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Navigation solution to maneuver a spacecraft relative to multiple satellites and ground locations

机译：导航航天器相对于多个卫星和地面位置的导航解决方案

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A dynamic differential correction algorithm is presented to deliver an impulsive maneuver to a satellite to place it within overlapping spheres, with user defined radii, centered around multiple non-maneuvering satellites and ground location's user defined line-of-sight within a constrained time. The solution is further constrained by elevation considerations for the ground locations. The differential correction algorithm develops and utilizes the state transition matrix, along with the equations of motion and multiple satellite's state information and ground location state information to determine the optimum trajectory to achieve the desired results. The results from the differential correction algorithm are very accurate for prograde orbits, as presented. The results allow for orbit design trade-offs, including the maneuvering satellite's initial inclination. The results deliver an analytical method to determine the optimum Delta V solution for the provided problem. This work ultimately establishes the generalized framework for applying the algorithm to a unique maneuvering spacecraft scenario which includes multiple satellites and ground locations. (C) 2014 Published by Elsevier Ltd. on behalf of IAA.
机译：提出了一种动态差分校正算法，该算法可将冲激机动传递给卫星，以将其置于重叠的球体中，并且用户定义的半径以多个非机动卫星为中心，并在一定时间内以地面位置的用户定义的视线为中心。该解决方案还受到地面位置高程考虑的限制。差分校正算法开发并利用了状态转换矩阵，以及运动方程式和多颗卫星的状态信息以及地面位置状态信息，以确定实现所需结果的最佳轨迹。如图所示，差分校正算法的结果对于前进轨道非常准确。结果考虑到了轨道设计的折衷，包括机动卫星的初始倾角。结果提供了一种分析方法，可以为所提供的问题确定最佳的Delta V解决方案。这项工作最终建立了将算法应用到包括多个卫星和地面位置的独特机动航天器场景的通用框架。 （C）2014由Elsevier Ltd.代表IAA发布。

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