空间站姿态控制/动量管理系统设计与仿真  

Design and Simulation of Attitude Control/Momentum Management System of Space Station Using Control Moment Gyroscopes

作　　者：吴忠[1] 赵建辉[1] 

机构地区：[1]北京航空航天大学仪器科学与光电工程学院,北京100083

出　　处：《系统仿真学报》2006年第1期151-154,共4页Journal of System Simulation

基　　金：国家863计划资助项目(2002AA741103)

摘　　要：在空间站姿态控制系统设计中,一般采用控制力矩陀螺(CMG)作为执行机构,并假定控制力矩陀螺具有理想的操纵性能。然而,当多个CMG协调工作时,有可能产生运动奇异,以致不能提供期望的控制力矩。为此,针对空间站姿态控制/动量管理系统的线性化模型,设计了一个线性二次型调节器,并利用计算机仿真的手段分析了CMG操纵性能及其对姿态控制/动量管理系统的影响。仿真结果表明,在典型的干扰力矩作用下,CMG操纵性能良好,没有出现奇异现象。同时,设计的姿态控制/动量管理策略可以连续调节CMG角动量使其存储角动量最小,建立空间站指向和CMG动量管理间的折衷。Control Moment Gyroscopes （CMGs） are often assumed to have ideal steering performance when they are used as actuators in the attitude control system of space station. However, the expected torque can not be produced due to the singularity, which can be encountered when several CMGs work coordinately. Therefore, simulation analysis was made concerning the steering performance of CMGs and their effects after a linear quadratic regulator（LQR） was designed for the attitude control and momentum management system. Simulation results indicate that CMGs have good steering performance and singularities do not appear in the control procedure of the space station with typical disturbances. And also, the LQR control strategy of attitude and momentum can regulate the CMG momentum continuously to minimize the accumulating momentum and establish the tradeoff between the station pointing and the CMG momentum management.

关 键 词：控制力矩陀螺 空间站 姿态控制 动量管理 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]