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首页> 外文期刊>Journal of guidance, control, and dynamics >Approximate Analytical Solutions to Optimal Reconfiguration Problems in Perturbed Satellite Relative Motion
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Approximate Analytical Solutions to Optimal Reconfiguration Problems in Perturbed Satellite Relative Motion

机译：卫星相对运动中最优重构问题的近似解析解

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摘要

This paper presents new analytical solutions to the optimal reconfiguration problems of formation flying using a power-limited low-thrust propulsion that includes perturbations associated with differential gravity effects, the eccentricity effects of a chief orbit, and J_2 effects. The perturbation approach and the calculus of variations are applied to optimal reconfiguration problems to obtain an approximate analytical solution. Some nonlinear relative dynamics are also presented to account for the nonlinear terms generated by each perturbation. For the sake of validity, numerical simulations are performed for satellite reconfiguration cases in which the distance between the satellites is large and the chief orbit is eccentric. The improved capacity of the new analytical solutions to ensure reasonable fuel usage is confirmed, and the magnitudes of the errors caused by each perturbation are compared and analyzed. It is found that the errors caused by unperturbed analytical solutions based on only the Hill-Clohessy-Wilshire equations are reduced by the new analytical solutions by one-half to one over 500, depending on which perturbation is considered.
机译：本文提出了一种新的分析解决方案，它使用功率受限的低推力推进来解决编队飞行的最佳重构问题，其中包括与重力差效应，主轨道偏心效应和J_2效应相关的扰动。摄动方法和变化演算被应用于最佳重构问题，以获得近似的解析解。还提出了一些非线性的相对动力学来解释每个扰动产生的非线性项。为了有效，对卫星之间的距离较大且主轨道偏心的卫星重新配置情况进行了数值模拟。确认了确保合理燃料使用的新分析解决方案的增强功能，并对每个扰动引起的误差的大小进行了比较和分析。结果发现，新的解析解将仅基于Hill-Clohessy-Wilshire方程的无扰动解析解引起的误差减少了一半，减少到500分之一，这取决于所考虑的扰动。

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