论文部分内容阅读
导弹飞行过程中,子弹头的释放会造成母舱质心位置的改变,常规单弹头导弹的姿态动力学模型已不再适用。详细分析了释放子弹头对导弹母舱姿态运动的影响,基于质心突变对转动惯量矩阵及控制力矩的改变,构建多头分导式导弹母舱姿态动力学数学模型,通过非线性状态反馈实现解耦控制;基于解耦后的系统设计二自由度三变量内模控制器,优化了控制系统性能。理论分析与仿真结果均表明,该设计方法算法简单,易于实现,控制系统具有良好的输入跟踪性能和干扰抑制能力。
During the flight of the missile, the release of the projectile will result in the change of the centroid position of the mother cabin, and the attitude dynamics model of the conventional single-head missile is no longer applicable. Based on the change of mass moment of inertia matrix and control torque, the mathematical model of multi-head submachine missile mast’s attitude dynamics is constructed and decoupled by nonlinear state feedback Control; based on the decoupled system design two degrees of freedom three-variable internal model controller, optimizing the control system performance. Theoretical analysis and simulation results show that the design method is simple and easy to implement, and the control system has good input tracking performance and interference suppression.