航天器相对运动水滴型悬停轨道研究

Study on Spacecraft Relative Drip-drop Hovering Orbit

对航天器相对运动的C-W方程进行了分析,提出了航天器相对运动轨道设计中的一种水滴型悬停轨道,能够实现航天器相对空间目标在一定范围内进行悬停,并且只需使用脉冲速度增量控制即可实现长时间的悬停。文章对悬停轨道的悬停周期与目标航天器轨道参数和悬停位置的关系,以及悬停控制所需的速度增量ΔV进行了分析,给出了进行悬停轨道选择及设计的工程方法,并对C-W方程的状态转移矩阵进行了推导,得到了由常规的后方伴飞轨道使用脉冲速度控制方案进入目标星正下方的悬停位置的初始速度增量、转移时间及末端速度增量。根据分析结果,水滴型悬停轨道有利于工程实现,其设计方法可以应用于航天器在轨服务、侦察、巡视等任务的轨道设计。

This paper anlyses the C-W equation of the relative orbit and introduces the drip-drop hovering orbit for the spacecraft relative motion orbit design. Hovering in some relative region to the space target can be achieved by this design, and only impulse △V control is needed to maintain long time hovering orbit. The relation between hovering period and target spacecraft orbit parameters is analyzed, and the required velocity increment is computed. The engineering method is given for the selection and design of hovering orbit. The entry velocity increment, transfer time and terminal impulsive velocity increment from the company orbit according to the state transfer matrix of C-W equation is analyzed. The drip-drop hovering orbit and its design method can be applied in the fields of spacecraft in-orbit service, space state reconnaissance,etc.