Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression
The axial compressive experiment was conducted on the domestic advanced composite stiffened panel, and its buckling and post-buckling performance was analyzed by monitoring strain and out-of-plane displacement of typical positions. The initial buckling load and buckling mode of panels were calculate...
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| Format: | Article |
| Language: | zho |
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Journal of Aeronautical Materials
2016-08-01
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| Series: | Journal of Aeronautical Materials |
| Subjects: | |
| Online Access: | http://jam.biam.ac.cn/CN/10.11868/j.issn.1005-5053.2016.4.008 |
| _version_ | 1828425293793067008 |
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| author | ZHANG Haoyu HE Yuting FENG Yu TAN Xiangfei ZHENG Jie |
| author_facet | ZHANG Haoyu HE Yuting FENG Yu TAN Xiangfei ZHENG Jie |
| author_sort | ZHANG Haoyu |
| collection | DOAJ |
| description | The axial compressive experiment was conducted on the domestic advanced composite stiffened panel, and its buckling and post-buckling performance was analyzed by monitoring strain and out-of-plane displacement of typical positions. The initial buckling load and buckling mode of panels were calculated by engineering methods to direct the follow-up axial compressive experiment. The experimental results show that the buckling patterns are mainly local buckling of panels between stiffeners, the second buckling of few positions of panels and cylindrical buckling of all 4 stiffeners successively; after local buckling of panels, part of load bearded by panels before is transferred to stiffeners and then stiffeners become the main bearing part; after fracture failure of stiffeners, the specimen is destroyed rapidly; the average value of failure load is 482.67 kN, which is 2.37 times of 204 kN of the average value of buckling load; the composite stiffened panel can bear more load after buckling. |
| first_indexed | 2024-12-10T16:30:01Z |
| format | Article |
| id | doaj.art-1f29189f3c474b1dba767b060fa8a15f |
| institution | Directory Open Access Journal |
| issn | 1005-5053 1005-5053 |
| language | zho |
| last_indexed | 2024-12-10T16:30:01Z |
| publishDate | 2016-08-01 |
| publisher | Journal of Aeronautical Materials |
| record_format | Article |
| series | Journal of Aeronautical Materials |
| spelling | doaj.art-1f29189f3c474b1dba767b060fa8a15f2022-12-22T01:41:33ZzhoJournal of Aeronautical MaterialsJournal of Aeronautical Materials1005-50531005-50532016-08-01364556310.11868/j.issn.1005-5053.2016.4.00820160408Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under CompressionZHANG Haoyu0HE Yuting1FENG Yu2TAN Xiangfei3ZHENG Jie4Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China;The First Aircraft Institute, Aviation Industry Corporation, Xi'an 710089, ChinaThe axial compressive experiment was conducted on the domestic advanced composite stiffened panel, and its buckling and post-buckling performance was analyzed by monitoring strain and out-of-plane displacement of typical positions. The initial buckling load and buckling mode of panels were calculated by engineering methods to direct the follow-up axial compressive experiment. The experimental results show that the buckling patterns are mainly local buckling of panels between stiffeners, the second buckling of few positions of panels and cylindrical buckling of all 4 stiffeners successively; after local buckling of panels, part of load bearded by panels before is transferred to stiffeners and then stiffeners become the main bearing part; after fracture failure of stiffeners, the specimen is destroyed rapidly; the average value of failure load is 482.67 kN, which is 2.37 times of 204 kN of the average value of buckling load; the composite stiffened panel can bear more load after buckling.http://jam.biam.ac.cn/CN/10.11868/j.issn.1005-5053.2016.4.008compositestiffened panelbuckling loadingbuckling modepost-buckling |
| spellingShingle | ZHANG Haoyu HE Yuting FENG Yu TAN Xiangfei ZHENG Jie Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression Journal of Aeronautical Materials composite stiffened panel buckling loading buckling mode post-buckling |
| title | Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression |
| title_full | Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression |
| title_fullStr | Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression |
| title_full_unstemmed | Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression |
| title_short | Buckling and Post-buckling Performance of Advanced Composite Stiffened Panel Under Compression |
| title_sort | buckling and post buckling performance of advanced composite stiffened panel under compression |
| topic | composite stiffened panel buckling loading buckling mode post-buckling |
| url | http://jam.biam.ac.cn/CN/10.11868/j.issn.1005-5053.2016.4.008 |
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