| SINS辅助的星敏感器在线标定方法 |
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| 引用本文： | 谷丛,刘洋,吴成智,肖波,林建华.SINS辅助的星敏感器在线标定方法[J].导航与控制,2020(3):27-32. |
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| 作者姓名： | 谷丛 刘洋 吴成智 肖波 林建华 |
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| 作者单位： | 上海航天控制技术研究所，上海 201109；上海惯性工程技术研究中心，上海 201109,上海航天控制技术研究所，上海 201109；上海惯性工程技术研究中心，上海 201109,上海航天控制技术研究所，上海 201109；上海惯性工程技术研究中心，上海 201109,上海航天控制技术研究所，上海 201109；上海惯性工程技术研究中心，上海 201109,上海航天控制技术研究所，上海 201109；上海惯性工程技术研究中心，上海 201109 |
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| 摘 要： | 航天器在飞行过程中，星敏感器受到外界温度、地面标定精度等因素影响存在较大的安装误差，这将严重影响星敏感器的定姿精度。为提高星敏感器精度，对其安装误差进行严格的在轨实时标定与修正是确保星敏感器测量精度的关键。提出了一种SINS辅助的在线标定方法，将SINS/星敏感器输出的姿态信息进行配准，构建了组合导航系统的Kalman滤波模型。该方法只需航天器在飞行过程中做简单的机动，即可对星敏感器的安装误差角进行实时在线标定。仿真结果表明，采用该标定方法可使星敏感器和惯导的安装误差角的总体估计率达到95%以上，具有较高的工程应用价值。
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| 关 键 词： | 星敏感器 捷联惯导系统 在线标定 姿态精度 |
On-orbit Calibration Method for Star Sensor Aided by SINS |
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| GU Cong,LIU Yang,WU Cheng-zhi,XIAO Bo and LIN Jian-hua.On-orbit Calibration Method for Star Sensor Aided by SINS[J].Navigation and Control,2020(3):27-32. |
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| Authors: | GU Cong LIU Yang WU Cheng-zhi XIAO Bo and LIN Jian-hua |
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| Institution: | Shanghai Institute of Space Flight Control Technology, Shanghai 201109; Shanghai Engineer Research Center of Inertia, Shanghai 201109,Shanghai Institute of Space Flight Control Technology, Shanghai 201109; Shanghai Engineer Research Center of Inertia, Shanghai 201109,Shanghai Institute of Space Flight Control Technology, Shanghai 201109; Shanghai Engineer Research Center of Inertia, Shanghai 201109,Shanghai Institute of Space Flight Control Technology, Shanghai 201109; Shanghai Engineer Research Center of Inertia, Shanghai 201109 and Shanghai Institute of Space Flight Control Technology, Shanghai 201109; Shanghai Engineer Research Center of Inertia, Shanghai 201109 |
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| Abstract: | During flight, because of the external temperature and ground calibration precision, the star sensor has a large installation error, which would seriously affect the attitude precision of the star sensor. In order to improve the accuracy of the star sensor, strict on-orbit calibration and correction of the installation error is the key to ensure the measurement accuracy of the star sensor. In this paper, SINS assisted on-orbit calibration method is proposed, the attitude information of SINS/star sensor is registered, the Kalman filtering model of integrated navigation system is constructed. The installation error of the star sensor can be calibrated online in real time only by the simple shake wing during flight. Simulation results show that this method can make the overall estimated rate of installation error between SINS and star sensor reach above 95%, and has high engineering application value. |
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