摘要
针对固定构型的控制力矩陀螺群无法灵活改变其合成角动量包络以适应卫星不同工况的姿态机动需求问题,设计了一种可变构型的控制力矩陀螺群控制方法。建立了可变构型的控制力矩陀螺群的动力学模型;在考虑控制力矩陀螺群框架角速度、高速转子转速以及构型倾角变化速率等多变量下,设计了可变构型的控制力矩陀螺群的操纵律;分析了构型倾角固定和构型倾角可变情形下的控制力矩陀螺群合成角动量包络和奇异状态分布情况。采用可变构型的控制力矩陀螺群进行了卫星多工况姿态敏捷机动控制。数学仿真校验表明,可变构型的控制力矩陀螺控制方法能够实现金字塔构型下不同数目的控制力矩陀螺故障时的卫星三轴敏捷机动控制。
The momentum envelope of fixed skew configuration control moment gyroscopes(CMGs)cannot be changed flexibly to meet the different satellite attitude maneuver requirements.The control method for variable skew configuration CMGs was designed.The dynamic model of the variable skew configuration CMGs was established.Considering multiple control variables,such as gimble rate,high-speed rotor speed and skew angle rate,the steer control law of the variable skew configuration CMGs was designed.The momentum envelope of CMGs and singular state distribution were analyzed.The variable skew configuration CMGs were used to achieve the satellite three-axis attitude agile maneuver control.The simulation results show that the control method for the variable skew configuration CMGs can realize the satellite three-axis attitude agile maneuver control with different number of CMG faults.
作者
张科备
高晶敏
关新
郭子熙
ZHANG Kebei;GAO Jingmin;GUAN Xin;GUO Zixi(Beijing Institute of Control Engineering,Beijing 100190,China;Science and Technology on Space Intelligent Control Laboratory,Beijing 100094,China;School of Automation,Beijing Information Science&Technology University,Beijing 100192,China)
出处
《中国空间科学技术》
EI
CSCD
北大核心
2020年第6期23-32,共10页
Chinese Space Science and Technology
基金
国家杰出青年科学基金项目(61525301)
民用航天技术预先研究项目(D020103)。
关键词
控制力矩陀螺
可变构型
角动量包络
操纵控制
姿态控制
control moment gyroscopes
variable skew configuration
momentum envelope
steer control law
attitude maneuver control
