天文导航设备水平基准姿态传递技术研究  

Horizontal Reference Attitude Transfer Technology for Celestial Navigation Equipment

作　　者：杜辉[1] DU Hui(92941Troops,PLA,Huludao 125003,China)

机构地区：[1]中国人民解放军92941部队,辽宁葫芦岛125003

出　　处：《光学与光电技术》2024年第4期84-91,共8页Optics & Optoelectronic Technology

摘　　要：天文导航设备水平姿态基准和测星组件分立安装时,受安装结构件温度变化、应力释放等因素的影响,水平姿态基准直接传递至测星组件,并引入安装误差角,对天文导航设备精度有重大影响。针对水平姿态基准和测星组件之间安装误差角的估计问题,设计并推导安装误差估计模型、优化测星组件、设计测星组件和水平姿态基准之间的相对运动策略。以测星组件和水平姿态基准之间三轴陀螺数据之差作为卡尔曼滤波的量测信息,可实现安装误差的有效估计。仿真结果表明:设计合适的模型,以陀螺角速度作为卡尔曼滤波器的量测信息,通过一定的转动策略配合,短时间内便可达到滤波稳定状态,水平安装误差角估计精度优于3.6"、测星组件陀螺零偏估计精度优于0.01°/h。该算法对于天文导航设备水平姿态基准传递至测星组件具有良好的适应性,具有实用价值和研究意义。When the horizontal attitude reference of celestial navigation equipment and the star tracker are installed separately,they are affected by the temperature change of the installation structure,stress release and other factors.The direct transmission of the horizontal attitude reference to the star tracker will introduce an installation error angle,which has a significant impact on the accuracy of celestial navigation.Aiming at the estimation problem of the installation error angle between the horizontal attitude reference and the star tracker,the installation error estimation model is design and derived,the measurement component is optimized,the relative motion strategy between the measurement component and the horizontal attitude reference is designed to determine the component and the horizontal attitude reference.The difference between the three-axis gyro data between the measured component and the horizontal attitude reference is used as the measurement information of the Kalman filtering,which can realize an effective estimation of the installation error.The simulation results show that a suitable model is designed,the angular velocity of the gyro is used as the measurement information of the Kalman filtering,and the stable state of the filter can be achieved in a short time through a certain rotation strategy,and the accuracy of horizontal installation error angle estimation is better than 3.6 arcseconds,and the accuracy of gyro bias estimation is better than 0.01 degrees per hour.Therefore,the algorithm has good adaptability for the transmission of the celestial navigation level attitude reference to the measurement component,and has practical value and research significance.

关 键 词：测星组件 水平姿态基准 天文导航设备 角速度 卡尔曼滤波 

分 类 号：V249.323[航空宇航科学与技术—飞行器设计]