星敏感器在轨测量误差修正  

Correction of Measurement Errors of Star Sensors in Orbit

作　　者：王燕清 钟金凤 杜伟峰 吴永康 金荷 郑循江 WANG Yanqing;ZHONG Jinfeng;DU Weifeng;WU Yongkang;JIN He;ZHENG Xunjiang(Shanghai Institute of Spaceflight Control Technology,Shanghai 201109,China)

机构地区：[1]上海航天控制技术研究所,上海201109

出　　处：《光子学报》2025年第2期123-133,共11页Acta Photonica Sinica

基　　金：国家自然科学基金(No.62005158)。

摘　　要：星敏感器在轨受到太阳照射角度变化产生的视轴指向漂移误差和光行差等轨道误差,影响了卫星平台姿态确定精度。对星敏感器在轨测量误差进行详细分类,对误差源进行分析,并对误差进行修正。通过探测器参数调节和姿态计算方法优化等方法,星敏感器在轨随机噪声降低为1.35″,其中噪声等效角为0.99″,低频误差为0.91″;通过仿真和试验验证改进星敏感器的热稳定性,对在轨数据进行分析,星敏感器的视轴指向热漂移从7.35″减小到1.11″;最后,通过光行差修正方法对在轨星敏感器进行光行差修正,轨道周期误差减少12.29″。上述在轨测量误差修正方法由星敏感器独立完成且实时输出,无需卫星平台后端处理拟合,对得到高质量的对地观测遥感图像具有很大的工程应用价值,可以满足新一代遥感卫星对高精度高稳定性的需求。To achieve high-precision terrain mapping and centimeter level surface deformation detection for the new generation of remote sensing satellites,it is necessary to improve the quality and accuracy of Earth observation remote sensing images.In addition to improving the resolution of payloads,satellite platforms also need to provide high-precision attitudes.Star sensors are high-precision satellite attitude measurement sensors,whose measurement accuracy directly determines the accuracy of satellite attitude determination.Their measurement accuracy is mainly affected by factors such as measurement noise of star sensors,installation matrix calibration errors,line of sight drift errors caused by changes in solar irradiation angles,thermal deformation of satellite structures,and optical orbit errors.Therefore,it is necessary to classify the in orbit measurement errors of star sensors,and then calculate,analyze,and correct each type of in orbit error.For this purpose,this article introduces a method for correcting in orbit measurement errors of star sensors.By adjusting detector parameters and optimizing attitude calculation methods,the random noise,noise equivalent angle,and low-frequency error of the star sensor can be reduced;to improve the design of star sensors through simulation and experimental verification,the thermal stability ability is improved by isolating the installation of the light shield and main frame,optimizing the structural materials and design,and optimizing the optical lens adjustment method;by calculating the sum of the Earth's revolution speed and satellite motion speed in the coordinate system measured by the star sensor,the angle of optical aberration error is obtained,and the optical aberration correction is performed on the in orbit star sensor.After optimizing the detection parameters,the accuracy of the star sensor's X direction centroid positioning increased by 19.35%and the Y direction centroid positioning accuracy increased by 48.52%.After optimization using dynamic weight algorithm,the

关 键 词：遥感卫星 星敏感器 在轨测量 热变形 误差修正 

分 类 号：V448[航空宇航科学与技术—飞行器设计]