Test Research on Fuselage Panel Subjected to Internal Pressure Load
Internal pressure is a severe cyclic load for fuselage structure, and it is important to investigate the fatigue and damage tolerance characters of fuselage panel under internal pressure. Boundary condition simulation of fuselage panel subjected to internal pressure load is challenging, and the qual...
| Main Authors: | , , |
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| Format: | Article |
| Language: | zho |
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Editorial Department of Advances in Aeronautical Science and Engineering
2018-02-01
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| Series: | Hangkong gongcheng jinzhan |
| Subjects: | |
| Online Access: | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2017079?st=article_issue |
| _version_ | 1798028869506170880 |
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| author | Zang Weifeng Chen An Dong Dengke |
| author_facet | Zang Weifeng Chen An Dong Dengke |
| author_sort | Zang Weifeng |
| collection | DOAJ |
| description | Internal pressure is a severe cyclic load for fuselage structure, and it is important to investigate the fatigue and damage tolerance characters of fuselage panel under internal pressure. Boundary condition simulation of fuselage panel subjected to internal pressure load is challenging, and the quality of the simulation influences the range of transition area and even the stress distribution size in examining area. To investigate the stress distribution of fuselage panel subjected to internal pressure, a new test method is proposed. “D” jig is utilized to simulate the longitudinal boundary conditions of fuselage panel, and “Arch” connectors are utilized to simulate the circumferential boundary conditions. Airtight end-plate is utilized to simulate the end of the fuselage barrel. Test fixture and fuselage panel specimen are designed and manufactured according to the boundary simulation requirements. Tests are conducted based on the proposed method. The test results show that hoop stress and axial stress in transition area are much more lower than in the test area. Hoop stress, axial stress and normal displacement in the test area are consistent with theoretic results. The proposed test method settle for engineering precision requirements and provides reference for configuration-selection tests of fuselage panel subjected to internal pressure load. |
| first_indexed | 2024-04-11T19:16:30Z |
| format | Article |
| id | doaj.art-3205fded1e6543e9b22a8a6e1b17b9e7 |
| institution | Directory Open Access Journal |
| issn | 1674-8190 |
| language | zho |
| last_indexed | 2024-04-11T19:16:30Z |
| publishDate | 2018-02-01 |
| publisher | Editorial Department of Advances in Aeronautical Science and Engineering |
| record_format | Article |
| series | Hangkong gongcheng jinzhan |
| spelling | doaj.art-3205fded1e6543e9b22a8a6e1b17b9e72022-12-22T04:07:26ZzhoEditorial Department of Advances in Aeronautical Science and EngineeringHangkong gongcheng jinzhan1674-81902018-02-0191697610.16615/j.cnki.1674-8190.2018.01.00920180109Test Research on Fuselage Panel Subjected to Internal Pressure LoadZang Weifeng0Chen An1Dong Dengke2Metallic Structure Strength Laboratory, Aircraft Strength Research Institute of China, Xi'an 710065, ChinaMetallic Structure Strength Laboratory, Aircraft Strength Research Institute of China, Xi'an 710065, ChinaMetallic Structure Strength Laboratory, Aircraft Strength Research Institute of China, Xi'an 710065, ChinaInternal pressure is a severe cyclic load for fuselage structure, and it is important to investigate the fatigue and damage tolerance characters of fuselage panel under internal pressure. Boundary condition simulation of fuselage panel subjected to internal pressure load is challenging, and the quality of the simulation influences the range of transition area and even the stress distribution size in examining area. To investigate the stress distribution of fuselage panel subjected to internal pressure, a new test method is proposed. “D” jig is utilized to simulate the longitudinal boundary conditions of fuselage panel, and “Arch” connectors are utilized to simulate the circumferential boundary conditions. Airtight end-plate is utilized to simulate the end of the fuselage barrel. Test fixture and fuselage panel specimen are designed and manufactured according to the boundary simulation requirements. Tests are conducted based on the proposed method. The test results show that hoop stress and axial stress in transition area are much more lower than in the test area. Hoop stress, axial stress and normal displacement in the test area are consistent with theoretic results. The proposed test method settle for engineering precision requirements and provides reference for configuration-selection tests of fuselage panel subjected to internal pressure load.http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2017079?st=article_issuefuselage panelinternal pressure loadboundary simulationhoop stressaxial stressshear stress |
| spellingShingle | Zang Weifeng Chen An Dong Dengke Test Research on Fuselage Panel Subjected to Internal Pressure Load Hangkong gongcheng jinzhan fuselage panel internal pressure load boundary simulation hoop stress axial stress shear stress |
| title | Test Research on Fuselage Panel Subjected to Internal Pressure Load |
| title_full | Test Research on Fuselage Panel Subjected to Internal Pressure Load |
| title_fullStr | Test Research on Fuselage Panel Subjected to Internal Pressure Load |
| title_full_unstemmed | Test Research on Fuselage Panel Subjected to Internal Pressure Load |
| title_short | Test Research on Fuselage Panel Subjected to Internal Pressure Load |
| title_sort | test research on fuselage panel subjected to internal pressure load |
| topic | fuselage panel internal pressure load boundary simulation hoop stress axial stress shear stress |
| url | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2017079?st=article_issue |
| work_keys_str_mv | AT zangweifeng testresearchonfuselagepanelsubjectedtointernalpressureload AT chenan testresearchonfuselagepanelsubjectedtointernalpressureload AT dongdengke testresearchonfuselagepanelsubjectedtointernalpressureload |