| 用弹性动力学基本分析方法求解导弹
折叠翼展开的动响应 |
| |
| 引用本文： | 谭湘霞,余旭东.用弹性动力学基本分析方法求解导弹
折叠翼展开的动响应[J].现代防御技术,2001,29(3):27-30. |
| |
| 作者姓名： | 谭湘霞 余旭东 |
| |
| 作者单位： | 1. 中国航天机电集团公司二院二部,
2. 西北工业大学, |
| |
| 摘 要： | 用机构弹性动力学的基本方法分析了一种导弹折叠翼展开的动力学问题，详细介绍了运动微分方程的解法，并将计算结果曲线与刚体动力学计算曲线、试验测得的曲线进行比较和分析，证明了该算法的可靠性和可行性。
|
| 关 键 词： | 导弹折叠翼 机构弹性动力学 动态响应 |
| 文章编号： | 1009-086X（2001）03-0027-04 |
| 修稿时间： | 1999年12月20 |
Unfolding Dynamic Analysis of Missile Folding Wing
Using Basic Method of Organization Elastodynamics |
| |
| TAN Xiang xia ,YU Xu dong.Unfolding Dynamic Analysis of Missile Folding Wing
Using Basic Method of Organization Elastodynamics[J].Modern Defence Technology,2001,29(3):27-30. |
| |
| Authors: | TAN Xiang xia YU Xu dong |
| |
| Institution: | TAN Xiang xia 1,YU Xu dong 2 |
| |
| Abstract: | In this paper, the unfolding dynamic problem of the missile folding wing is solved by the basic method of organization elastodynamics.The kinetic differential equation is developed and the solution is found at length.After comparing the calculated curve with rigidity result curve and tested curve, it is demonstrated that this arithmetic is not only reliable but also feasible. |
| |
| Keywords: | Missile folding wing Organization elastodynamics Dynamic response |
| 本文献已被 CNKI 万方数据 等数据库收录！ |
