2001-08-012024-05-18https://scholars.lib.ntu.edu.tw/handle/123456789/703246摘要：航空完整性評估在航空結構與組件之品保中佔有重要之地位，而金屬疲勞裂縫成長又為航空結構完整性評估中極為重要之一項研究課題，因此本計畫進行航空結構材料之疲勞裂縫成長研究，採用蒙地卡羅模擬及兩個考慮參數變異與相關性之隨機裂縫成長模式修正式來呈現裂縫延伸與疲勞壽命分佈，同時進行相當數量之等振幅與隨機振幅疲勞裂縫延伸實驗，透過模擬結果與實驗數據之比較，以驗證所採用模式之可用性與準確性。<br> Abstract: Structure integrity assessment plays a significant role in the quality assurance of aeronautical structures and components. Fatigue crack propagation is one of the most important issues in the integrity assessment of aeronautical structures. Therefore, fatigue crack propagation of aeronautical materials is studied. Special emphasis is put on the variability analysis of the fatigue crack growth curves. In the project, two approaches are employed for such an analysis. The first approach is a Monte-Carlo simulation method and the second one is based on a modified stochastic fatigue crack growth model. In the latter case, the relationship between two important parameters is considered in particular. A sufficient amount of fatigue crack propagation tests are carried out to verify the simulation and analytical results.航空結構完整性評估金屬疲勞裂縫成長蒙地卡羅模擬隨機裂縫成長模式可靠度分析Structural Integrity AssessmentFatigue Crack PropagationMote-Carlo SimulationStochastic Crack Propagation ModelReliability Analysis