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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Research on angles-only/SINS/CNS relative position and attitude determination algorithm for a tumbling spacecraft
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Research on angles-only/SINS/CNS relative position and attitude determination algorithm for a tumbling spacecraft

机译：翻滚航天器的仅角度/ SINS / CNS相对位置和姿态确定算法研究

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In this paper, the relative navigation technique of final approach phase for a tumbling target spacecraft is studied and exploited. It is assumed that the tumbling target is in failure or out of control and there is no good a priori rotation rate information. The Euler's rotational dynamics is used to propagate the target angular velocity, and the unknown inertia parameter circumstance is also considered. The chaser spacecraft is equipped with three strapdown gyros and accelerometers and a star sensor that determine the absolute motion parameters, and an optical camera that measures relative azimuth and elevation angles to the target spacecraft. On the basis of the rotational and translational motions of both spacecrafts, an angles-only/strapdown inertial navigation system/celestial navigation system navigation filter is designed. Simulation results indicate that the proposed algorithm can accurately estimate the relative position, velocity, and attitude between two spacecrafts and compensate the biases of the gyros and accelerometers.
机译：本文研究并利用了翻滚目标航天器最后进近阶段的相对导航技术。假定翻滚目标处于故障或失控状态，并且没有良好的先验旋转速率信息。欧拉的旋转动力学用于传播目标角速度，并且还考虑了未知的惯性参数情况。追赶者航天器配备了三个捷联陀螺仪和加速计以及一个确定绝对运动参数的星型传感器，以及一个光学相机，用于测量与目标航天器的相对方位角和仰角。基于两个航天器的旋转和平移运动，设计了仅角度/捷联惯性导航系统/天体导航系统导航滤波器。仿真结果表明，所提算法能够准确估计两个航天器之间的相对位置，速度和姿态，并能补偿陀螺仪和加速度计的偏差。

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