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文中采用有限元方法模拟柔性旋转火箭的空间运动姿态,建立变截面转轴的动力学偏微分方程,给出发射过程中火箭动态响应的数值解.
In this paper, the finite element method is used to simulate the attitude of the flexible rotating rocket and the dynamic partial differential equations are established. The numerical solution of the rocket dynamic response during the launch is given.