摘要
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。
The splitting of sub-warheads causes it difficult to apply traditional attitude dynamics model In this paper, the author analyzes the impact of centroid derivation to build the attitude dynamics model of MIRV. Then a nonlinear state feedback method is applied to solve the attitude coupling problem. In order to optimize the performance of control system, a two-degree of freedom （TOF） muhivariable internal model controller （IMC） is set up. Simulation results show that the coupling of attitude control system has been eliminated. Compared with the original system, the IMC provides the control system better inputtracking performance and interference suppression capacity.
出处
《飞行力学》
CSCD
北大核心
2014年第6期531-535,545,共6页
Flight Dynamics
基金
国家自然科学基金资助(61125306)
关键词
多头分导式导弹
姿态动力学建模
解耦
内模控制
multiple independently targeted reentry vehicle
attitude dynamics model
decoupling
internal model control
