复合控制导弹反步滑模IGC自适应设计方法  

Adaptive integrated guidance and control backstepping sliding mode design for blended control missile

作　　者：夏川 董朝阳[1] 王青[2] 程昊宇 XIA Chuan;DONG Chaoyang;WANG Qing;CHENG Haoyu(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;School of Automation Science and Electrical Engineering,Beihang University,Beijing 100191,China;School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]北京航空航天大学自动化科学与电气工程学院,北京100191 [3]西北工业大学航天学院,陕西西安710072

出　　处：《系统工程与电子技术》2018年第10期2325-2333,共9页Systems Engineering and Electronics

基　　金：国家自然科学基金(61374012);航空科学基金(2016ZA51011)资助课题

摘　　要：针对直接力/气动力复合控制导弹,基于扩张状态观测器和反步终端滑模控制,提出一种制导与控制一体化设计方法。通过对系统不确定性进行观测,并设计自适应律补偿观测误差,实现系统对复合干扰的抑制。随后引入虚拟控制力矩的概念,规避了直接在控制器中求解控制量,基于梯度下降法和混合整数线性规划提出一种自适应控制分配策略,充分利用系统已有信息,解决控制量分配实时性要求和精度要求的矛盾。最后通过数值仿真证明,所提出的综合设计方法能够在系统存在内外扰动时,保证系统收敛且使得控制量减小,制导精度提高。Based on extended state observer and backstepping terminal sliding mode control,an integrated guidance and control design is proposed for dual-control missiles.An adaptive compensation law is designed to implement the error of observation,and suppress the interfere due to the uncertainty of the system.Then the concept of virtual control torque is introduced to avoid direct solving of the controller.An adaptive control allocation method based on the gradient descent method and the mixed integer programming method which makes full use of the information of the system is proposed to resolve contradiction between real-time requirement and precision requirement.Finally,the simulation results show that the proposed integrated design method can reduce the control quantity,and improve the guidance accuracy when the system is influenced by internal and external disturbances.

关 键 词：制导控制一体化 扩张状态观测器 反步终端滑模 自适应补偿 虚拟控制力矩 自适应控制分配 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]