重复使用运载火箭精确回收滑模动态面控制  

Sliding Mode Dynamic Surface Control in Precise Recovery Phase for Reusable Launch Vehicle

作　　者：钱默抒[1,2] 熊克 王海洋[1] QIAN Mo-shu;XIONG Ke;WANG Hai-yang(State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Electrical Engineering and Control Science,Nanjing Tech University,Nanjing 211816,China)

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [2]南京工业大学电气工程与控制科学学院,南京211816

出　　处：《宇航学报》2018年第8期879-888,共10页Journal of Astronautics

基　　金：江苏省博士后科研资助计划(1701140B);南京工业大学GF科研培育课题(201709)

摘　　要：针对可重复使用运载火箭一子级再入垂直着陆阶段,利用滑模动态面控制(SMDSC)技术设计了一个精确垂直回收控制策略。首先考虑运载火箭的燃料消耗、质心变化及转动惯量摄动等特点,建立运载火箭一子级返回段动力学模型。然后针对范数有界的不确定性和有界连续的未知干扰,设计一个滑模状态观测器和一个自适应参数估计器用于获得其估计值;随后,基于获得的状态估计值和未知参数估计值,设计了一个基于自适应动态面技术的跟踪控制律。最后,通过数值仿真,对比两种不同控制策略下的运载火箭垂直返回姿态角跟踪能力。结果表明,采用本文提出的自适应滑模动态面控制策略具有更好的跟踪效果.A precise vertical recovery control strategy is designed by using the sliding mode dynamic surface control（SMDSC） technology in the reentry landing phase for a reusable launch vehicle. Firstly,the actual dynamic model of the launch vehicle is established,which includes the fuel consumption,the change of the center of mass and the inertia perturbation. Then,a sliding mode state observer and an adaptive parameter estimator are given to obtain the estimated value of the norm bounded uncertainties and disturbances. Subsequently,a dynamic surface tracking control law is proposed based on the derived estimations. Finally,the numerical simulation is carried out to compare with the attitude tracking ability of the vertical return launch vehicle under two different control strategies. The results show that the proposed adaptive sliding mode dynamic surface control strategy has better tracking performance.

关 键 词：运载火箭 滑模观测器 参数估计器 动态面控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]