基于前置反馈补偿的火箭靶弹解耦方法
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摘要
针对基于插值法计算的解耦方法的反馈增益精度不高,以及采用非线性解耦算法需要的模型精度高,计算量大的问题,提出了基于前置反馈补偿的火箭靶弹解耦方法。该解耦方法在靶弹运动学和控制频域模型基础上,将开环传递函数矩阵分解为运动学耦合和控制耦合,通过引入一个预补偿器,使得运动和控制耦合的传递函数矩阵是对角占优的,便可以将补偿后的俯仰、偏航通道进行单独设计,进而实现靶弹姿态和过载解耦控制系统的设计。仿真结果表明,采用前置反馈补偿解耦方法有效解决了旋转靶弹俯仰和偏航通道之间的耦合效应,并且具有解耦器结构简单,动态响应性能好等优点。
For the decoupling method based on interpolation is not accurate, and the nonlinear decoupling algorithm requires high precision and large computational complexity, a decoupling method of target missiles based on pre-feedback compensation was proposed. Based on the dynamics of target missiles and control frequency domain model, the open-loop transfer function matrix is decomposed into kinematic coupling and control coupling. By introducing a pre-compensator, the diagonal of kinematic and control coupling's transfer function matrix was dominant, and then the compensated pitch and yaw channels could be separately designed to realize the design of the missiles attitude and overload decoupling control system. The simulation results showed that the pre-feedback compensation decoupling method effectively solved the coupling effect between the pitch and yaw channels of the rotating missiles, and had the advantages of simple decoupler structure, good dynamic response performance, etc. and also had certain guiding significance in engineering.
For the decoupling method based on interpolation is not accurate, and the nonlinear decoupling algorithm requires high precision and large computational complexity, a decoupling method of target missiles based on pre-feedback compensation was proposed. Based on the dynamics of target missiles and control frequency domain model, the open-loop transfer function matrix is decomposed into kinematic coupling and control coupling. By introducing a pre-compensator, the diagonal of kinematic and control coupling's transfer function matrix was dominant, and then the compensated pitch and yaw channels could be separately designed to realize the design of the missiles attitude and overload decoupling control system. The simulation results showed that the pre-feedback compensation decoupling method effectively solved the coupling effect between the pitch and yaw channels of the rotating missiles, and had the advantages of simple decoupler structure, good dynamic response performance, etc. and also had certain guiding significance in engineering.
引文
[1]周伟.旋转弹动态稳定性与鲁棒变增益控制[D].北京:北京理工大学,2016:5-10.
[2]袁天保,刘新建,秦子增.自旋弹道导弹运动学与控制[J].宇航学报,2006,27(2):217-221.
[3]陈罗婧,刘莉,于剑桥.双通道控制旋转导弹自动驾驶仪回路的数学变换及其耦合性分析[J].北京理工大学学报,2007,27(10):847-850.
[4]臧月进,陈欣,张民.基于μ综合的空空导弹驾驶仪增益调度方法研究[J].兵器装备工程学报,2017(10):133-136.
[5]李越群,王建.典型空空导弹弹性伺服控制系统稳定性研究[J].兵器装备工程学报,2018,39(5):35-38.
[6]李玉林,李晅,杨树兴.过载自动驾驶仪分析研究[J].战术导弹技术,2008(5):63-68.
[7]钱杏芳,林瑞熊,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2016:64-68.
[8]张泓,郭正玉.基于粒子群优化算法的旋转导弹姿态修正策略[J].兵器装备工程学报,2017(1):32-35.
[9]李永亮.十字型鸭翼布局旋转弹控研究[D].南京:南京航空航天大学,2013:39-40.
[10]FAN Shipeng,LIN Defu,LU Yulong.Research and simulation of rolling missile's control system[J].Computer Science and Automation Engineering,2011(1):195-198.
[2]袁天保,刘新建,秦子增.自旋弹道导弹运动学与控制[J].宇航学报,2006,27(2):217-221.
[3]陈罗婧,刘莉,于剑桥.双通道控制旋转导弹自动驾驶仪回路的数学变换及其耦合性分析[J].北京理工大学学报,2007,27(10):847-850.
[4]臧月进,陈欣,张民.基于μ综合的空空导弹驾驶仪增益调度方法研究[J].兵器装备工程学报,2017(10):133-136.
[5]李越群,王建.典型空空导弹弹性伺服控制系统稳定性研究[J].兵器装备工程学报,2018,39(5):35-38.
[6]李玉林,李晅,杨树兴.过载自动驾驶仪分析研究[J].战术导弹技术,2008(5):63-68.
[7]钱杏芳,林瑞熊,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2016:64-68.
[8]张泓,郭正玉.基于粒子群优化算法的旋转导弹姿态修正策略[J].兵器装备工程学报,2017(1):32-35.
[9]李永亮.十字型鸭翼布局旋转弹控研究[D].南京:南京航空航天大学,2013:39-40.
[10]FAN Shipeng,LIN Defu,LU Yulong.Research and simulation of rolling missile's control system[J].Computer Science and Automation Engineering,2011(1):195-198.