Along-Track Boundedness Condition for Spacecraft Relative Motion Around a Slowly Rotating Asteroid

Along-Track Boundedness Condition for Spacecraft Relative Motion Around a Slowly Rotating Asteroid
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航天器绕慢速旋转小行星相对运动的沿轨有界条件

DOI:
10.1109/taes.2022.3183181
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发表时间:
2023-02
影响因子:
4.4
通讯作者:
Baoyin Hexi
Baoyin Hexi
中科院分区:
计算机科学2区
文献类型:
--
作者:
Wang Wei;Lei Hanlun;Mengali Giovanni;Quarta Aless;ro A;Baoyin Hexi

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本文给出了航天器绕慢速自转小行星相对运动的闭合形式沿轨道有界条件。与以前提出的必须满足三个必要约束的准则不同,目前的方法只需要实施一个约束来抑制沿轨漂移,从而在航天器编队设计中允许增加两个自由度。特别是,为了适应适用于较大尺寸地层的导出结果,然后将一阶分析的有界性条件扩展为二阶结果。在后一种情况下,平均半长轴差的值被发现是二次(代数)方程的根。此外,还分析了最优单脉冲机动,在存在初始化误差的情况下,可以保证有界的相对运动。通过算例验证了分析结果的正确性。
In this paper, the closed-form along-track boundedness condition for spacecraft relative motion around a slowly rotating asteroid is presented. As opposed to the previously proposed criteria where three necessary constraints must be satisfied, the current approach only requires to enforce one constraint to suppress the along-track drift, thus allowing two additional degrees of freedom in spacecraft formation design. In particular, to adapt the derived results applicable for formation with a relatively large size, the boundedness condition via first-order analysis is then extended to obtain a second-order result. In the latter case, the value of mean semimajor axis difference is found to be the root of a quadratic (algebraic) equation. Moreover, an optimal single-impulse maneuver is analyzed, by means of which the bounded relative motion can be guaranteed in the presence of initialization errors. Illustrative examples are provided to validate the analytical results.
围绕缓慢旋转的小行星的准冻结轨道
DOI: 10.2514/1.g003837
发表时间: 2019-04
期刊: Journal of Guidance, Control, and Dynamics
影响因子: --
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