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将导弹弹体弹性变形引起的附加气动力引入导弹刚体运动方程和弹性振动方程,推导出弹性体导弹数学模型,在此基础上引入主动作动力,建立起适合进行主动减振设计的弹性体导弹状态空间模型.针对解耦的刚性子系统设计H∞控制器模拟刚体导弹控制器,针对弹性子系统设计LQR控制器,再考虑耦合项对弹性子系统进行控制器设计,得到主动减振组合控制器.仿真结果验证了所设计的组合控制器在保证弹体运动姿态控制的同时具有较好的减振效果.
The additional aerodynamic force caused by the elastic deformation of the missile projectile is introduced into the rigid body motion equation and the elastic vibration equation of the missile to derive the mathematical model of the elastic missile. Based on this, the active maneuvering force is introduced to establish the elastomeric missile suitable for the active vibration reduction design State space model.Aiming at the decoupled rigid subsystems, a H∞ controller is designed to simulate a rigid-body missile controller, an LQR controller is designed for the elastic subsystems, and then a controller is designed by considering the coupling term of the elastic subsystems to obtain active damping control The simulation results verify that the designed combined controller has good damping effect while ensuring the attitude control of projectile.