引用本文:刘岩,曹璐,秦开宇,肖冰,施孟佶,李维豪.分布式航天器编队约定时间姿轨耦合协同控制[J].控制理论与应用,2024,41(5):829~838.[点击复制]
LIU Yan,CAO Lu,QIN Kai-yu,XIAO Bing,SHI Meng-ji,LI Wei-hao.Appointed-time attitude-orbit coupling control for distributed spacecraft formation[J].Control Theory and Technology,2024,41(5):829~838.[点击复制]
分布式航天器编队约定时间姿轨耦合协同控制
Appointed-time attitude-orbit coupling control for distributed spacecraft formation
摘要点击 3935  全文点击 289  投稿时间：2022-07-04  修订日期：2024-03-01
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DOI编号  10.7641/CTA.2023.20595
  2024,41(5):829-838
中文关键词  航天器编队飞行  姿轨耦合控制  预设性能控制  约定时间控制  航天器队形重构
英文关键词  spacecraft formation flying  attitude and orbit coupled control  prescribed performance control  appointedtime control  spacecraft formation reconfiguration
基金项目  国家自然科学基金项目(11972373), 四川省科技厅项目(2022JDR0107, 2020YJ0044, 2021YFG0131)
作者单位E-mail
刘岩 电子科技大学航空航天学院 liuyan1631998@163.com 
曹璐* 军事科学院国防科技创新研究院 caolu_space2015@163.com 
秦开宇 电子科技大学航空航天学院  
肖冰 西北工业大学自动化学院  
施孟佶 电子科技大学航空航天学院  
李维豪 电子科技大学航空航天学院  
中文摘要
      针对具有参数不确定性、外部扰动和预设性能需求的航天器编队约定时间姿轨耦合控制问题, 本文基于预设性能控制方法提出了一种低复杂度的约定时间编队姿轨耦合协同控制器, 使得航天器在设定时间内形成编队, 且编队误差满足预设的各种性能指标. 首先, 通过结合有限时间稳定概念引入一种约定时间性能函数, 其系统稳定时间可以由使用者任意设定; 然后, 把约定时间性能函数与预设性能控制方法结合起来, 提出了不依赖航天器质量和转动惯量等信息的约定时间编队协同控制器, 保证了编队状态量的收敛性能和收敛时间, 并使用李雅普诺夫理论证明了其稳定性. 最后, 通过仿真验证了该控制方案的有效性
英文摘要
      This paper addresses the problem of appointed-time attitude and orbit coupled control for distributed spacecraft formation with parameter uncertainties, external disturbances and requirements of prescribed performance. A low complexity cooperative controller was proposed based on the prescribed performance control method, which realized the spacecraft formation flying within the set time and the formation errors met the preset performance indexes. Firstly, an appointed-time performance function that can arbitrarily set the stability time of the system is introduced by using the concept of finite time stability. Secondly, by combining the appointed-time performance function with the prescribed performance control method, a appointed-time cooperative controller is designed to ensure the transient performance and the steady performance and finite-time stability of spacecraft formation control system. And the controller is independent of spacecraft mass and moment of inertia. Finally, the Lyapunov stability theorem is applied to prove the stability of the control system, and numerical simulation results show the effectiveness of the control law.