| 摘要: |
| 空天飞行器高动态、长航时的运动特性可能导致一体化安装的惯性/天文组合导航系统中星敏感器与惯导间产生安装误差角。设计了一种星敏感器安装误差角动态辨识方法，建立了星敏感器安装误差角模型，设计了基于天文角度观测的星敏感器安装误差角动态辨识方案，分析了不同机动飞行方式下星敏感器安装误差角的可观测度。仿真结果表明，所设计的基于卡尔曼滤波的动态辨识方法能够在飞行器机动过程中快速地对星敏感器安装误差角进行在线标定，对安装误差角的标定值可以达到实际误差值的85%以上，有效地提高了组合导航系统的精度。 |
| 关键词: 空天飞行器 导航系统 星敏感器 安装误差 卡尔曼滤波 动态辨识 |
| DOI： |
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| 基金项目:国家自然科学基金（61673208,61873125,61533009,61533008）；江苏省自然科学基金（BK20181291）；中央高校基本科研业务费专项资金（NZ2019007）；上海航天科技创新基金（SAST2019-085） |
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| On-line Calibration Method for Installation Error of Star Sensor of Aerospace Vehicle |
| AN Jing-ke,XIONG Zhi,WANG Rong,KANG Jun,ZHANG Xin-rui,LIU Jian-ye |
| (Navigation Research Center of Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China) |
| Abstract: |
| The high dynamic and long-endurance movement characteristics of the aerospace vehicles may cause installation error angle between the star sensor and the inertial navigation system in the integrated inertial/celestial integrated navigation system.In this paper, a method for dynamic identification of the installation error angle of a star sensor is designed, the installation error angle model of the star sensor is established, a dynamic identification scheme of the installation error angle of the star sensor based on astronomical angle observation is designed, and the observability of the sensor installation error angle under different maneuvering modes are analyzed.The simulation results show that the designed dynamic identification method based on Kalman filter can quickly calibrate the installation error angle of the star sensor during the maneuver of the aircraft, and the calibration value of the installation error angle can reach 85% of the actual error value. The accuracy of the integrated navigation system is effectively improved. |
| Key words: Aerospace vehicle Navigation system Star sensor Intallation error Kalman filter Dynamic identification |
