基于零化视线角速率的非线性预测制导律  

Nonlinear predictive guidance law based on zeroing line of sight rate

作　　者：叶继坤 雷虎民[1] 肖增博[1] 李炯[1] 卓启明[2] 

机构地区：[1]空军工程大学导弹学院,三原713800 [2]中国人民解放军驻149厂军代室,上海200245

出　　处：《系统工程理论与实践》2012年第2期411-416,共6页Systems Engineering-Theory & Practice

基　　金：航空科学基金(20090196005)

摘　　要：利用非线性预测控制理论设计了一种零化视线角速率的预测制导律.首先,以弹目视线角速率为反馈项,最小化预测误差为性能指标,基于非线性预测控制理论和最优化理论推导出非线性预测制导律,并对闭环回路的稳定性进行了证明.其次,针对制导律中含有的目标机动项信息,设计了一种基于时间延迟控制理论的滤波算法,并应用于预测制导律,最后仿真考虑到导弹的延迟环节,采用三阶自动驾驶仪模型,验证了设计的制导律能够有效拦截机动目标,与传统比例导引相比,视线角速率变化平稳,克服了末端视线角速率变化过快而导致过载饱和的情况,降低了对执行机构的要求.Based on the continuous time nonlinear control theory approach, a new formulation of predictive guidance law which zeroing the line of sight （LOS） rate is derived. Firstly, the LOS is used as an feedback in the guidance loop, and the minimized predictive error as a performance index, the nonlinear predictive guidance law is proposed based on the nonlinear control theory approach and optimal theory, also the stability of error dynamics is given. Secondly, a new filter algorithm is formulated using the time delay control theory, and the new filter is used to estimate the acceleration information about target in the designed guidance law. Thirdly, considering the missile＇s delay link, the three order autopilot model is used to validate the proposed guidance law, performance of the presented guidance law with conventional proportional guidance law （PNG） is presented and it has been shown that the sight-rate used predictive guidance changes more smooth than PNC, and also it overcomes the overload saturation in the terminal guidance, so the new guidance has a lower requirement for the actuator in some sense.

关 键 词：预测控制 非线性 制导 滤波 时间延迟控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]