摘要
为抑制航天器自身结构参数变化和内外扰动对姿态控制精度和姿态稳定度的影响,设计了航天器姿态自抗扰控制器.自抗扰控制器(ADRC)由跟踪微分器(TD)、扩张状态观测器(ESO)和姿态反馈控制器(AFC)3部分组成.跟踪微分器负责安排姿态指令过渡过程,并提取其微分信号.扩张状态观测器(ESO)充分利用姿态敏感器与速率陀螺的量测信息,可对航天器姿态及内部和外部干扰进行观测.姿态反馈控制器则在补偿ESO估计的干扰的同时,实现航天器的姿态控制.与已有研究相比,扩张状态观测器采用复合量测信息对状态估计进行校正,性能较好.而自抗扰控制器只采用一个环路即可实现姿态控制及干扰补偿,结构简单.对某航天器姿态控制系统的仿真结果表明,以上自抗扰控制器是可行的.
In order to attenuate the effects of the parameter variations and disturbances of the spacecrafts on attitude control accuracy and stability,an active disturbance rejection controller （ADRC） is designed.ADRC consists of three parts：tracking differentiator （TD）,extended state observer （ESO） and attitude feedback controller （AFC）.TD smoothes the process of attitude maneuver and provides differential signal of the attitude; ESO estimates the attitude and the disturbances acting on the spacecraft by taking full advantage of the information of the gyros and the attitude sensors; AFC realizes the attitude control of the spacecraft by compensating the disturbances from the ESO.Compared with the relative results,ESO has better performance by adopting the composite measurement information to correct the estimate,and ADRC has simpler structure by adopting only one loop to realize attitude control and disturbance compensation.Simulation results of a certain spacecraft demonstrate that the ADRC of this paper is feasible.
出处
《控制理论与应用》
EI
CAS
CSCD
北大核心
2013年第12期1617-1622,共6页
Control Theory & Applications
基金
国家重点基础研究发展计划("973"计划资助项目(2012CB720003)
国家自然科学基金资助项目(10772011)
关键词
航天器
姿态控制
自抗扰控制器
姿态敏感器
速率陀螺
spacecraft
attitude control
active disturbance rejection controller
attitude sensors
rate gyros
