基于大星座低轨道卫星差分载波相位测量的导航

Joe J. Khalife, M. Neinavaie, Z. Kassas
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引用次数: 45

摘要

提出了一种利用大星座低地球轨道(LEO)卫星信号差分载波相位进行导航的机会框架。针对整数最小二乘(ILS)问题的复杂度随卫星数量呈指数增长的特点,提出了一种计算效率高的整数模糊度求解算法。以Starlink星座为例,验证了该算法的有效性,将ILS问题的大小减少了60%。为了高效、准确地表征低轨道卫星导航框架的性能,并便于系统参数设计以满足预期的性能要求,推导了巨型星座低轨道卫星方位角和仰角的联合概率密度函数。实验结果显示,一架无人机(UAV)通过该框架仅使用来自两颗Orbcomm LEO卫星的信号进行2.28公里的导航,在2分钟内实现了前所未有的位置均方根误差14.8米。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Navigation With Differential Carrier Phase Measurements From Megaconstellation LEO Satellites
An opportunistic framework to navigate with differential carrier phase measurements from megaconstellation low Earth orbit (LEO) satellite signals is proposed. A computationally efficient integer ambiguity resolution algorithm is proposed to reduce the size of the integer least-squares (ILS) problem, whose complexity grows exponentially with the number of satellites. The Starlink constellation is used as a specific megaconstellation example to demonstrate the efficacity of the proposed algorithm, showing a 60% reduction in the size of the ILS problem. The joint probability density function of the megaconstellation LEO satellites' azimuth and elevation angles is derived for efficient and accurate performance characterization of navigation frameworks with LEO satellites, and to facilitate system parameter design to meet desired performance requirements. Experimental results are presented showing an unmanned aerial vehicle (UAV) navigating for 2.28 km exclusively using signals from only two Orbcomm LEO satellites via the proposed framework, achieving an unprecedented position root mean squared error of 14.8 m over a period of 2 minutes.
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