高超声速飞行器多层次结构强度分析方法

doi:10.7527/S1000-6893.2015.0262

固体力学与飞行器总体设计

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高超声速飞行器多层次结构强度分析方法

梁珩¹, 曾建江¹, 易礼毅², 童明波¹

1. 南京航空航天大学飞行器先进设计技术国防重点学科实验室, 南京 210016;
2. 株洲时代新材料科技股份有限公司, 株洲 412007

收稿日期:2014-11-04 修回日期:2015-09-25 出版日期:2016-02-15 发布日期:2015-09-30
通讯作者: 童明波,男,博士,教授,博士生导师。主要研究方向:飞行器结构设计。Tel:025-84896031,E-mail:tongw@nuaa.edu.cn E-mail:tongw@nuaa.edu.cn
作者简介:梁珩,男,博士研究生。主要研究方向:复合材料结构。Tel:025-84892791,E-mail:leunghengh@sina.com;曾建江,男,博士,副教授。主要研究方向:飞行器结构设计。Tel:025-84892791,E-mail:zengjj@nuaa.edu.cn;易礼毅,男,硕士,工程师。主要研究方向:结构强度。Tel:0731-22837949,E-mail:yiliyinuaa@163.com
基金资助:
江苏高校优势学科建设工程资助项目

Multi-level strength analysis approach for hypersonic vehicle

LIANG Heng¹, ZENG Jianjiang¹, YI Liyi², TONG Mingbo¹

1. Ministerial Key Discipline Laboratory of Advanced Design Technology of Aircraft, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Zhuzhou Times New Material Technology Co., Ltd., Zhuzhou 412007, China

Received:2014-11-04 Revised:2015-09-25 Online:2016-02-15 Published:2015-09-30
Supported by:
A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要：

针对高超声速飞行器结构应力损伤问题,采用有限元子模型法对高超声速飞行器结构强度进行分析研究。有限元分析依据模型复杂情况分为3个层次进行:第1层次采用较为稀疏的网格,获得二级子模型边界上各点的位移和力分布;第2层次将二级子模型网格划分细密,并用Fastener单元模拟群钉连接结构,获得较为准确的应力计算结果及钉载分配;第3层次选取钉载最大的部位建立三级子模型,引入渐进损伤子程序对危险部位进行损伤分析。文中采用ABAQUS子模型法,结合Fastener单元及UMAT(User-defined Material Mechanical Behavior)对高超声速飞行器结构强度由整体到局部进行了有限元分析,解决了常规有限元分析法网格多、计算困难等难题。

关键词: 有限元方法, 子模型法, 渐进损伤, 高超声速飞行器, 结构强度

Abstract:

In order to obtain more accurate result of structural stress damage, sub-model method is used to analyze a hypersonic vehicle structure. According to the complexity of the hypersonic vehicle, the procedure of the sub-model method consists of three steps. Firstly, a coarsely meshed model is used for the whole structure to calculate the displacement of the cut-boundary nodes and force distribution. Secondly, a denser mesh is generated for the secondary sub-model and multi-bolt joints are simulated by Fastener which could help to obtain more accurate structural stress and bolt loads distribution. Thirdly, the three-level sub-model is built at the maximum bolt load area. With the subroutine of progressive damage, damage of the laminate is analyzed. With the application of the sub-model method, Fastener and UMAT(user-defined material mechanical behavior), the strength of the hypersonic vehicle structure, from global to local, is analyzed, which proves that the workload could be reduced significantly and the simulation would be more accurate.

Key words: FEM, sub-model method, progressive damage, hypersonic vehicle, structure strength

中图分类号:

V414.1

梁珩, 曾建江, 易礼毅, 童明波. 高超声速飞行器多层次结构强度分析方法[J]. 航空学报, 2016, 37(2): 588-596.

LIANG Heng, ZENG Jianjiang, YI Liyi, TONG Mingbo. Multi-level strength analysis approach for hypersonic vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 588-596.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高超声速飞行器多层次结构强度分析方法

Multi-level strength analysis approach for hypersonic vehicle

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