Experimental investigation of repair of impact-damaged aircraft winglet under static bending moments 机翻标题: 暂无翻译,请尝试点击翻译按钮。

来源
Journal of Adhesion Science and Technology: The International Journal of Theoredtical and Basic Aspects of Adhesion Science and Its Applications in All Areas of Technology
年/卷/期
2018 / 32 / 13/16
页码
1410-1427
ISSN号
0169-4243
作者单位
Northwestern Polytech Univ, Sch Aeronaut, Inst Computat Mech & Its Applicat NPUiCMA, Xian, Shaanxi, Peoples R China;Northwestern Polytech Univ, Sch Aeronaut, Inst Computat Mech & Its Applicat NPUiCMA, Xian, Shaanxi, Peoples R China;Northwestern Polytech Univ, Sch Aeronaut, Inst Computat Mech & Its Applicat NPUiCMA, Xian, Shaanxi, Peoples R China;Northwestern Polytech Univ, Sch Aeronaut, Inst Computat Mech & Its Applicat NPUiCMA, Xian, Shaanxi, Peoples R China;Northwestern Polytech Univ, Sch Aeronaut, Inst Computat Mech & Its Applicat NPUiCMA, Xian, Shaanxi, Peoples R China;
作者
Feng, Wei;Xu, Fei;Li, Menglin;Zhang, Xiaoyu;You, Hao;
摘要
Bending behaviours of the repaired aircraft winglet were investigated in this paper. Impact damage was firstly inflicted at the center of three pristine winglets by using a drop-weight impact device. The damaged core was restored by filling in the same foam and the damaged skin was repaired by bonding to a three-dimensional scarf patch accompanied with an additional external layer (Doubler). Then, the ultimate load-bearing capacity and failure mechanism of the repaired winglets under static bending moments were studied and compared with the pristine ones. Furthermore, the influence of the stress state of the patch (tension or compression) was discussed by attaching the patch on the top and bottom respectively during testing. The experimental results show that the repaired winglets retain approximately 82% of the load capacity of pristine winglets. Damage occurs along the bolt holes on the composite skin of pristine winglets, while the repaired winglets fail due to the shear crack of the foam and debonding between the foam core and the composite skins. Finally, finite element method were used to explore the failure mechanism for repaired and pristine winglets by comparing the stress distributions. In addition, parametric studies were conducted.
机翻摘要
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关键词/主题词
Aircraft winglet;bonded repair;three-dimensional scarf patch;static bending moments;
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