摘要
针对现有姿态控制系统检控分离导致姿控系统存在异位控制等突出问题,提出了一种基于磁悬浮控制力矩陀螺的航天器姿态角速率测量方法。建立了基于磁悬浮控制力矩陀螺金字塔构型的动力学模型,根据惯量矩定理分析了基于磁悬浮控制力矩陀螺的航天器测控一体化机理,并通过金字塔构型中3个磁悬浮控制力矩陀螺的联合求解,得到了航天器姿态角速率的解析表达式。仿真结果证明了该方法的有效性和优越性。
For the problem of abnormal position control,which is produced by separation of measure and control,in the existing attitude control system,a spacecraft attitude angular rate method based on magnetically suspended control moment gyroscope is proposed. A dynamic model of magnetically suspended control moment gyroscope with pyramid configuration is established,and the integrated measurement and control mechanism of spacecraft based on magnetically suspended control moment gyroscope is analyzed according to the theorem of inertia moment. An analytical expression of attitude angular velocity is obtained through joint solution of 3 magnetically suspended control moment gyroscopes in pyramid configuration. Simulation results verify the correctness and superiority of this method.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2015年第10期1907-1915,共9页
Acta Armamentarii
基金
国家自然科学基金项目(51475472
61403396)
关键词
控制科学与技术
姿态角速率测量
磁悬浮控制力矩陀螺
惯量矩定理
解析解
control science and technology
measurement of attitude angular rate
magnetically suspended control moment gyroscope
theorem of inertia moment
analytical solution
