Decomposition analysis of spacecraft relative motion with different inter-satellite ranges

Decomposition analysis of spacecraft relative motion with different inter-satellite ranges
复制标题

DOI:
10.1016/j.actaastro.2019.01.012
复制
发表时间:
2019-10
期刊:
影响因子:
3.5
通讯作者:
Jiang Chao;Zhaokui Wang;Zhang Yulin
Jiang Chao;Zhaokui Wang;Zhang Yulin
中科院分区:
工程技术3区
文献类型:
--
作者:
Jiang Chao;Zhaokui Wang;Zhang Yulin

文献摘要

相似文献

近年来,随着卫星集群和巨型星座的发展,由于燃料消耗的限制和轨道摄动的影响,这些系统的轨道设计和长期维护变得更加困难。因此,有必要研究适用于不同星间距离的相对运动解析模型。然后,考虑轨道根数的摄动演化,将相对运动模型分解为两部分,分别反映绕主星的绕圈运动和相对主星的整体运动,提出了分解相对运动模型。偏心率展开已进行分解模型提供一个时间显式的解析解。基于该一阶时间显式解析解,研究了开普勒轨道上不同星间距离下的束缚相对运动。同时导出了一般主心圆相对运动的初始条件计算公式。从理论和数值两方面对分解模型的一阶解析解的精度进行了估计,以反映星间距离和主偏心率的影响。最后,将基于平均轨道根数的一阶解析解与摄动下的高精度数值解进行了比较,验证了其在长期稳定性分析中的有效性。
With the development of satellite cluster and giant constellations in recent years, the orbit design and long-term maintenance of these systems become more difficult with the restriction of fuel consumption and the influence of orbital perturbations. It's necessary to study the analytical model of relative motion which applicable to different inter-satellite ranges. Then, considering the perturbed evolutions of orbital elements, the decomposed relative motion model was proposed by separating the higher-fidelity relative motion model into two different parts, which reflect the circling motion around chief, and their overall motion relative to chief respectively. Eccentricity expansions had been carried out to provide a time-explicit analytical solution of the decomposed model. Based on this first order time-explicit analytical solution, the bound relative motions with different inter-satellite ranges were studied in Kepler orbit. The initial condition calculation formula for general chief centered circular relative motion was derived at the same time. The accuracy of first order analytical solution of the decomposed model was estimated both theoretically and numerically, to show the effect of inter-satellite range and chief's eccentricity. At last, the first order analytical solution using mean orbital elements was compared with high precision numerical solution under perturbations to validate it's effective in long-term stability analysis.