基于自抗扰算法的导弹制导律设计方法  

A Design Method of Missile Guidance Law Based on ADRC Algorithm

作　　者：王德爽[1] 蔡永恒[1] 

机构地区：[1]中国航天空气动力技术研究院第11总体设计部,北京100074

出　　处：《兵工自动化》2013年第5期50-54,共5页Ordnance Industry Automation

摘　　要：针对机动目标的拦截方法所能允许的不确定性变化范围非常有限的问题,提出一种基于自抗扰算法的导弹制导律设计方法。该方法将自抗扰控制思想应用于导弹制导律设计,根据空间弹目追逃模型,设计基于自抗扰控制算法的制导律,运用状态观测器对目标机动参数、随机干扰等各种因素引起的未知扰动进行观测并实时补偿,实现了动态反馈线性化和解耦控制,使视线角速度快速趋于零。仿真结果表明:相比于传统比例导引律,该方法的制导精度高,脱靶量低,制导飞行时间短,制导性能有极大提高。For limit variable range of uncertainty of intercept maneuvering target, active disturbance rejection control （ADRC） is applied to the design of missile guidance law. The method uses ADRC in design of missile guidance law. According to space missile-goal pursuit model, guidance law is designed based on ADRC control algorithm. Unknown disturbances caused by various factors such as target maneuver parameters, random noise and so on were observed and real-time compensation by state observer. Dynamic feedback linearization and decoupling control is achieved and line of sight angular velocity tends to zero quickly： Simulation results show that, compared to the traditional proportional navigation guidance law, guidance precision is higher, miss distance is lower, guided flight time is short, and guided performance is greatly improved.

关 键 词：三维弹目模型 自抗扰控制 状态观测器 扰动补偿 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]