论文:2012,Vol:30,Issue(5):668-674
引用本文:
贺尔铭, 张钊, 胡亚琪, 张晓辉, 贺元晨. 单轴压缩载荷下夹层梁结构屈曲及皱曲模拟研究[J]. 西北工业大学
He Erming, Zhang Zhao, Hu Yaqi, Zhang Xiaohui, He Yuanchen. In-Depth Study on Buckling and Wrinkling of Foam-Cored Sandwich Beam under Uniaxial Compression Load[J]. Northwestern polytechnical university

单轴压缩载荷下夹层梁结构屈曲及皱曲模拟研究
贺尔铭1, 张钊1, 胡亚琪1, 张晓辉2, 贺元晨3
1. 西北工业大学 航空学院, 陕西 西安 710072;
2. 西安爱生技术集团公司, 陕西 西安 710065;
3. 西安电子科技大学 机电学院, 陕西 西安 710071
摘要:
泡沫夹层结构以其较高的比刚度及比强度特性在航空航天等领域具有巨大的应用潜力,但当夹层结构作为主承力部件承压时可能带来复杂的屈曲及皱曲稳定性问题。文章基于有限元分析软件Ansys,建立了铝面板泡沫夹层梁结构的二维有限元模型,研究了夹层梁结构在单轴压缩载荷下结构临界失稳载荷与屈曲失效模态的内在关系,并分析了芯材厚度、芯材弹性模量等参数对夹层结构稳定性的影响规律。研究结果表明:芯材-面板的厚度比及弹性模量比对夹层结构的屈曲失效模态具有决定性作用,增加芯材厚度及选用较高弹性模量的芯材,可有效提高泡沫夹层结构的临界失稳载荷,文中研究结果可为泡沫夹层结构的优化设计及工程应用提供理论依据。
关键词:    泡沫夹层梁结构    屈曲    皱曲    稳定性    有限元分析   
In-Depth Study on Buckling and Wrinkling of Foam-Cored Sandwich Beam under Uniaxial Compression Load
He Erming1, Zhang Zhao1, Hu Yaqi1, Zhang Xiaohui2, He Yuanchen3
1. College of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Xi'an ASN Technology Group Co.,Ltd, Xi'an 710065, China;
3. School of Electronical & Machanical Engineering, Xidian University, Xi'an 710071, China
Abstract:
The foam-cored sandwich structure is used widely in the fields of aeronautics and aerospace for havingthe advantages of higher stiffness ratio and strength ratio.The main propose of this paper is to explore the stabilityproblem of sandwich structure used in the UAV (Unmanned Aerial Vehicle), in which the thick or soft core usuallyleads to the short-wave buckling mode, namely wrinkling.Sections 1 and 2 of the full paper explain and evaluateour study mentioned in the title, which we believe gives some in-depth results.The core of sections 1 and 2 consistsof: (1) in order to simulate the overall buckling and wrinkling of the sandwich beam subjected to uniaxial compres-sion load, a two-dimensional finite element model of foam-cored sandwich beam with aluminum face-sheets was de-veloped in Ansys software; (2) the critical instability load, the buckling/wrinkling control mode, and the inherentrelation between them were calculated and analyzed based on the model; (3) the simulation studies were carriedout to investigate the influences of the main structural parameters on the stability of the sandwich beam, such as thecore thickness, the core elastic modulus and the thickness ratio of core-to-sheet.The research results, given inFigs.4 though 7 and Tables 2 and 4, and their analysis show preliminarily that: (1) the critical instability load offoam-cored sandwich beam increases with increasing core thickness and elastic modulus; (2) the thickness ratiand elastic modulus ratio of core-to-sheet are key parameters to determine which kind of three instability modes fi-nally occurs, e.g.overall buckling, symmetricalwrinkling and antisymmetrical wrinkling.Section 3 gives our pre-liminary conclusions in more detail with some suggestions for optimization design and engineering application of thefoam-cored sandwich structure.
Key words:    beams and girders    computer simulation    computer software    mathematical models    finite element method    sandwich structures    schematic diagrams    stability    stiffness    unmanned aerial vehicles (UAV);critical instability load    foam-cored sandwich beam    instability modes   
收稿日期: 2011-11-01     修回日期:
DOI:
基金项目: 教育部博士点基金(20116102110002);西北工业大学爱生创新基金(2011CX08)资助
通讯作者:     Email:
作者简介: 贺尔铭(1964-),西北工业大学教授,主要从事飞行器结构动力学分析及优化设计、振动及稳定性控制等研究。
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