采用DGCMG的敏捷卫星姿态/角动量联合控制  

Attitude and Momentum Control of Agile Satellite Using DGCMG

作　　者：崔培玲[1,2,3] 张颖[1,2,3] 

机构地区：[1]北京航空航天大学仪器科学与光电工程学院,北京100191 [2]惯性技术国家级重点实验室,北京100191 [3]新型惯性仪表与导航系统技术国防重点学科实验室,北京100191

出　　处：《电光与控制》2013年第1期49-55,共7页Electronics Optics & Control

基　　金：国家"九七三"项目(2009CB72400101C);国家民用航天预研项目;国家自然基金创新群体(61121003)

摘　　要：研究了采用双框架控制力矩陀螺(Double Gimbaled Control Momentum Gyroscope,DGCMG)的敏捷卫星姿态/角动量联合控制问题,针对DGCMG的饱和奇异问题,提出了基于Lyapunov的姿态/角动量联合控制方法。首先,建立了采用两个平行构型DGCMG的卫星姿态动力学模型,然后根据陀螺的力矩方程,通过可视化分析得出该构型只有内部隐奇异和饱和奇异两类奇异。隐奇异可以通过操纵律进行避免,而饱和奇异只能通过卸载方式来解决。为了避免采用推力器或磁力矩器等卸载方式带来的问题,设计了连续管理角动量的姿态/角动量联合控制器。此外,为了缩短系统的稳定时间,采用Sigmoid函数对控制器的参数选取进行了改进。该控制器完成敏捷卫星快速机动快速稳定任务的同时,还能连续调节角动量,达到姿态控制和角动量管理的折中。数值仿真结果验证了控制器的有效性。Attitude and momentum control for saturation singularity of Double Gimbaled Control and momentum controller based on the theory agile satellite was investigated. In the presence of the Momentum Gyroscope（DGCMG）, we proposed an attitude of Lyapunov. Firstly, the satellite dynamic model with 2 DGCMGs in parallel configuration was constructed, and the singularity visualization analysis of the DGCMGs based on the torque equation was given. There are two kinds of singularity type, inner singularity and saturation singularity. The former can be avoided by using steering law, and the later can only be solved by using the desaturation method. In order to avoid the problem caused by desaturation method, the attitude and momentum controller was given. Besides, sigmoid function was used to modify the controller parameter selection for the purpose of shortening the stabilization time. The controller can accomplish the assignment of rapid maneuver and quick stability while keeping the tradeoff between the attitude control and momentum management. Simulation results are given to show the validity of the proposed controller.

关 键 词：双框架控制力矩陀螺 敏捷卫星 姿态 角动量姿态联合控制器 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计] O221.6[理学—运筹学与控制论]