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。
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.
出处
《现代防御技术》
2001年第3期27-30,47,共5页
Modern Defence Technology
