基于扩张干扰观测器的带攻击角约束制导律  

Guidance law with impact angle constraints based on extended disturbance observer

作　　者：张皎[1] 杨旭[1] 刘源翔[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《北京航空航天大学学报》2015年第12期2256-2268,共13页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对导弹拦截机动目标时要求限制终端攻击角度的问题,提出了一种基于扩张干扰观测器(EDO)的有限时间收敛制导律.考虑拦截时弹目相对运动关系,将导弹速度的时变、未知的运动目标加速度视为扰动,采用EDO对干扰进行实时的观测和补偿.通过引入快速跟踪微分器解决制导律中所需期望视线角速率无法直接获取的问题.同时,在制导律性能分析中引入了滑模捕捉能力的概念,分别对不同攻击场景和不同运动形式的机动目标进行拦截仿真,结果表明该制导律有良好的制导性能和鲁棒性,并与其他的制导律进行仿真对比,其所需过载小,脱靶量小,易于工程实现.Aimed at the requirement for intercepting maneuvering targets with impact angle constraint,based on the technology of extended disturbance observer（ EDO）,a novel finite-time convergence guidance law was presented. Considering the relative motion between missile and target,the time-varying uncertainty of missile velocity and the unknown target acceleration were regarded as the disturbance,which is estimated and compensated by EDO. The fast tracking differentiator was introduced to solve the immeasurability problem of the desired line of sight angle rate. Moreover,the domain of sliding mode capturability was introduced to the performance evaluation of guidance law. The simulation experiments of different interception scenarios and different forms of maneuvering target were carried out. The simulation results show that the proposed guidance law has good interception performance and robustness,and it is of less missile acceleration and higher guidance accuracy,which is more helpful for the realization in engineering.

关 键 词：末端制导律 攻击角度约束 有限时间收敛 扩张干扰观测器 跟踪微分器 

分 类 号：V488.13[航空宇航科学技术]