指向约束下有限时间航天器姿态重定向控制  

Finite-Time Spacecraft Attitude Reorientation Control Under Pointing Constrains

作　　者：关涛 李彬[1] 武云丽[2] GUAN Tao;LI Bin;WU Yunli(Sichuan University,Chengdu 610065,China;Beijing Institute of Control Engineering,Beijing 100094,China)

机构地区：[1]四川大学,成都610065 [2]北京控制工程研究所,北京100094

出　　处：《空间控制技术与应用》2024年第3期52-59,共8页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(62071317);空间科学技术创新与应用研究“慧研”资助项目(CD2B65B6);空间智能控制技术重点实验室稳定支持基金资助项目(HTKJ2023KL502005)。

摘　　要：针对指向约束下的航天器姿态重定向控制问题,提出一种解析的有限时间滑模控制器.与现有渐进收敛控制算法相比,该算法具有更快的收敛速度.根据姿态机动目标和姿态指向约束建立相应的导航势函数,并在滑模面上引入势函数及其梯度信息,使得航天器机动到目标姿态的过程中可以满足姿态指向约束.为严格保证滑模面外指向约束的可行性,结合滑模函数以及人工势场函数建立了新的李雅普诺夫函数.接着,基于该李雅普诺夫函数和有限时间收敛定理,设计一种控制器以实现指向约束下有限时间航天器姿态重定向控制.数值仿真表明所提控制器可以实现姿态快速收敛并确保航天器姿态指向约束的可行性.An analytical finite-time sliding mode controller is proposed for spacecraft attitude reorientation control under pointing constraints,which has the faster convergence compared with the existing asymptotic convergence control algorithms.Firstly,the navigation potential function is established based on the attitude maneuver target and the attitude pointing constraints.For further,the potential function and its gradient information are introduced on the sliding mode surface such that the attitude pointing constraints are satisfied during spacecraft attitude maneuver.To ensure the feasibility of attitude pointing constraints outside sliding mode surface rigorously,a new Lyapunov function is established by combining the sliding mode function and the artificial potential function.Then,based on the designed Lyapunov function and the finite-time convergence theorem,a controller is designed to achieve finite-time spacecraft attitude reorientation control under attitude pointing constraints.Finally,numerical simulation shows that the proposed controller can achieve fast attitude convergence and ensure the feasibility of the spacecraft attitude pointing constraints.

关 键 词：姿态控制 指向约束 滑模控制 有限时间收敛 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]