Numerical and experimental fatigue crack growth analysis in mode-I for repaired aluminum panels using composite material |
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| Affiliation: | 1. Aerospace Engineering Department, Amirkabir University of Technology, Hafez Avenue, 424, Tehran, Iran;2. Mechanical Engineering Department, Amirkabir University of Technology, Hafez Avenue, 424, Tehran, Iran;1. Fatigue and Fracture Mechanics Lab., Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran;2. Department of Mechanical Engineering, Shahid Rajaee Teacher Training University, Tehran, Iran;3. Institute for Materials Testing, Materials Science and Strength of Materials (IMWF), University of Stuttgart, Stuttgart, Germany;1. School of Mechanical and Aerospace Engineering, Gyeongsang National University, Jinju, Gyeongnam 660-701, Republic of Korea;2. Agency for Defense Development, Republic of Korea;3. School of Mechanical and Aerospace Engineering, Research Center for Aircraft Parts Technology, Gyeongsang National University, Jinju, Gyeongnam 660-701, Republic of Korea;1. INEGI – Instituto de Ciência e Inovação em Engenharia Mecânica e Engenharia Industrial, Rua Dr. Roberto Frias 400, 4200-465 Porto, Portugal;2. Faculdade de Engenharia da Universidade do Porto, Departamento de Engenharia Mecânica, Rua Dr. Roberto Frias, 4200-465 Porto, Portugal;1. Key Laboratory of High Performance Ship Technology (Wuhan University of Technology), Ministry of Education, Wuhan 430063, China;2. State Key Laboratory of Ocean Engineering, Shanghai Jiao Tong University, Shanghai 200240, China;3. China Ship Development and Design Center, Wuhan 430064, China;1. College of Quality and Technical Supervision, Hebei University, Baoding 071002, China;2. National & Local Joint Engineering Research Center of Metrology Instrument and System, Hebei University, Baoding 071002, China;3. Hebei Key Laboratory of Energy Metering and Safety Testing Technology, Hebei University, Baoding 071002, China;1. Governement Engineering College, Dahod 389151, India;2. Birla Vishvakarma Mahavidyalaya, V.V.Nagar 388120, India |
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| Abstract: | Crack-front shape is an important parameter influencing the stress intensity factor and crack propagation rate in asymmetric repaired panels. In this study, the numerical and experimental fatigue crack growth behaviour of centrally cracked aluminum panels in mode-I condition repaired with single-side composite patches are investigated. It is shown that the crack growths non-uniformly from its initial location through the thickness of a single-side repaired panel. There is a good agreement between the propagated crack-front shapes obtained from finite element analysis with those obtained from the experiments for various repaired panels with different patch thicknesses. Furthermore, effects of plate and patch thickness on the crack growth life of the repaired panels are investigated. The experimental results show that the crack growth life of thin panels may increase up to 236% using a 16 layers patch. However, for thick panels, the life may extend about 21–35% using a 4 layers patch. Implementing of 8 and 16 layers patches has not a significant effect on the life extension of thick panels with respect to the 4 layers patch life. |
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