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弹箭与制导学报 >

2011 , Vol. 31 >Issue 5: 141 - 144

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.05.046

弹道与气动力技术

折叠弹翼展开的刚柔耦合动力学分析

  • 赵俊锋 ,
  • 刘莉
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赵俊锋(1984-),男,山西人,博士研究生,研究方向:飞行器结构设计与分析。

收稿日期: 2011-01-16

  网络出版日期: 2025-05-30

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Flex-rigid Coupling Dynamics Analysis of Folding Wing Deployment

  • ZHAO Junfeng ,
  • LIU Li
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Received date: 2011-01-16

  Online published: 2025-05-30

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摘要

为了更精确的计算折叠弹翼展开的动力学响应,基于柔性多体系统动力学建模方法建立了弹翼展开的刚柔耦合动力学模型。引入固定界面子结构法并作适当修正来描述弹翼,有效考虑了边界处的效应,提高了计算的精度,并可使用模态应力恢复的方法得到弹翼的动应力。以某导弹折叠翼为例进行展开动力学分析,结果表明了该建模方法的有效性。

关键词： 折叠弹翼; 动力学分析; 刚柔耦合; 应力恢复; 固定界面子结构法

本文引用格式

赵俊锋 , 刘莉 . 折叠弹翼展开的刚柔耦合动力学分析[J]. 弹箭与制导学报, 2011 , 31(5) : 141 -144 . DOI: 10.15892/j.cnki.djzdxb.2011.05.046

Abstract

In order to obtain more accurate dynamics response of folding wing, flexible multi-body system method was employed to build the flex-rigid coupling dynamics analysis model. The Craig-Bampton method was modified to describe the flexible wing. Therefore, the boundary effects could be taken into account easily, and the calculation precision was improved. Also, the time varying stress could be gained by means of the modal stress recovery. A given folding wing was analyzed as an example, and the results demonstrated the validity of this method.

Key words： folding wing; dynamic analysis; flex-rigid coupling; stress recovery; Craig-Bampton method

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参考文献

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