Research and strength analysis of hoop bending test of composite fuselage integral frame
As the main bearing structure of civil aircraft, the fuselage frame is of great significance to the weight of the aircraft.A hoop bending test is carried out on the composite fuselage curved panels with C-type and Z-type integral frames to study the failure mode and load-bearing capacity of the inte...
| Main Authors: | , , |
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| Format: | Article |
| Language: | zho |
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Editorial Department of Advances in Aeronautical Science and Engineering
2023-02-01
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| Series: | Hangkong gongcheng jinzhan |
| Subjects: | |
| Online Access: | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2022037 |
| _version_ | 1797823277425491968 |
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| author | LIANG Heng TANG Guowei ZHENG Xiaoling |
| author_facet | LIANG Heng TANG Guowei ZHENG Xiaoling |
| author_sort | LIANG Heng |
| collection | DOAJ |
| description | As the main bearing structure of civil aircraft, the fuselage frame is of great significance to the weight of the aircraft.A hoop bending test is carried out on the composite fuselage curved panels with C-type and Z-type integral frames to study the failure mode and load-bearing capacity of the integral frame, as well as the influence of lateral support on the load-bearing capacity of the frame.A pair of force couple is used to apply bending load on the panel.The modified engineering method and finite element (FE) model are used to predict the failure load and compare with the test results.The results show that C-type integral fame has better design redundancy than Z-type integral frame.The arrangement of lateral support is the key to improve the load capability of the integral frame, as it can affect the failure mode.The modified engineering method can predict the frame lateral stability effectively,which can be used for calculation iterations of the integral frame size and lateral support arrangement rapidly.However, the engineering algorithm for inner flange local stability is not conservation, and the FE model should be used for optimization iteration. |
| first_indexed | 2024-03-13T10:21:44Z |
| format | Article |
| id | doaj.art-4e247b97c4f5436fbc89af041ccf6e32 |
| institution | Directory Open Access Journal |
| issn | 1674-8190 |
| language | zho |
| last_indexed | 2024-03-13T10:21:44Z |
| publishDate | 2023-02-01 |
| publisher | Editorial Department of Advances in Aeronautical Science and Engineering |
| record_format | Article |
| series | Hangkong gongcheng jinzhan |
| spelling | doaj.art-4e247b97c4f5436fbc89af041ccf6e322023-05-20T08:56:58ZzhoEditorial Department of Advances in Aeronautical Science and EngineeringHangkong gongcheng jinzhan1674-81902023-02-0114110411310.16615/j.cnki.1674-8190.2023.01.1220230112Research and strength analysis of hoop bending test of composite fuselage integral frameLIANG Heng0TANG Guowei1ZHENG Xiaoling2Composite Center, Shanghai Aircraft Manufacturing Co., Ltd., Shanghai 201324, ChinaComposite Center, Shanghai Aircraft Manufacturing Co., Ltd., Shanghai 201324, ChinaComposite Center, Shanghai Aircraft Manufacturing Co., Ltd., Shanghai 201324, ChinaAs the main bearing structure of civil aircraft, the fuselage frame is of great significance to the weight of the aircraft.A hoop bending test is carried out on the composite fuselage curved panels with C-type and Z-type integral frames to study the failure mode and load-bearing capacity of the integral frame, as well as the influence of lateral support on the load-bearing capacity of the frame.A pair of force couple is used to apply bending load on the panel.The modified engineering method and finite element (FE) model are used to predict the failure load and compare with the test results.The results show that C-type integral fame has better design redundancy than Z-type integral frame.The arrangement of lateral support is the key to improve the load capability of the integral frame, as it can affect the failure mode.The modified engineering method can predict the frame lateral stability effectively,which can be used for calculation iterations of the integral frame size and lateral support arrangement rapidly.However, the engineering algorithm for inner flange local stability is not conservation, and the FE model should be used for optimization iteration.http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2022037fuselage framecompositestabilityfailure modeengineering method |
| spellingShingle | LIANG Heng TANG Guowei ZHENG Xiaoling Research and strength analysis of hoop bending test of composite fuselage integral frame Hangkong gongcheng jinzhan fuselage frame composite stability failure mode engineering method |
| title | Research and strength analysis of hoop bending test of composite fuselage integral frame |
| title_full | Research and strength analysis of hoop bending test of composite fuselage integral frame |
| title_fullStr | Research and strength analysis of hoop bending test of composite fuselage integral frame |
| title_full_unstemmed | Research and strength analysis of hoop bending test of composite fuselage integral frame |
| title_short | Research and strength analysis of hoop bending test of composite fuselage integral frame |
| title_sort | research and strength analysis of hoop bending test of composite fuselage integral frame |
| topic | fuselage frame composite stability failure mode engineering method |
| url | http://hkgcjz.cnjournals.com/hkgcjz/article/abstract/2022037 |
| work_keys_str_mv | AT liangheng researchandstrengthanalysisofhoopbendingtestofcompositefuselageintegralframe AT tangguowei researchandstrengthanalysisofhoopbendingtestofcompositefuselageintegralframe AT zhengxiaoling researchandstrengthanalysisofhoopbendingtestofcompositefuselageintegralframe |