Nonlinear analysis of a composite panel with a cutout repaired by a bonded tapered composite patch |
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| Affiliation: | 1. Aerospace and Mechanical Engineering, The University of Arizona, Tucson, AZ 85721, United States;2. NASA Langley Research Center, Hampton, VA 23681, United States;1. SISSA – International School for Advanced Studies, Via Bonomea 265, 34136 Trieste, Italy;2. Dip. Ingegneria Civile, Università di Roma Tor Vergata, Italy;3. Università di Roma Tor Vergata, Italy;1. Research center of Lightweight Structures and Intelligent Manufacturing, State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. Aerospace System Engineering Shanghai, Shanghai 201108, China;1. Department of Aerospace Engineering, University of Michigan, Ann Arbor, MI 48109-2140, United States;2. Department of Aeronautics and Astronautics, Guggenheim Hall, 211E, University of Washington, Seattle, WA 98195-2400, United States;1. Department of Mathematics, Hannam University, Daejeon 34430, Republic of Korea;2. Mechatronics R&D Center, Samsung Electronics, Hwaseong 18848, Republic of Korea;3. Department of Mathematical Sciences and Research Institute of Mathematics, Seoul National University, Seoul 08826, Republic of Korea |
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| Abstract: | This study presents a solution method to analyze the geometrically nonlinear response of a patch-repaired flat panel (skin) with a cutout under general loading conditions. The effect of induced stiffening due to tensile loading on the in-plane and, particularly, the out-of-plane behaviors of the patch-repaired skin are investigated. The damage to the skin is represented in the form of a cutout under the patch. The patch with tapered edges is free of external tractions. The skin is subjected to general boundary and loading conditions along its external edge. The solution method provides the transverse shear and normal stresses in the adhesive between the skin and the patch, and in-plane and bending stresses in the patch and skin. Both the patch and skin are made of linearly elastic composite laminates, and the adhesive between them is homogeneous and isotropic, exhibiting a bi-linear elastic behavior. Modified Green’s strain–displacement relations in conjunction with von Karman assumptions are employed in determining the in-plane strains in the skin and patch; however, the transverse shear strains in the adhesive are determined based on the shear-lag theory. The present solution method utilizes the principle of virtual work in conjunction with complex potential functions. |
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