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针对深空探测中轨道转移时间长且能量消耗较大的问题,提出基于准流形实现从地球停泊轨道到日地系L3点转移轨道的设计方法。在日地限制性三体问题模型下,在L1点或L2点Halo轨道上施加扰动推力,构造准流形,利用其非线性三体动力学特性,通过霍曼转移轨道与近地轨道进行拼接,使航天器进入准流形后能够无动力滑行到L3点附近区域。在准流形与L3点周期轨道交点,施加速度脉冲,使航天器进入相应周期轨道,从而完成轨道转移。仿真结果表明,利用该方法所得结果与基于不变流形的转移轨道相比,能将速度增量从4 398m/s减少为4 014m/s,并将转移时间从9年以上缩短到7.3年以内,有效地提高了航天器的工作效率。
In view of the problem of long orbit transfer time and high energy consumption in deep space exploration, a design method based on quasi- manifold is proposed to realize the transfer trajectory from the earth mooring orbit to the daytime system. Under the constrained three-body problem model in Japan, a perturbed thrust is applied to the Hal orbit of point L1 or L2 to construct quasi- manifolds. By using the nonlinear three-body dynamics, they are spliced through the Hopman orbit and the near-Earth orbit , So that the spacecraft can enter the quasi- manifold without gliding to the area near L3. In the quasi manifold and L3 point orbital intersection, the application of speed pulse, the spacecraft into the corresponding orbit, thus completing the orbit transfer. The simulation results show that the proposed method can reduce the speed increment from 4 398 m / s to 4 014 m / s and transfer time from 9 years to 7.3 years compared with that based on invariant manifolds Within the effective increase of spacecraft efficiency.