RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS
Composite stiffened panel structure is widely used in modern aircraft,which is prone to buckling under working conditions.A large number of tests show that the aircraft composite stiffened thin-wall structure has considerable post-buckling bearing capacity.The design scheme of the stiffened fuselage...
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| Format: | Article |
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| Language: | zho |
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Editorial Office of Journal of Mechanical Strength
2024-01-01
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| Series: | Jixie qiangdu |
| Online Access: | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2024.06.018 |
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| collection | DOAJ |
| description | Composite stiffened panel structure is widely used in modern aircraft,which is prone to buckling under working conditions.A large number of tests show that the aircraft composite stiffened thin-wall structure has considerable post-buckling bearing capacity.The design scheme of the stiffened fuselage curved panel with inner cladding and without inner cladding was proposed.The buckling load,bearing capacity and failure mode of the two kinds of curved panels with inner cladding and without inner cladding were calculated by using Abaqus under axial compressive load,pure shear load and compressive shear combined load.In the model,the Tsai-Wu criterion was used as the failure criterion of composite materials,and the damage evolution was realized by the subroutine Usdfld.It is found that the inner cladding of the hat stringer can significantly improve the post-buckling capacity of the structure and prolong the post-buckling process. |
| format | Article |
| id | doaj-art-3b130f45e71347769ad99e65efc0d4ff |
| institution | DOAJ |
| issn | 1001-9669 |
| language | zho |
| publishDate | 2024-01-01 |
| publisher | Editorial Office of Journal of Mechanical Strength |
| record_format | Article |
| series | Jixie qiangdu |
| spelling | doaj-art-3b130f45e71347769ad99e65efc0d4ff2025-08-20T03:11:54ZzhoEditorial Office of Journal of Mechanical StrengthJixie qiangdu1001-96692024-01-01461408141898128166RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELSComposite stiffened panel structure is widely used in modern aircraft,which is prone to buckling under working conditions.A large number of tests show that the aircraft composite stiffened thin-wall structure has considerable post-buckling bearing capacity.The design scheme of the stiffened fuselage curved panel with inner cladding and without inner cladding was proposed.The buckling load,bearing capacity and failure mode of the two kinds of curved panels with inner cladding and without inner cladding were calculated by using Abaqus under axial compressive load,pure shear load and compressive shear combined load.In the model,the Tsai-Wu criterion was used as the failure criterion of composite materials,and the damage evolution was realized by the subroutine Usdfld.It is found that the inner cladding of the hat stringer can significantly improve the post-buckling capacity of the structure and prolong the post-buckling process.http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2024.06.018 |
| spellingShingle | RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS Jixie qiangdu |
| title | RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS |
| title_full | RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS |
| title_fullStr | RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS |
| title_full_unstemmed | RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS |
| title_short | RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS |
| title_sort | research on post buckling design of hat stringer stiffened fuselage panels |
| url | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2024.06.018 |