固体导弹助推段自抗扰制导控制一体化设计方法  

An Active Disturbance Rejection Design Method for Ascent Integrated Guidance and Control of Solid Missiles

作　　者：聂文明 李惠峰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《宇航学报》2017年第11期1177-1185,共9页Journal of Astronautics

基　　金：国家重点研发计划(2016YFB1200100)

摘　　要：针对存在建模误差及外部干扰情况下的固体导弹助推段制导控制一体化(IGC)设计问题,给出一类自抗扰制导控制一体化设计方法。首先考虑质心运动与绕质心运动间的耦合,结合轨迹线性化方法建立了面向控制的固体导弹助推段制导控制一体化设计模型。采用扩张状态观测器(ESO)实时估计系统建模误差与外部干扰,进而基于反步法结合反馈线性化方法,提出一类考虑质心运动与绕质心运动间的耦合作用的自抗扰制导控制一体化设计方法,并通过Lyapunov稳定性理论证明了该制导控制一体化设计方法可保证闭环系统的稳定性,解决了传统制导控制系统分离设计方法无法保证闭环系统稳定性的问题。最后,数值仿真校验了本文所提的助推段自抗扰制导控制一体化(ADRIGC)设计方法的控制性能及抗干扰性能。This paper presents a novel design method of the integrated guidance and control （IGC） for the solid missiles in the ascent phase subject to modeling uncertainties and external disturbances. Firstly, an ascent model considering the coupling between the guidance and control loops is established. Then it is converted to a control oriented ascent IGC design model based on the trajectory linearization method. The extended state observer （ES0） is adopted to timely estimate the modeling uncertainties and external disturbances to make them available for feedback. Based on the backstepping and feedback control methods, an active disturbance rejection based IGC design method is proposed. The stability analysis of the closed-loop system is provided in the framework of the Lyapunov stability theory. Finally, the numerical simulation demonstrates the efficiency and robustness of the proposed active disturbance rejection integrated guidance and control （ADRIGC）.

关 键 词：助推段制导控制一体化模型 制导控制一体化 扩张状态观测器 反步控制 固体导弹 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]