基于圆型限制性三体模型的借力飞行机理研究

Research on Gravity-Assist Mechanism in Circular Restricted Three-body Problem

针对星际探测中的借力飞行技术,基于圆型限制性三体模型,深入研究了全相位角情况下借力飞行自由参数与借力飞行轨道变化之间的关系。在圆型限制性三体问题的假设下,通过正向与逆向积分相结合的方法,给出了圆型限制性三体系统中,通过借力飞行实现逃逸与俘获以及顺行轨道与逆行轨道转变的条件,并以地月系统为例,给出了通过月球借力飞行实现地月系统俘获与逃逸的借力飞行参数选择区域。同时,也给出了通过月球借力飞行实现轨道类型转变的参数变化范围。最后,讨论分析了借力飞行高度、速度和借力相位角对借力飞行轨道能量变化量的影响,进一步揭示借力飞行自由参数与借力飞行轨道变化之间的关系。

To the Gravity-Assist Technology in interplanetary mission, we research deeply on the relative between the independent variables that describe completely the Gravity-Assist maneuver and orbital change before and after gravity-assist maneuver by using Circular Restricted Three-body problem （CRTP）. On the condition of CRTP, we provide the conditions of escape and captive, switching condition between direct orbit and retrograde orbit with gravity-assist maneuver in CRTP by using the method of forward and back integral. Taking the Earth-Moon system as an example, we provide the selection region of gravity-assist parameters that can achieve escape and captive and switch orbital type in Earth-Moon system with Moon gravity-assist. Finally, we analyze the influence of the latitude, velocity and phase angle of gravity-assist maneuver on change of orbital energy before and after gravity-assist in order to improve our understanding of this problem further.