RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT)
In order to study the fatigue crack propagation of the fuselage skin under uniform pressurized cyclic load, experiments were carried out with the self-made aircraft fuselage skin uniform pressurized fatigue device. Firstly, the stress intensity factor was calculated by the extended finite element me...
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Editorial Office of Journal of Mechanical Strength
2023-01-01
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| Series: | Jixie qiangdu |
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| Online Access: | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2023.04.031 |
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| author | LIU LiPing HAN HaoHao LIU JiaHuan BAO Rui LIN YueGuo |
| author_facet | LIU LiPing HAN HaoHao LIU JiaHuan BAO Rui LIN YueGuo |
| author_sort | LIU LiPing |
| collection | DOAJ |
| description | In order to study the fatigue crack propagation of the fuselage skin under uniform pressurized cyclic load, experiments were carried out with the self-made aircraft fuselage skin uniform pressurized fatigue device. Firstly, the stress intensity factor was calculated by the extended finite element method. Then, the deflection angle of the crack was calculated based on the maximum circumferential stress criterion and the strain energy density factor criterion, and the fatigue crack propagation path of the fuselage skin was predicted. Finally, the fatigue fracture was analyzed under scanning electron microscope. The results show that the crack propagation paths predicted by the two criteria are basically consistent with the crack propagation path obtained by experiment.The surface cracks of the fuselage skin are mixed mode cracks. With the increase of the crack length, K<sub>Ⅰ</sub> first increases and then decreases, K<sub>Ⅱ</sub> first decreases rapidly to around 0, then oscillates around 0, and finally increases rapidly when the lower hole is about to penetrate. Observing the fatigue fracture shows that the fatigue cracks are initiated by multiple fatigue sources. The crack propagation zone has typical quasi-cleavage fracture characteristics, and the fatigue crack growth rate first increases and then decreases with the increase of crack length. The instantaneous fracture zone is a typical dimple feature with different sizes. |
| format | Article |
| id | doaj-art-bbf782cb9d114538bf5f0fd67bf5ba24 |
| institution | Kabale University |
| issn | 1001-9669 |
| language | zho |
| publishDate | 2023-01-01 |
| publisher | Editorial Office of Journal of Mechanical Strength |
| record_format | Article |
| series | Jixie qiangdu |
| spelling | doaj-art-bbf782cb9d114538bf5f0fd67bf5ba242025-01-15T02:41:05ZzhoEditorial Office of Journal of Mechanical StrengthJixie qiangdu1001-96692023-01-0198599242278052RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT)LIU LiPingHAN HaoHaoLIU JiaHuanBAO RuiLIN YueGuoIn order to study the fatigue crack propagation of the fuselage skin under uniform pressurized cyclic load, experiments were carried out with the self-made aircraft fuselage skin uniform pressurized fatigue device. Firstly, the stress intensity factor was calculated by the extended finite element method. Then, the deflection angle of the crack was calculated based on the maximum circumferential stress criterion and the strain energy density factor criterion, and the fatigue crack propagation path of the fuselage skin was predicted. Finally, the fatigue fracture was analyzed under scanning electron microscope. The results show that the crack propagation paths predicted by the two criteria are basically consistent with the crack propagation path obtained by experiment.The surface cracks of the fuselage skin are mixed mode cracks. With the increase of the crack length, K<sub>Ⅰ</sub> first increases and then decreases, K<sub>Ⅱ</sub> first decreases rapidly to around 0, then oscillates around 0, and finally increases rapidly when the lower hole is about to penetrate. Observing the fatigue fracture shows that the fatigue cracks are initiated by multiple fatigue sources. The crack propagation zone has typical quasi-cleavage fracture characteristics, and the fatigue crack growth rate first increases and then decreases with the increase of crack length. The instantaneous fracture zone is a typical dimple feature with different sizes.http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2023.04.031Fuselage skinUniform pressurizedFatigue crackCrack propagationFatigue fracture |
| spellingShingle | LIU LiPing HAN HaoHao LIU JiaHuan BAO Rui LIN YueGuo RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT) Jixie qiangdu Fuselage skin Uniform pressurized Fatigue crack Crack propagation Fatigue fracture |
| title | RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT) |
| title_full | RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT) |
| title_fullStr | RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT) |
| title_full_unstemmed | RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT) |
| title_short | RESEARCH ON THE FATIGUE CRACK PROPAGATION OF AIRCRAFT FUSELAGE SKIN UNDER UNIFORM PRESSURIZED LOAD (MT) |
| title_sort | research on the fatigue crack propagation of aircraft fuselage skin under uniform pressurized load mt |
| topic | Fuselage skin Uniform pressurized Fatigue crack Crack propagation Fatigue fracture |
| url | http://www.jxqd.net.cn/thesisDetails#10.16579/j.issn.1001.9669.2023.04.031 |
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