基于平均方法的三体绳系系统末端星体姿态控制  

Attitude Control of End Satellites in the Three-body Tethered System Based on the Averaging Method

作　　者：张莹 王长青[1] ZABOLOTNOV Yuriy ISHKOV Sergei 高辛 ZHANG Ying;WANG Changqing;ZABOLOTNOV Yuriy;ISHKOV Sergei;GAO Xin(School of Automation,Northwestern Polytechnical University,Xi’an 710129,China;Samara National Research University,Samara 443086,Russia;Academy of Aerospace Liquid Propulsion Technology,Xi’an 710100,China)

机构地区：[1]西北工业大学自动化学院,西安710129 [2]萨马拉国家研究型大学,萨马拉443086 [3]航天推进技术研究院,西安710100

出　　处：《宇航学报》2024年第8期1261-1268,共8页Journal of Astronautics

基　　金：中央高校基本科研业务费专项资金资助(D5000220031);陕西省国际科技合作计划项目-重点项目(2023-GHZD-32)。

摘　　要：针对三体绳系卫星系统展开过程星体姿态稳定问题,提出了动力学分析解与控制器设计相结合的控制策略。通过对三体绳系卫星系统中子星姿态振动的动力学方程应用平均方法,获得末端星体姿态振动的解析解,为控制器设计奠定了基础。基于化简后的动力学方程设计了一种滑模控制律来抑制子星姿态振动,并利用李雅普诺夫理论证明了闭环系统的渐近稳定性。通过仿真实验验证了所提出方法的可行性和有效性,仿真结果不仅证明了理论分析解的准确性,还验证了控制器的有效性。A control strategy combining the analytical solution of the dynamics and the controller design is proposed for solving the problem of star attitude stabilization during the deployment process of a three-body tethered satellite system.By applying averaging methods to the dynamic equations governing subsatellite attitude oscillations in a threebody tethered satellite system,analytical solutions for end satellites attitude oscillations are obtained,laying the groundwork for controller design.A sliding mode control law is developed based on the simplified dynamic equations to suppress subsatellite attitude oscillations,and the stability of the closed-loop system is theoretically proven using Lyapunov theory.The feasibility and effectiveness of the proposed method are validated through simulation experiments.Simulation results not only affirm the accuracy of the theoretical analytical solutions but also validate the efficacy of the controller.

关 键 词：绳系卫星系统 卫星姿态 平均方法 滑模控制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]