Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model

被引：0

作者：

Ding Z. ^{[1
]}

Li H. ^{[1
]}

Guan X. ^{[2
]}

机构：

[1] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

[2] Beijing Institute of Power Machinery, China Aerospace Science and Industry Corporation, Beijing

来源：

Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University | 2022年 / 40卷 / 02期

关键词：

Kriging; Parametric modeling; Reliability; Sandwich structure; Subset simulation;

D O I：

10.1051/jnwpu/20224020360

中图分类号：

学科分类号：

摘要：

Composite structures are characterized by multiple source uncertainties in mechanical properties, geometric dimension, etc., and multiple failure modes, which bring challenges to their design and application. In order to explore the reliability analysis method of composite sandwich structures with multi-source uncertainties and multi-failure modes, a parametric finite element model and an acoustic boundary element model were established for deterministic analysis of a fuselage skin sandwich structure. Considering the randomness of the mechanical properties of composite materials and the laminate thickness, the structural reliability models were established for three typical failure modes of sandwich structures: static strength failure, global buckling and vibration noise. In order to reduce the computational effort, the Kriging surrogate models of failure modes were constructed, and the subset simulation method was used to predict the system failure probability of the sandwich structure of fuselage skin. The proposed computational framework provides support and tool for the fine design of composite sandwich structure. © 2022 Journal of Northwestern Polytechnical University.

引用

页码：360 / 368

页数：8

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