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首页> 外文期刊>The Journal of the Astronautical Sciences >Third-Body Perturbation Effects on Satellite Formations
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Third-Body Perturbation Effects on Satellite Formations

机译：三体摄动对卫星编队的影响

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The effects of third-body perturbations on satellite formations are investigated using differential orbital elements to describe the relative motion. Absolute and differential effects of the lunar perturbation on satellite formations are derived analytically based on the simplified model of the circular restricted three-body problem. This analytical description includes averaged long-term effects on the orbital elements, including the full transformation between the osculating elements and the lunar-averaged elements, which is absent from previous research. A simplified Earth Moon system model is used, but the results are applicable to any formation reference orbit about the Earth. Simulations are performed to determine the effects of the lunar perturbation on example formations in upper MEO, highly eccentric orbits by using the formation design criteria of Phases I and II of the NASA Magnetospheric Multi scale mission. The changes in angular differential orbital elements (delta omega, delta Omega, and delta M-0) and in science return quality due to this perturbation are compared to changes due to J(2). The method is then expanded to include the inclination of the Moon's orbit and results are compared to simulation using the NASA General Mission Analysis Tool.
机译：使用微分轨道元素描述相对运动，研究了第三体摄动对卫星编队的影响。基于圆形受限三体问题的简化模型，分析性地得出了月球摄动对卫星编队的绝对和差分影响。这种分析性描述包括对轨道要素的平均长期影响，包括振荡要素和月球平均要素之间的完全转换，这是先前研究所没有的。使用了简化的地球月球系统模型，但结果适用于围绕地球的任何编队参考轨道。通过使用NASA磁层多尺度任务的阶段I和II的编队设计标准，进行模拟以确定月球摄动对上部MEO，高偏心轨道中的示例编队的影响。将这种微扰引起的角差轨道元素（δω，δω和δM-0）的变化和科学返回质量的变化与J（2）的变化进行比较。然后将该方法扩展到包括月球轨道的倾斜度，并将结果与​​使用NASA通用任务分析工具进行的仿真进行比较。

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