Abstract

Methods and algorithms for determining the orbit of a space vehicle onboard using the measurements of global navigation satellite (NS) systems are considered. Methods and algorithms for obtaining radio navigation measurements in the case of the highly dynamic orbital motion are described. The celestial mechanics interpretation of measurements is given. Algorithms for the three-phase processing of trajectory measurements that improve the reliability and accuracy of determining the orbit are proposed. A mathematical model of a simulator of the satellite navigation signals is developed. The computational results are presented.

中文翻译：

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确定太空飞行器的轨道

摘要

考虑了用于使用全球导航卫星（NS）系统的测量确定机载航天器的轨道的方法和算法。描述了在高度动态轨道运动的情况下获得无线电导航测量值的方法和算法。给出了测量的天体力学解释。提出了用于轨迹测量的三相处理的算法，该算法提高了确定轨道的可靠性和准确性。建立了卫星导航信号模拟器的数学模型。给出了计算结果。