標準鉚釘拉伸剪切破壞模式研究

在飛機結構上有許多是須利用鉚釘結合的，本研究針對鉚釘承受正向壓力變形後，再進行拉伸試驗，模擬飛機結構蒙皮結合之鉚釘承受剪切應力的變形模式，並以不同鉚合方式及不同材質鉚釘進行試驗，本研究主要係以航空用鉚釘MS-20470-AD-5-6~MS-20470-AD-5-8為主要試驗材料，並以材質6061-T6鋁合金板製成尺寸173mm*25.4mm*1mm基板，以兩片一組搭接鉚合兩顆鉚釘鉚合而成標準拉伸試片，夾持端並以END TAB保護試片夾持端，以確保實驗準確性，並夾持於萬用材料拉伸試驗機進行拉伸試驗，並將其試驗結果透過電腦紀錄實驗結果，將其結果彙整圖表與文獻作比較，並探討鉚釘承受正向應力後的正向剪切應力變形模式，其結果可供未來相關學者參考。

關鍵字

材料拉伸試驗；剪切應力；萬用材料拉伸試驗機

並列摘要

There are many aircraft structure members that must be attached by rivets. This study focuses on the deformation of rivets under positive pressure and then the tensile test, simulating the deformation mode of the rivets under shear stress when such rivets are attached to the skin of an aircraft structure. The test uses different riveting approaches and rivets of different materials. The primary test materials of this study are rivets used in the aviation industry such as MS-20470-AD-5-6 ~ MS-20470-AD-5-8. In addition, 6061-T6 aluminum plate is used to make a base plate with dimension of 173 mm * 25.4 mm * 1 mm; and then two rivets are used to attach together the lap-joint of two base plates to form the standard tensile test specimen. Moreover, end tabs are used to protect the gripping end of the specimen to ensure the accuracy of test. The specimen is then gripped by the multipurpose testing machine to conduct the tensile test and the test results are recorded by computer; the experimental results are tabulated in graphic charts to compare with existing literature and to explore the deformation mode of rivets after being subjected to positive stress shear. Such results can be used as reference by students concerned in the future.

並列關鍵字

Tensile Test ； Shear Stress ； Multipurpose Tensile Testing Machine

國際替代計量

標準鉚釘拉伸剪切破壞模式研究

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