非线性约束的大型旋转火箭瞬态响应模拟

摘要

In this paper,the vibration is considered for a spinning free rocket with large slenderness ration．Dynamic responses of the rocket-launcher coupling system with nonlinear boundary conditions are studied．The rocket is modeled as a varying stiffness flexible rotor．The Launcher is assumed to be a uniform Euler-Beinulli beam．The rocket and launcher are connected by some nonlinear flexible supporting shoes．Transient responses of the rocket are simulated using the numerical integral method during launching phase．Effects of characteristics of the launch system on the rocket’s motion attitude are analyzed．Results of numerical example show that the method has a good accuracy and reliability．%以大长径比、旋转无控火箭为研究对象，探讨弹-架非线性约束系统的发射动力学响应。将火箭模拟为多支承、变刚度柔性转子，发射装置则简化为具有弹性约束的Euler-Bernoulli，二者通过非线性弹性元件相耦联。数值模拟发射过程中的火箭瞬态响应，分析了系统特性对火箭姿态的影响。