期刊文献+

折叠弹翼展开的刚柔耦合动力学分析 被引量:6

Flex-rigid Coupling Dynamics Analysis of Folding Wing Deployment
下载PDF
导出
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。 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.
作者 赵俊锋 刘莉
出处 《弹箭与制导学报》 CSCD 北大核心 2011年第5期141-144,共4页 Journal of Projectiles,Rockets,Missiles and Guidance
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 folding wing dynamic analysis flex-rigid coupling stress recovery Craig-Bampton method
  • 引文网络
  • 相关文献

参考文献6

二级参考文献9

共引文献69

同被引文献48

引证文献6

二级引证文献20

;
使用帮助 返回顶部