Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model
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 m...
| Main Authors: | , , |
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| Format: | Article |
| Language: | zho |
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EDP Sciences
2022-04-01
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| Series: | Xibei Gongye Daxue Xuebao |
| Subjects: | |
| Online Access: | https://www.jnwpu.org/articles/jnwpu/full_html/2022/02/jnwpu2022402p360/jnwpu2022402p360.html |
| _version_ | 1797422290475941888 |
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| author | DING Zhendong LI Hongshuang GUAN Xiaole |
| author_facet | DING Zhendong LI Hongshuang GUAN Xiaole |
| author_sort | DING Zhendong |
| collection | DOAJ |
| description | 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. |
| first_indexed | 2024-03-09T07:30:03Z |
| format | Article |
| id | doaj.art-3c82aa3859c44d86a16a577a3b5743ed |
| institution | Directory Open Access Journal |
| issn | 1000-2758 2609-7125 |
| language | zho |
| last_indexed | 2024-03-09T07:30:03Z |
| publishDate | 2022-04-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | Xibei Gongye Daxue Xuebao |
| spelling | doaj.art-3c82aa3859c44d86a16a577a3b5743ed2023-12-03T06:25:20ZzhoEDP SciencesXibei Gongye Daxue Xuebao1000-27582609-71252022-04-0140236036810.1051/jnwpu/20224020360jnwpu2022402p360Reliability analysis of composite sandwich structure for fuselage skin based on surrogate modelDING Zhendong0LI Hongshuang1GUAN Xiaole2College of Aerospace Engineering, Nanjing University of Aeronautics and AstronauticsCollege of Aerospace Engineering, Nanjing University of Aeronautics and AstronauticsBeijing Institute of Power Machinery, China Aerospace Science and Industry CorporationComposite 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.https://www.jnwpu.org/articles/jnwpu/full_html/2022/02/jnwpu2022402p360/jnwpu2022402p360.htmlsandwich structurereliabilityparametric modelingkrigingsubset simulation |
| spellingShingle | DING Zhendong LI Hongshuang GUAN Xiaole Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model Xibei Gongye Daxue Xuebao sandwich structure reliability parametric modeling kriging subset simulation |
| title | Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model |
| title_full | Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model |
| title_fullStr | Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model |
| title_full_unstemmed | Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model |
| title_short | Reliability analysis of composite sandwich structure for fuselage skin based on surrogate model |
| title_sort | reliability analysis of composite sandwich structure for fuselage skin based on surrogate model |
| topic | sandwich structure reliability parametric modeling kriging subset simulation |
| url | https://www.jnwpu.org/articles/jnwpu/full_html/2022/02/jnwpu2022402p360/jnwpu2022402p360.html |
| work_keys_str_mv | AT dingzhendong reliabilityanalysisofcompositesandwichstructureforfuselageskinbasedonsurrogatemodel AT lihongshuang reliabilityanalysisofcompositesandwichstructureforfuselageskinbasedonsurrogatemodel AT guanxiaole reliabilityanalysisofcompositesandwichstructureforfuselageskinbasedonsurrogatemodel |