无角速度测量和饱和输入条件下航天器编队姿态有限时间跟踪控制  

Finite-Time Spacecraft Formation Attitude Tracking Control with Angular Velocity-Free Measurement and Saturation Input

作　　者：关启学[1] 代京[2] 王伟光 姜月秋[1] Guan Qixue;Dai Jing;Wang Weiguang;Jiang Yueqiu(Colleee of Information Science and Engineering,Shenyang Ligong University,Shenyang 110159,China;China Academy of Launch Vehicle Technology,Beijing 100076,China;Rocket Army Engineering of University,Xi'an 710025,China)

机构地区：[1]沈阳理工大学信息科学与工程学院,沈阳110159 [2]中国运载火箭技术研究院,北京100076 [3]火箭军工程大学,西安710025

出　　处：《航空兵器》2020年第4期39-44,共6页Aero Weaponry

基　　金：国家自然科学基金项目(61501307);辽宁省自然科学基金指导计划项目(2019-ZD-0255);辽宁省教育厅高等学校基本科研项目(LG201708);辽宁省兴辽英才计划项目(XLYC1902095);沈阳理工大学重点学科开放基金项目(4771004kfx24)。

摘　　要：针对无角速度测量和饱和输入条件下航天器编队姿态跟踪控制问题,提出一种基于滑模面的有限时间协同控制协议。通过数学转换将未知饱和输入的影响与外部扰动相结合为总扰动,基于航天器的姿态信息,通过所设计的有限时间非线性观测器在线估计未知总扰动,应用所提出的滑模控制协议,实现各航天器姿态跟踪误差的有限时间收敛。数值仿真验证了所提滑模控制协议的有效性。Aiming at the problem of spacecraft formation attitude tracking control under angular velocity-free measurement and saturation input conditions,a finite-time cooperative control protocol based on sliding mode surface is proposed.The influence of unknown saturated input is combined with external disturbance into total disturbance through mathematical transformation.Based on the attitude information of the spacecraft,the unknown total disturbance is estimated online by the designed finite-time nonlinear observer.The proposed sliding mode control protocol is applied to realize the finite time convergence of attitude tracking error of each spacecraft.The numerical simulation results validate the effectiveness of the proposed sliding mode control protocol.

关 键 词：飞行器编队 无角速度测量 饱和输入 有限时间观测器 滑模控制 

分 类 号：TJ760[兵器科学与技术—武器系统与运用工程] V412[航空宇航科学与技术—航空宇航推进理论与工程]