基于剪式控制力矩陀螺的低轨卫星垂轨摆扫姿态控制  

Orbit-Perpendicular Swing Scanning Attitude Control of Low Orbit Satellite Based on Scissored-Pair CMGs

作　　者：曹永奎 廖育荣 倪淑燕 杨新岩 Cao Yongkui;Liao Yurong;Ni Shuyan;Yang Xinyan(Campany of Postgraduate Management,Space Engineering University,Beijing 101416,China;Vocational Education Center,Space Engineering University,Beijing 101416,China;Department of Electronic and Optical Engineering,Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学研究生院,北京101416 [2]航天工程大学职业教育中心,北京101416 [3]航天工程大学电子与光学工程系,北京101416

出　　处：《航天控制》2019年第4期47-53,65,共8页Aerospace Control

基　　金：军队科研项目(1700050400)

摘　　要：针对低轨卫星大范围探测,设计了基于剪式控制力矩陀螺的姿态控制系统。按照2种垂轨摆扫姿态机动轨迹,获得姿态机动的期望姿态。使用剪式安装的控制力矩陀螺作为执行机构,给出框架角速率操纵率,避免出现奇异状况,简化了雅克比矩阵。仿真验证了姿控系统对于大范围探测任务的有效性。Aiming at the wide swath detection task of the LEO satellite,the attitude control system based on scissored-pair control moment gyroscopes is designed.The desired angles of attitude maneuver are obtained according to two kinds of attitude maneuver trajectories.Scissored-pair control moment gyroscopes are selected as the attitude control actuator,and the gyro gimbal angles steer law is given,which avoids the singularity and simplifies the Jacobian matrix.The simulation result verifies the effectiveness of the attitude control system for a wide swath detection tasks.

关 键 词：大范围探测 垂轨摆扫 控制力拒陀螺 框架角操纵律 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]