Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics
In the current research, we propose a novel non-ordinary state-based peridynamics (PD) fatigue model for multiple cracks’ initiation and growth under tension–tension fatigue load. In each loading cycle, the fatigue loading is redistributed throughout the peridynamic solid body, leading to progressiv...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-07-01
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| Series: | Metals |
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| Online Access: | https://www.mdpi.com/2075-4701/12/8/1286 |
| _version_ | 1797408917440954368 |
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| author | Junzhao Han Guozhong Wang Xiaoyu Zhao Rong Chen Wenhua Chen |
| author_facet | Junzhao Han Guozhong Wang Xiaoyu Zhao Rong Chen Wenhua Chen |
| author_sort | Junzhao Han |
| collection | DOAJ |
| description | In the current research, we propose a novel non-ordinary state-based peridynamics (PD) fatigue model for multiple cracks’ initiation and growth under tension–tension fatigue load. In each loading cycle, the fatigue loading is redistributed throughout the peridynamic solid body, leading to progressive fatigue damage formation and expansion in an autonomous fashion. The proposed fatigue model parameters are first verified by a 3D numerical solution, and then, the novel model is used to depict the widespread fatigue damage evolution of the aircraft wing corner box. The modified constitutive damage model has been implemented into the peridynamic framework. Furthermore, the criteria and processes from multiple initiations to propagation are discussed in detail. It was found that the computational results obtained from the PD fatigue model were consistent with those from the test data. The angular errors of multiple cracks are within 2.66% and the number of cycles errors are within 15%. A comparison of test data and computational results indicates that the fatigue model can successfully capture multiple crack formations and propagation, and other behaviors of aluminum alloy material. |
| first_indexed | 2024-03-09T04:05:31Z |
| format | Article |
| id | doaj.art-6c47ae72c2b846cb8e953d27eecf8d4e |
| institution | Directory Open Access Journal |
| issn | 2075-4701 |
| language | English |
| last_indexed | 2024-03-09T04:05:31Z |
| publishDate | 2022-07-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Metals |
| spelling | doaj.art-6c47ae72c2b846cb8e953d27eecf8d4e2023-12-03T14:06:44ZengMDPI AGMetals2075-47012022-07-01128128610.3390/met12081286Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based PeridynamicsJunzhao Han0Guozhong Wang1Xiaoyu Zhao2Rong Chen3Wenhua Chen4School of Mechanical Engineering and Automation, Zhejiang Sci-Tech University, Hangzhou 310018, ChinaHenghong Intelligent Equipment Co., Ltd., Hangzhou 310018, ChinaChina Ship Scientific Research Center, Wuxi 214028, ChinaSchool of Mechanical Engineering and Automation, Zhejiang Sci-Tech University, Hangzhou 310018, ChinaSchool of Mechanical Engineering and Automation, Zhejiang Sci-Tech University, Hangzhou 310018, ChinaIn the current research, we propose a novel non-ordinary state-based peridynamics (PD) fatigue model for multiple cracks’ initiation and growth under tension–tension fatigue load. In each loading cycle, the fatigue loading is redistributed throughout the peridynamic solid body, leading to progressive fatigue damage formation and expansion in an autonomous fashion. The proposed fatigue model parameters are first verified by a 3D numerical solution, and then, the novel model is used to depict the widespread fatigue damage evolution of the aircraft wing corner box. The modified constitutive damage model has been implemented into the peridynamic framework. Furthermore, the criteria and processes from multiple initiations to propagation are discussed in detail. It was found that the computational results obtained from the PD fatigue model were consistent with those from the test data. The angular errors of multiple cracks are within 2.66% and the number of cycles errors are within 15%. A comparison of test data and computational results indicates that the fatigue model can successfully capture multiple crack formations and propagation, and other behaviors of aluminum alloy material.https://www.mdpi.com/2075-4701/12/8/1286non-ordinary state-based peridynamicstension–tension fatigue loadmultiple cracksaircraft wing corner box |
| spellingShingle | Junzhao Han Guozhong Wang Xiaoyu Zhao Rong Chen Wenhua Chen Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics Metals non-ordinary state-based peridynamics tension–tension fatigue load multiple cracks aircraft wing corner box |
| title | Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics |
| title_full | Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics |
| title_fullStr | Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics |
| title_full_unstemmed | Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics |
| title_short | Modeling of Multiple Fatigue Cracks for the Aircraft Wing Corner Box Based on Non-ordinary State-based Peridynamics |
| title_sort | modeling of multiple fatigue cracks for the aircraft wing corner box based on non ordinary state based peridynamics |
| topic | non-ordinary state-based peridynamics tension–tension fatigue load multiple cracks aircraft wing corner box |
| url | https://www.mdpi.com/2075-4701/12/8/1286 |
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