基于双框架控制力矩陀螺的航天器动量管理  

Momentum Management of Spacecraft Based on DGCMGs

作　　者：卢松涛[1] 王磊[1] 赵育善[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《上海航天》2011年第1期28-31,36,共5页Aerospace Shanghai

摘　　要：为减小维持大型航天器的姿态稳定和降低能量消耗的动量管理中的扰动力矩对姿态稳定的干扰,设计了周期性抑制滤波器。姿态控制的执行机构采用双框架控制力矩陀螺群(DGCMGs),应用KENNEL操纵率,使航天器执行机构的角动量在本体系的x轴分量和偏航角可达稳定,同时角动量在本体系的z轴分量和滚转角可在较小的范围内振荡。数值仿真结果验证了方案的可行性。In order to decrease the disturbance on the attitude stabilization in the momentum management of the attitude maintain and reduce the energy consumed for the large spacecraft,the period restrained rejector was designed in this paper.The double gimbaled control moment gyros（DGCMGs） were used as the attitude control institution,so that the segment of angle momentum on the x axis and yawing angle could be stabilized,and the segment of angle momentum on the z axis and rolling angle could be oscillated in small range by using KENNEL＇s control law. The numerical simulation results proved the feasibility of the momentum management project.

关 键 词：动量管理 双框架 控制力矩陀螺 KENNEL操纵率 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]