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A Study on a Composite Laminate Pull-through Joint

  • Kwon, Jeong-Sik (Department of Aerospace & Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Jin-Sung (Department of Aerospace & Mechanical Engineering, Korea Aerospace University) ;
  • Seo, Bum-Kyung (Department of Aerospace & Mechanical Engineering, Korea Aerospace University) ;
  • Lee, Soo-Yong (Department of Aerospace & Mechanical Engineering, Korea Aerospace University)
  • Received : 2016.07.20
  • Accepted : 2016.12.15
  • Published : 2017.03.30

Abstract

In this paper, composite laminate pull-through resistance was analyzed using the FEM method and compared with test results. 2D and 3D simplified FEM models, a nonlinear analysis, and a progressive failure analysis utilizing three composite laminate failure theories Maximum Stress, Maximum Strain, and Tsai-Wu were used to predict the FEM results with the test results. The load and boundary conditions of the test were applied to the FEM to simulate the test. A composite laminate pull-through test (ASTM D7332 Proc. B) was designed with a special fixture to collect more precise data. The test results were compared with the FEM analysis results.

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