Abstract
在航空及一般工程構件的製造或使用過程中，構件材料的區域性損傷（如金屬材料中的裂紋或孔洞和複合材料中的脫層或空穴）往往難以預料。倘若某構件損傷程度並未達到影響整體結構的使用時，應盡量避免拆換該構件，以達節約及爭取時效之目的。因此，修補便成為確保結構安全的最佳途徑之一。而修補方法中，膠合修補可達到方便、迅速且有效的要求，而且膠合修補不似機械式修補產生由於鑽孔而所導致額外的應力集中現象，是一種廣泛使用的修補方法。近年來，由於複合材料擁有種種優越的材料性質而且被進步地發展，因此複合材料已廣泛地被運用於修補領域中。本文利用複合材料對含缺陷（裂縫）之航空金屬材料做一系列不同方式的膠合修補（Bonded Repair）， 進而以電子光斑影像干涉術（ Elec-tronic Speckle Pattern Interferometry, ESPI ）擷取修補前後的資料作為評估修補效果的依據。修補的方式分為單邊和雙邊補綻，而修補之補片之纖維方向及厚度對於修補的效果，也將做一完整的討論。另外，實驗結果將與有限單元法 (Finite Element Method, FEM) 所得之數值結果相互比較，並且求取黏著劑中最大剪應力及最大剝離應力和補片上之最大主應力，以期完整地討論膠合修補之修補效率。最後，本文嘗試利用混合實驗與有限單元法－－混合法，將實驗所得的資料代入有限單元法的邊界條件中，以求取其修補效應並比較利用這些方法所得結果的差異性。 本文共分九章：第一章引言；第二章文獻回顧；第三章理論；第四章實驗準備；第五章實驗技術；第六章數值方法；第七章複合法；第八章結果與討論；第九章結論。When defects or cracks exist in a structure, patching is one ofthe best solutions to enhance the structural safety and tosave the repair expenses. Because composite materials havethe characteristics of light weight and high strength-to-weight and stiffness ratios, they have found their ways intomost subsys- tems of aeronautic and aerospace vehicles inthe recent years. Various parameters must be considered incomposite patching te- chnique such as patching designs,material selections, repair methods, environmental factors,defect testings, economic consi- derations, etc. A series ofaluminum alloy sheets containing a central crack weremanufactured in this dissertation. Effects of variousstacking sequences, fiber orientations and repair methodsof composite patchings on the stress intensity factor (SIF)were investigated. Then the repair efficiency can becalculated in terms of the SIF. In the past, the combinedexperimental and numerical method, so-called hybrid method, wasseldom utilized to investigate the composite patchingproblems. In this dissertation, in addition to the adoptedexperimental method, i.e. the electronic speckle patterninterferometry (ESPI) method, the numerical method, i.e. thefinite element method (FEM) and the hybrid method were usedto investigate the repair efficiency of composite patching.In addition, maximum shear stress in the adhesive, maximumpeeling stress in the adhesive and maximum principal stress inthe pat- ching were also investigated by the FEM and the hybridmethod.