一种SGCMG系统方向奇异规避操纵律  

A Directional Singularity Avoidance Steering Law for SGCMG System

作　　者：易涛[1] 耿云海[1] 吴宝林[1] YI Tao;GENG Yunhai;WU Baolin(Research Center of Satellite Technology,School of Astronautics,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]哈尔滨工业大学航天学院卫星技术研究所,哈尔滨150001

出　　处：《宇航学报》2023年第10期1586-1592,共7页Journal of Astronautics

基　　金：国家自然科学基金(61873312)。

摘　　要：针对航天器姿态机动中单框架控制力矩陀螺群(SGCMGs)的奇异问题,对于沿欧拉轴机动情况下SGCMGs的方向奇异框架角进行求解,并提出一种新的奇异规避操纵律。首先基于逆投影方法将角动量方向固定的奇异框架角求解问题描述为约束下非线性优化问题进行求解;然后基于方向约束下奇异框架角提出一种方向奇异规避(DSA)操纵律,通过包含奇异参数梯度和误差框架角矢量的零运动项分别规避SGCMG构型的隐奇异和显奇异状态。数值仿真结果表明所提出操纵律能实现无奇异的姿态机动。Considering the singularity problem of single gimbal control moment gyroscope(SGCMG)system during spacecraft attitude maneuvering,the SGCMGs singular gimbal angles with directional angular momentum decided by Euler axis vector of attitude maneuver is obtained,and a novel singularity avoidance steering law is proposed.Firstly,singular gimbal angles with fixed angular momentum direction is converted to solutions of a constrained nonlinear optimization problem basing on inverse mapping method.Then,a directional singularity avoidance(DSA)steering law,in which null motion about singular measurement parameter and error gimbal angles are designed to avoid hyperbolic and elliptic singularity respectively,is proposed.Finally,numerical simulations demonstrate that the proposed steering law can avoid singularity during attitude maneuver.

关 键 词：控制力矩陀螺 姿态机动 奇异规避 操纵律 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]