太阳观测系统二维指向机构变形误差在轨辨识方法  

On-orbit Identification Method of Deformation Error for Two-dimensional Pointing Mechanism of Solar Observation System

作　　者：王皓[1] 王田野 宋宵含 徐凯 许海玉[1] WANG Hao;WANG Tianye;SONG Xiaohan;XU Kai;XU Haiyu(Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]上海卫星工程研究所,上海201109

出　　处：《航天器工程》2025年第2期75-81,共7页Spacecraft Engineering

摘　　要：太阳观测系统由太阳观测载荷与二维指向机构组成,卫星在轨运行时,二维指向机构变形误差会对太阳观测载荷光轴指向确定精度造成影响。针对这一问题,提出一种变形误差在轨辨识方法。首先,对太阳观测系统内部变形误差传递过程进行数学建模。其次,对数学模型中各坐标系间的变形误差参数给出在轨辨识方法。最后,通过数学仿真进行在轨变形误差模拟、变形误差参数辨识和光轴指向确定精度评估。仿真结果验证了文章提出方法的有效性,研究结果可为其他含二维指向机构的有效载荷提供参考。The solar observation system is composed of a solar observation payload and a two-dimensional pointing mechanism.During on-orbit satellite operation,deformation errors in the two-dimensional pointing mechanism affect the accuracy of optical axis pointing determination for the solar observation payload.Aiming at this problem,an on-orbit identification method of the deformation error is proposed.Firstly,a mathematical model is established for the internal deformation error transmission process within the solar observation system.Secondly,an on-orbit identification method is developed for the deformation error parameters between coordinate systems in the mathematical model.Finally,the on-orbit deformation error simulation,the identification of the deformation error parameters and the accuracy evaluation of the optical axis pointing are carried out by mathematical simulation.The simulation results verify the effectiveness of the proposed method.The research results can provide a reference for other payloads with two-dimensional pointing mechanism.

关 键 词：太阳观测系统 二维指向机构 变形误差 在轨辨识 

分 类 号：V474.24[航空宇航科学与技术—飞行器设计]