… 45
圖3-21複材中央鑽孔4mmψ及無鑽孔十字疊之疲勞負載與溫度的關係 ……………………………………………… 46
圖3-22複材中央鑽孔4mmψ及無鑽孔類似均向疊之疲勞負載與溫度的關係 ………………………………………… 46
圖3-23複材中央鑽孔4mmψ及無鑽孔十字疊之(疲勞強度/極限強度)比值與溫度的關係 ………………………… 47
圖3-24複材中央鑽孔4mmψ及無鑽孔類似均向疊之(疲勞強度/極限強度)比值與溫度的關係 ……………………… 47
圖3-25中央鑽孔4mmψ之十字疊試片由左而右溫度分別為75℃、100℃、125℃、150℃之破壞模式之正視圖 … 48
圖3-26中央鑽孔4mmψ之十字疊試片由左而右溫度分別為75℃、100℃、125℃、150℃之破壞模式之斷面圖 … 48
圖3-27中央鑽孔4mmψ之類似均相疊試片由左而右溫度分別為75℃、100℃、125℃、150℃之破壞模式之正視圖.49
圖3-28中央鑽孔4mmψ之類似均相疊試片由左而右溫度分別為75℃、100℃、125℃、150℃之破壞模式之斷面圖.49
圖3-29左邊為中央鑽孔4mmψ角疊之標準試片、中間為疲勞實驗後、右邊為拉伸實驗後 ………………………… 50
圖3-30左邊為無鑽孔角疊之標準試片、中間為疲勞實驗後
、右邊為拉伸實驗後 …………………………………. 50
圖3-31施力負載與複合材料碳纖維方向示意圖 ……. 51

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