| 星敏感器在轨光行差修正方法研究 |
| |
| 引用本文： | 李苗,周连文,何益康,余维,谢任远,沈怡颹.星敏感器在轨光行差修正方法研究[J].导航定位于授时,2018,5(1):60-63. |
| |
| 作者姓名： | 李苗 周连文 何益康 余维 谢任远 沈怡颹 |
| |
| 作者单位： | 上海航天控制技术研究所,上海 200233;上海市空间智能控制技术重点实验室,上海 201109,上海航天控制技术研究所,上海 200233;上海市空间智能控制技术重点实验室,上海 201109,上海航天控制技术研究所,上海 200233;上海市空间智能控制技术重点实验室,上海 201109,上海航天控制技术研究所,上海 200233;上海市空间智能控制技术重点实验室,上海 201109,上海航天控制技术研究所,上海 200233;上海市空间智能控制技术重点实验室,上海 201109,上海航天控制技术研究所,上海 200233;上海市空间智能控制技术重点实验室,上海 201109 |
| |
| 摘 要： | 星敏感器作为目前航天器中最重要的姿态测量敏感器,其精度直接影响航天器姿态测量精度,因此对其误差源进行分析和修正则尤为重要。提出了一种星敏感器在轨光行差修正方法,根据光行差产生的原理和特点,将星敏感器沿探测器X和Y方向产生的光行差误差角巧妙地转换为光行差误差四元数,并直接对输出四元数进行修正,从而为修正星敏感器光行差提供了一种方便简洁的方法。
|
| 关 键 词： | 星敏感器 慢变误差 光行差误差角 光行差误差四元数 光行差修正 |
A Method of Star Sensor Aberration Correction On-Orbit |
| |
| LI Miao,ZHOU Lian-wen,HE Yi-kang,YU Wei,XIE Ren-yuan and SHEN Yi-wei.A Method of Star Sensor Aberration Correction On-Orbit[J].Navigation Positioning & Timing,2018,5(1):60-63. |
| |
| Authors: | LI Miao ZHOU Lian-wen HE Yi-kang YU Wei XIE Ren-yuan and SHEN Yi-wei |
| |
| Institution: | Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China,Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China,Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China,Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China,Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China and Shanghai Institute of Spaceflight Control Technology,Shanghai 200233,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China |
| |
| Abstract: | Star sensor is one of the most important attitude measuring sensors used by the spacecraft. Its precision directly affects the spacecraft attitude measuring precision. Therefore to analyze and modify its error source is particularly important. A method of star sensor aberration correction on-orbit is proposed. According to the principles and characteristics of aberration,the aberration error angle along X and Y directions of sensor are cleverly converted into aberration error quaternions and then can be directly corrected,which provides a convenient and concise method to correct the aberration of star sensor. |
| |
| Keywords: | Star sensor Low frequency error Aberration error Aberration error quaternion Aberration correction |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《导航定位于授时》浏览原始摘要信息 |
| 点击此处可从《导航定位于授时》下载免费的PDF全文 |
|
