带扩张观测器的新型滑模导引律  

A new sliding mode guidance law based on extended state observer

作　　者：王华吉[1] 简金蕾[1] 雷虎民[1] 李解[1] 马卫东[1] 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《固体火箭技术》2015年第5期622-627,共6页Journal of Solid Rocket Technology

基　　金：航空科学基金(20130196004)

摘　　要：在精确制导问题中,为克服目标机动和弹体动态特性对制导精度的影响,建立了平面内的弹目相对运动模型,在此基础上建立考虑导弹动态特性的制导模型;为提高末制导精度,设计了考虑导弹动态特性和目标机动的自适应滑模导引律;为了实现该导引律,利用带有滤波器的扩张观测器估计视线角速率、视线角加速度、目标机动加速度及其变化率等制导信息。仿真结果表明,扩张观测器收敛速度快、估计精度高,且具有较强的抗干扰能力;在不同机动条件下,所设计的考虑导弹动态特性的含扩张观测器的改进滑模控制律相比于比例导引律、增广比例导引律和滑模导引律具有较好的导引性能。To overcome the effect of target maneuvering and dynamic characteristics as guidance accuracy in guidance process,a guidance model with dynamic characteristics considered was firstly established. Based on the model,an adaptive sliding mode guidance law consideriny dynamic characteristics and target maneuvering was designed. Then,an extended observer was used to estimate the guidance message such as the rate of line-of-sight（ LOS）,acceleration of LOS,maneuvering acceleration and acceleration rate of target. The result of simulation shows that the extended observer has fast speed of convergence,high accuracy of estimation and good ability of anti-jamming. The guidance law designed has better guidance performance than that of proportional navigation guidance（ PNG）,augmented proportional navigation guidance（ APNG） and sliding mode guidance（ SMG） in different conditions of target maneuvering.

关 键 词：滑模导引律 扩张观测器 自动驾驶仪 导引精度 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]