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、疲勞壽命長之優點，目前已廣泛應用於航太工業上。本文主要以實驗之方法探討此一材料在不同疊序時，比較其鑽孔及無鑽孔於不同大小之拉力-拉力疲勞作用下，其殘留強度、殘留勁度及機械性質等。
選用之疊層有十字疊層[0/90]4S與類似均向疊層[0/+45/90/-45]2S，中央鑽孔4mm及無鑽孔試片，分別施以60%與80%不同應力等級之負載進行疲勞實驗；在到達指定的疲勞振次後停止疲勞負載，再進行靜態拉伸實驗，以求取材料之殘留強度與勁度，最後以電子顯微鏡(SEM)觀察複合材料破壞斷面，並探討複合材料的疲勞特性及破壞機制。
實驗之結果得知，極限強度、彈性模數、疲勞強度方面以十字疊之強度大於類似均向疊。中央鑽孔後，破壞皆發生於鑽孔處，並降低複合材料極限強度與疲勞強度值。在受到疲勞作用後，殘留強度值隨所受之疲勞振次之增加而有衰減之趨勢，然而殘留勁度值則較無明顯之變化；這些變化以類似均相疊所受影響較十字疊大。

ABSTRACT

AS-4 carbon fibers reinforced polyetheretherketone (PEEK) composite materials have been widely used in aerospace industry because of longer fatigue life, high specific stiffness and strength. The thesis is aimed to investigate the residual strength, residual stiffness and mechanical properties of thermoplastic AS-4/PEEK composite laminates subjected to tension-tension (T-T) cyclic loading at room temperature.
We adopt modified diaphragm forming method by controlling temperature, pressure, vacuum and time conditions according to the obtained beast curing process to form composite laminates of low crystallinity, transcrystallinity and good fiber / matrix interfaces. Two common type of laminates are used, such as cross-ply [0/90]4S and quasi-isotropic [0/+45/90/-45]2S. Static tension test is performed to measure the elastic modulus and ultimate strength. And T-T fatigue test is conducted with maximum stress of 60% and 80% ultimate strength to find the residual strength and stiffness. Then, through the observation of failure surfaces of composite laminates we understand the failure initiation and mechanism by Scanning Electron Microscope (SEM).
The results of experiment can be concluded as follows. The ultimate strength, elastic modulus and fatigue strength of cross-ply composite laminates are larger than those of quasi-isotropic. As centrally notched, the net area of the specimen is reduced, the ultimate strength and fatigue strength of composite materials are lower. The residual strength, adopted to describe the damage process, is monotonically decreasing with increasing of applied cycles. It is found that the residual strength of cross-ply laminates is larger than that of quasi-isotropic laminates. However, the residual stiffness has little change with increasing of applied cycles.

目 錄

目錄 …………………………………………………………… I
表目錄 ………………………………………………………… IV
圖目錄 ………………………………………………………… VI
中文摘要 ……………………………………………………… XI
ABSTRACT ……………………………………………………… XII
第一章 緒論 …………………………………………………… 1
1-1前言 ……………………………………………………… 1
1-2複合材料概述 …………………………………………… 2
1-3實驗材料簡介 …………………………………………… 3
1-4研究方向 ………………………………………………… 4
1-5文獻回顧 ………………………………………………… 5
1-6組織與章節 ……………………………………………… 6
第二章 實驗工作 ……………………………………………… 8
2-1儀器設備 ………………………………………………… 8
2-2積層板製作 ……………………………………………… 9
2-3試片製作與分組 ………………………………………… 12
2-4拉伸與疲勞實驗 ………………………………………… 13
2-5 SEM實驗 ………………………………………………… 15
第三章 實驗結果 ……………………………………………… 22
3-1拉力實驗 ………………………………………………… 22
3-2疲勞實驗 ………………………………………………… 23
3-3破壞機制觀察 …………………………………………… 27
第四章 分析與討論 …………………………………………… 52
4-1殘留強度的探討 ………………………………………… 52
4-1.1疊序效應之影響 …………………………………… 52
4-1.2負載大小之影響 …………………………………… 53
4-1.3鑽孔效應之影響 …………………………………… 54
4-2殘留勁度的探討 ………………………………………… 55
4-2.1疊序效應之影響 …………………………………… 55
4-2.2負載大小之影響 …………………………………… 55
4-2.3鑽孔效應之影響 …………………………………… 56
4-3破壞模式的探討 ………………………………………… 57
4-3.1十字疊試片 ………………………………………… 57
4-3.2類似均相疊試片 …………………………………… 58
第五章 結論與建議 …………………………………………… 60
5-1結論 ………………………………………………………… 60
5-2建議 ………………………………………………………… 61
5-3未來展望 …………………………………………………… 62
參考文獻 ……………………………………………………… 63

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