摘要
随着遥感卫星观测能力的逐步提升,对卫星敏捷机动能力提出了更高的要求。针对敏捷卫星大角度姿态机动问题,以6个单框架控制力矩陀螺(SGCMG)组成五棱锥构型的姿态控制系统执行机构,在构建敏捷卫星姿态运动数学模型以及设计SGCMG系统操纵律的基础上,对卫星绕Euler轴进行姿态机动的角轨迹进行规划,并设计了一种基于误差四元数与误差角速度的变结构控制器。仿真及在轨验证结果表明,该控制器能够完成规划轨迹的良好跟踪且具有较强的鲁棒性,研究成果对敏捷卫星姿态控制系统的设计具有重要的参考意义。
With the gradual improvement of the observation capability of space-based remote sensing satellites,higher requirements are put forward for the agile maneuverability of satellites.In order to solve the problem of large angle attitude maneuver of agile satellite,a pentagon configuration composed of six single gimbal control moment gyroscope(SGCMGs)is used as the actuator of attitude control system.Based on the mathematical model of attitude motion of agile satellite and the control law of SGCMG system,the angular trajectory of attitude maneuver around Euler axis is planned and designed.A variable structure controller based on error quaternion and error angular velocity is proposed.The simulation results show that the controller can track the planned trajectory well and has strong robustness.The research results have important reference significance for the design of the attitude control system of agile satellite.
作者
梁健
眭晓虹
赵阳
蔡娅雯
张和芬
LIANG Jian;SUI Xiao-hong;ZHAO Yang;CAI Ya-wen;ZHANG He-fen(Beijing Institute of Spacecraft System Engineering,Beijing 100094;Qian Xuesen Laboratory of Space Technology,Beijing 100094)
出处
《导航与控制》
2020年第2期59-66,共8页
Navigation and Control
基金
国家自然科学基金(编号:41501364)。
关键词
敏捷卫星
单框架控制力矩陀螺
轨迹规划
变结构控制器
鲁棒性
奇异状态
agile satellite
single gimbal control moment gyroscope(SGCMG)
trajectory planning
variable structure controller
robustness
singular state
