摘要
面向未来使用平动点航天器编队进行深空探测的需求,研究了特殊的定向辐轮构型航天器编队在日地L2平动点Halo轨道上的动力学和相关控制问题。首先,建立了圆型限制性三体问题(CRTBP)的相对动力学和辐轮构型编队模型的数学表达;其次,基于Floquet理论和傅里叶级数展开推导了Halo轨道的相对运动解析解,该解的推导同样可应用于其他小偏离的周期时变系统;接着,以深空探测任务为导向,基于Floquet模态法和LQR控制法分别给出编队主星和从星的分层控制策略;最后,对控制策略进行仿真,详细分析了辐轮构型维持控制力的规律等,得到了构型参数(半径和频率)与维持代价的关系。
To fulfill the future requirement for deep space exploration through the utilization of libration point spacecraft formations,the dynamics and associated control matters of spacecraft formations featuring a distinctive directional spoke-wheel configuration on the Sun-Earth L2 libration point Halo orbit are examined in this work.Firstly,the mathematical representations for the relative dynamics of the Circular Restricted Three-Body Problem(CRTBP)and the spoke-wheel configuration formation model are formulated.Secondly,founded on Floquet theory and Fourier series expansion,analytical solutions for the relative motion of Halo orbits are deduced,which are applicable to other marginally perturbed periodic time-varying systems.Subsequently,aiming at deep space exploration missions,hierarchical control strategies for the formation's leader(chief)and followers(deputies)are proposed by employing the Floquet mode method and LQR control method.Finally,simulations of the control strategies are carried out,along with a detailed analysis of the patterns of control forces in maintaining the spoke-wheel configuration.The relationship between configuration parameters(radius and frequency)and the cost of maintenance is acquired.
作者
闫雪梅
杜博皓
徐明
张锐
胡志强
YAN Xuemei;DU Bohao;XU Ming;ZHANG Rui;HU Zhiqiang(Institute of Spacecraft System Engineering,Beijing 100094,China;School of Astronautics,Beihang University,Beijing 100191,China;Shen Yuan Honors College,Beihang University,Beijing 100191,China;Shanghai Satellite Network Research Institute Co.,Ltd.,Shanghai 200131,China;Shanghai Key Laboratory of Satellite Network Shanghai 200131,China)
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2024年第9期1408-1418,共11页
Journal of Astronautics
