Tensile Property of Aeronautical Composite-Metal Joint Structure and Its Progressive Damage

ZHANG Haoyu; HOU Bo; HE Yuting; FENG Yu; TAN Xiangfei

doi:10.11973/jxgccl201708020

Materials and Mechanical Engineering > 2017 > 41(8): 87-92. > DOI: 10.11973/jxgccl201708020

ZHANG Haoyu, HOU Bo, HE Yuting, FENG Yu, TAN Xiangfei. Tensile Property of Aeronautical Composite-Metal Joint Structure and Its Progressive Damage[J]. Materials and Mechanical Engineering, 2017, 41(8): 87-92. DOI: 10.11973/jxgccl201708020

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Tensile Property of Aeronautical Composite-Metal Joint Structure and Its Progressive Damage

1. No. 95906 Troops of PLA, Beijing 102206, China;
2. Army Aviation Research Institute, Beijing 101121, China;
3. Engineering College, Air Force Engineering University, Xi'an 710038, China

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Received Date: July 07, 2016
Revised Date: June 07, 2017

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Abstract

Abstract

The model of the composite-metal joint structure of one type aircrafe was established using the finite element software. Then with the modified Camanho damage degradation model as the criterion of failure judgment, the tensile property and damage accumulation process of the joint structure were simulated and verified by the tests. The results show that after assembled with the anti-bending fixture, the tensile test results of the composite-metal joint structure were more accurate and the tensile damage mode changed from pull-off failure to crushing failure. Under relatively low tensile loads, the strain increased linearly with the increase of load and was obviously larger on the metal than on the composite laminate. The damage was produced from the connecting bolts between the composite and metal, then accumulated gradually and extended along the compressive direction of the bolts with the increase of load. The simulated final destruction load was 90 kN with the relative error of only 6.5% comparing to the test result, indicating the accuracy of the simulation.
- composite,
- accumulated damage,
- joint structure,
- failure criterion,
- tensile strength

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