敏捷卫星姿态机动的非线性模型预测控制

范国伟; 常琳; 戴路; 徐开; 杨秀彬

doi:10.3788/OPE.20152308.2318

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敏捷卫星姿态机动的非线性模型预测控制

微纳技术与精密机械 | 更新时间：2020-08-12

- 敏捷卫星姿态机动的非线性模型预测控制
- Nonlinear model predictive control of agile satellite attitude maneuver
- 光学精密工程 2015年23卷第8期页码：2318-2327
- 作者机构：
  
  中国科学院长春光学精密机械与物理研究所小卫星技术国家地方联合工程研究中心, 吉林长春 130033
- 作者简介：
- 基金信息：
  
  吉林省青年基金资助项目(No.201201010)();军口863项目(No.2014AA7044030)()
- DOI：10.3788/OPE.20152308.2318
  中图分类号： V448.22
- 收稿日期：2014-05-18，
  
  修回日期：2014-07-12，
  
  纸质出版日期：2015-08-25
- 稿件说明：
移动端阅览
范国伟, 常琳, 戴路等. 敏捷卫星姿态机动的非线性模型预测控制[J]. 光学精密工程, 2015,23(8): 2318-2327

FAN Guo-wei, CHANG Lin, DAI Lu etc. Nonlinear model predictive control of agile satellite attitude maneuver[J]. Editorial Office of Optics and Precision Engineering, 2015,23(8): 2318-2327
范国伟, 常琳, 戴路等. 敏捷卫星姿态机动的非线性模型预测控制[J]. 光学精密工程, 2015,23(8): 2318-2327 DOI： 10.3788/OPE.20152308.2318.

FAN Guo-wei, CHANG Lin, DAI Lu etc. Nonlinear model predictive control of agile satellite attitude maneuver[J]. Editorial Office of Optics and Precision Engineering, 2015,23(8): 2318-2327 DOI： 10.3788/OPE.20152308.2318.

摘要

针对以金字塔构型控制力矩陀螺(CMG)为执行机构的敏捷小卫星开展了先进机动控制算法的研究。在考虑控制力矩陀螺力矩约束及增量约束情况下

设计了基于非线性模型预测控制(NMPC)方法的卫星姿态快速机动控制律及操纵律。通过多种仿真分析了控制器设计参数变化对卫星姿态机动的影响

并与终端滑模控制方法进行了比较。实验结果表明

增大跟踪性能加权矩阵或延长预测时域均可以提高卫星姿态机动速度

缩短卫星姿态机动时间。设计的控制方法能够使卫星姿态在18s内实现40°的大角度快速机动

姿态指向精度和稳定度分别为0.01°和0.04(°)/s

与终端滑模控制方法相比

机动速度及稳态性均得到提高。本文方法为敏捷小卫星的在轨应用方式提供了理论支撑。

Abstract

By taking a pyramid configuration Control Moment Gyro(CMG) as the actuator

an advanced maneuver control algorithm was explored. In consideration of the constraint or incremental constraint of control torque for the CMG

the control law and manipulation law for the satellite attitude fast maneuver were designed based on the Nonlinear Model Predictive Control (NMPC) method

and the impact of satellite attitude maneuver controller parameters on tracking performance was analyzed by different simulations. The simulation results indicate that increasing tracking performance weighting matrix and lengthening predicting time domain

the satellite attitude maneuver speed can be improved and the maneuver time can be shortened. The designed control method can achieve 40°attitude maneuver in the 18 s

and the corresponding pointing accuracy and stability are 0.01°and 0.04(°)/s

respectively. Simulation results were also compared with that the terminal sliding-mode control method

and it shows that the control performance of satellite attitude maneuver has been improved. The proposed control method in this paper provides a theoretical support for the in-orbit applications of agile small satellites.

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references

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