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将太阳-地球-火星-飞行器组成的四体问题分解成由太阳-地球-飞行器和太阳-火星-飞行器两个共面圆形限制性三体问题,设计日地系L2点与日火系L1点Lyapunov轨道之间的转移轨道,该转移轨道可以作为探测火星时的低能中间转移轨道.采用Richardson三阶近似解作为初始值,运用微分修正方法分别得到两个不同三体系统下拉格朗日点的精确Lyapunov轨道.基于Lyapunov轨道不变流形以及微分修正方法,设计了日地系L2点与日火系L1点间的转移轨道.将所得结果与基于Halo轨道不变流形设计的转移轨道进行了对比.结论表明:利用Lyapunov轨道不变形设计探火中间转移轨道相较于利用Halo轨道不变流形设计探火中间转移轨道在能量消耗以及飞行时间上都存在优势.
The four-body problem of the solar-earth-Mars-spacecraft is decomposed into two coplanar circular restricted three-body problems of the Sun-Earth-Spacecraft and the Sun-Mars-Aircraft. Point Lyapunov orbit, which can be used as low-energy intermediate transfer orbit when detecting Mars. The Richardson third-order approximation solution is used as initial value, and two different three-body systems are used to obtain Lagrange points Based on the Lyapunov orbit invariant manifold and the differential correction method, the transfer orbit between the L2 and the L1 of L1 is designed. The results obtained are compared with those based on the Halo orbit invariant manifold design The results show that there is an advantage in both energy consumption and flight time when using Lyapunov orbit deformation to design the middle orbit of fire detection is better than using the Halo orbit invariant manifold to design the middle orbit of fire detection.