| 引用本文: | 陈小前,冉德超,曹璐.面向集群飞行的微小卫星姿态容差估计与快速精细控制方法[J].控制理论与应用,2023,40(12):2247~2256.[点击复制] |
| CHEN Xiao-qian,RAN De-chao,CAO Lu.Attitude state tolerance estimation and fastly precise control of microsatellite for swarm flying[J].Control Theory and Technology,2023,40(12):2247~2256.[点击复制] |
|
| 面向集群飞行的微小卫星姿态容差估计与快速精细控制方法 |
| Attitude state tolerance estimation and fastly precise control of microsatellite for swarm flying |
| 摘要点击 647 全文点击 284 投稿时间：2023-05-13 修订日期：2023-12-06 |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| DOI编号 10.7641/CTA.2023.30323 |
| 2023,40(12):2247-2256 |
| 中文关键词 微小卫星 执行器受限 干扰抑制 中心误差熵 厚尾非高斯噪声 精细补偿 预定时间控制 |
| 英文关键词 microsatellite actuator constraint disturbance rejection centered error entropy heavy-tailed non-gaussian noise precise compensation predefined-time control |
| 基金项目 国家自然科学基金项目(11972373)资助. |
|
| 中文摘要 |
| 针对微小卫星集群执行空间非合作目标操控等任务时对单星自身姿态的确定与快速控制问题, 本文提出
了一种容差估计与快速精细控制方法. 该容差估计方法设计了一种鲁棒性强的中心误差熵稀疏高斯埃尔米特求积
滤波器, 实现了厚尾非高斯测量噪声作用下的姿态高精度估计. 此外, 该方法基于一种新的预定时间姿态跟踪精细
控制器设计而成, 在预定时间内精确估计并精细补偿了姿态动力学模型误差, 并在执行器控制能力受限条件下实现
了对高动态强时变姿态轨迹的预定时间跟踪控制, 率先同时解决了执行器能力受限与姿态预定时间控制问题. 将该
方法应用于某型微小卫星姿态控制系统设计, 仿真结果表明该方法能显著地提高姿态估计精度与姿态跟踪控制速
率. |
| 英文摘要 |
| A state tolerance estimation and fastly precise control approach is presented for attitude determination and
control problem of microsatellite in swarm flying with severe modeling error. In this approach, a scattered Gauss-Hermite
quadrature filter is first developed based on the centered error entropy. Applying this filter, the attitude state is estimated
with high accuracy and great robustness to modeling error and heavy-tailed non-Gaussian noise. Moreover, a disturbance
observer-based predefined-time attitude tracking controller is designed. The disturbance is precisely estimated and compensated within the predefined time. The closed-loop attitude tracking control system governed by this controller is proved to
be predefined-time stable. The desired time-varying attitude trajectory is followed with zero error after that predefined time.
The predefined time control problem and the actuator constraint problem are simultaneously solved. Using this approach
to a microsatellite attitude control system design, simulation results are given to demonstrate that the attitude estimation
accuracy and attitude control precision as well as convergence rate can be significantly improved by the presented approach. |