本研究之目標乃針對Carbon/Epoxy [0/45/90/-45]2S擬均向性複合材料積層板之疲勞性質與微觀分析，進行一系統性之探討；分析此複合材料在不同溫度及濕度環境下，及承受扭矩負載及低能量衝擊情況下，其破壞機制與其對疲勞性質之影響，探討積層板承受扭矩負載和低能量衝擊之耦合效應(couple effects)後，其殘餘拉伸強度分佈情形，以及不同應力負載下之疲勞性質，訂出其疲勞測試之S-N曲線方程式。藉此比較，吾人可探討材料承受扭矩負載以及衝擊交互作用前、後對拉伸-拉伸疲勞性質的差異性。另外，觀察材料在不同的溫度及濕度環境下，承受扭矩負載、低能量衝擊及疲勞測試後之損傷以及斷裂面之破壞情形，藉以探討各分析模式之適用性，以發揮CFRP複合材料之特性，並能安全的應用於航空、國防科技與民生工業上。經由實驗結果之比較，發現不論應力負載的大小及溫溼度環境的高低，先預扭再經低能量衝擊最後再經溫濕處理之試片，多半有比一般預估值有較長的疲勞壽命表現；而先預扭再經溫濕處理再經低能量衝擊之試片，疲勞壽命表現次之；而先低能量衝擊再預扭再經溫濕處理之試片，疲勞壽命表現再次之；先低能量衝擊再經溫濕處理最後再經扭轉作用之試片疲勞壽命最短。

This work presents a systematic study of the fatigue behavior and microscopic analysis of Carbon/Epoxy [0/45/90/-45]2S quasi-isotropic composite laminates. The failure mechanism and fatigue effects of the composites under pretorsional twist angle, low-energy impact and/or hygrothermal treatment are investigated in this study. The couple effects of the laminates under pretorsional twist angle, low-energy impact and/or hygrothermally treated as well as the distribution of the residual tensile strength and the S-N curve under various stress levels are also studied. The residual strength of the specimen under hygrothermal treatment is decreased, especially for 60oC with 60%RH treatment. Pretorsion then low-energy impact and then hygrothermal treatment specimen has the longest fatigue life, pretorsion then hygrothermally treated and then low-energy impact specimen has the secondary fatigue life that longer than the low-energy impact then pretorsion and then hygrothermally treated specimen, however, the low-energy impact first then hygrothermally treated and then pretorsion specimen has the shortest fatigue life.

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