本實驗主要在探討中央鑽孔鈦金屬/碳纖維/聚醚醚酮奈米複材積層板承受二梯階應力譜之響應及鑽孔效應。試片是使用三層鈦金屬及二層碳纖維/聚醚醚酮組成，並在碳纖維/聚醚醚酮表面均勻噴灑奈米微粒，奈米微粒占總重量的1%，接著碳纖維/聚醚醚酮依十字疊及類似均向疊兩種疊序排放，之後使用改良隔膜成型法熱壓，壓製成試片，再進行切割及鑽孔，鑽孔孔徑為4mm及6mm。
接著在室溫下進行靜態拉伸試驗及疲勞試驗，並將所得之數據取90%σnom及70%σnom進行二階梯應力譜試驗，二階梯應力譜試驗可分成高應力→低應力及低應力→高應力兩種，其中90%σnom為高應力，70%σnom為低應力，首先施加第一階段應力的50%疲勞壽命，接著再施加第二階段應力，直至試片斷裂。
進行完所有實驗後，可得到幾點結論:第一，鑽孔效應對十字疊之影響較大，將未鑽孔試片與鑽孔試片之拉伸數據作比較，可發現鑽孔後十字疊極限負載之強度減少50%左右，類似均向疊極限負載之強度減少30%，且隨著鑽孔孔徑的增加，十字疊及類似均向疊試片之極限負載也越來越接近；第二，十字疊或類似均向疊的中央鑽孔4mm試片和中央鑽孔6mm試片之負載-疲勞振次曲線都很吻合，抗疲勞性質皆差不多，而未鑽孔十字疊試片抗疲勞性質略差於中央鑽孔十字疊試片，未鑽孔類似均向疊試片抗疲勞性質則是優於中央鑽孔類似均向疊試片；第三，在二階梯應力譜試驗中，中央鑽孔類似均向疊試片之平均疲勞壽命較中央鑽孔十字疊試片高，且受鑽孔效應之影響，中央鑽孔4mm試片之平均疲勞壽命皆比中央鑽孔6mm試片高。

The aims of this thesis to investigate the two step loading of Ti/APC-2 hybrid nanocomposite laminates and their notched effect. Ti/APC-2 laminates were composed of three layers of titanium sheets and two layers of APC-2. Nanoparticles SiO2 were dispersed uniformly on the interfaces of APC-2 with the optimal amount of 1 wt %. Then, APC-2 was stacked according to cross-ply [0/90]s and quasi-isotropic [0/45/90/-45] sequences. The modified diaphragm curing process was adopted to fabricate the hybrid panels for minimal impact of production. The panels were cur into samples and drilled an diameter hole in the center with diameters of 4 or 6 mm.
Both tension and fatigue tests were carried out with MTS 810 universal testing machine at room temperature. Also, two-step loading tests include high→low and low→high tests, were conducted. 0.9σnom is denoted as high load and 0.7σnom low load for two-step loading spectrum. In both high→low and low→high step loadings the first step is to do cyclic tests at a half life of the corresponding load, and then finish it due to last step load.
From the received results, some conclusions were made. First, the ultimate load of notched cross-ply samples was reduced about 50% and the notched quasi-isotropic samples reduced about 30% compared to their unnotched counterparts. Second, the S-N curves are very close for both centrally notched samples of diameters 4 mm and 6 mm in cross-ply and quasi-isotropic samples. Third, quasi-isotropic samples had higher average values of cumulative damage than cross-ply samples. Because of notched effect centrally notched samples of diameters 4 mm had higher average values of cumulative damage than centrally notched samples of diameters 6 mm.

摘要 i
ABSTRACT ii
目 錄 iii
圖目錄 v
表目錄 viii

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 奈米材料性質簡介 1
1-2-3 奈米複合材料簡介 2
1-2-4實驗材料簡介 3
1-3研究方向 4
1-4文獻回顧 5
1-5組織與章節 7
第二章 疲勞損傷累積理論 8
2-1疲勞損傷機制 8
2-2疲勞損傷累積理論 8
第三章 實驗設備及方法 10
3-1儀器設備 10
3-2中央鑽孔鈦金屬/碳纖維/聚醚醚酮奈米複材積層板之製程 11
3-2-1鈦金屬之前處理 11
3-2-2 APC-2預浸布之前處理 11
3-2-3熱壓製程 11
3-2-4試片切割及鑽孔 12
3-3拉伸及疲勞試驗 12
3-4二階梯應力譜試驗 13
第四章 實驗結果 22
4-1靜態拉伸試驗 22
4-2疲勞試驗 22
4-3二階梯應力譜試驗 23
4-4試片觀察 23
4-5鈦合金表面處理 24
第五章 分析與討論 49
5-1 鑽孔效應之影響 49
5-1-1拉伸試驗 49
5-1-2疲勞試驗 50
5-2二階梯應力譜對試片之影響 51
5-3二階梯應力譜之試片破壞模式 53
第六章 結論 61
參 考 文 獻 62

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