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首页> 外文期刊>Mathematical Problems in Engineering >Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS
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Onboard and Real-Time Artificial Satellite Orbit Determination Using GPS

机译：利用GPS确定机载和实时人造卫星轨道

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摘要

An algorithm for real-time and onboard orbit determination applying the Extended Kalman Filter (EKF) method is developed. Aiming at a very simple and still fairly accurate orbit determination, an analysis is performed to ascertain an adequacy of modeling complexity versus accuracy. The minimum set of to-be-estimated states to reach the level of accuracy of tens of meters is found to have at least the position, velocity, and user clock offset components. The dynamical model is assessed through several tests, covering force model, numerical integration scheme and step size, and simplified variational equations. The measurement model includes only relevant effects to the order of meters. The EKF method is chosen to be the simplest real-time estimation algorithm with adequate tuning of its parameters. In the developed procedure, the obtained position and velocity errors along a day vary from 15 to 20 m and from 0.014 to 0.018 m/s, respectively, with standard deviation from 6 to 10 m and from 0.006 to 0.008 m/s, respectively, with the SA either on or off. The results, as well as analysis of the final adopted models used, are presented in this work.
机译：开发了一种使用扩展卡尔曼滤波（EKF）方法进行实时和机载轨道确定的算法。为了确定非常简单但仍相当准确的轨道，进行了分析以确定建模复杂度与准确度的适当性。发现达到几十米的精确度水平的最小一组待估计状态至少具有位置，速度和用户时钟偏移分量。通过几个测试评估了动力学模型，这些测试涵盖了力模型，数值积分方案和步长以及简化的变分方程。测量模型仅包括与米级相关的影响。选择EKF方法作为最简单的实时估计算法，并对其参数进行适当调整。在开发的程序中，一天中获得的位置和速度误差分别为15至20 m和0.014至0.018 m / s，标准偏差分别为6至10 m和0.006至0.008 m / s，启用或关闭SA。结果，以及对最终采用的模型的分析，都在这项工作中介绍。

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