标准铆钉拉伸剪切破坏模式研究AStudyontheShear-中华科技大学.PDFVIP

Journal of China University of Science and Technology Vol.56-2013.07 標準鉚釘拉伸剪切破壞模式研究 A Study on the Shear Failure Mode of Standard Rivets Tensile 鍾禎有 Chen-Yu Chung 中華科技大學 航空機械系 ，講師 Department of Aviation Mechanical Engineering China University of Science Technology, Iecturer 摘要 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。 關鍵詞 ：材料拉伸試驗、剪切應力、萬用材料拉伸試驗機 。 Abstract 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 35 標準鉚釘拉伸剪切破壞模式研究 gripped by the multipurpose testing machine to conduct the tensile test and