基于电推进卫星飞往平衡点的转移轨道研究

Research on transferring orbits flying to stable point based on electric propulsion satellites

针对航天器飞往日地拉格朗日点的转移轨道的问题,给出了一种基于稳定不变流形的直接配点方法。首先对小推力轨道及限制性三体问题进行建模,研究其从地球停泊轨道出发至绕日地L2点Halo轨道的转移轨道。然后基于限制性三体问题的雅可比积分常数寻找推力段与滑行段轨道的拼接点,优化航天器螺旋上升轨道。最后,仿真分析及计算表明,直接法优化小推力轨道具有收敛速度快且对初值猜测不敏感等优点,并且相比于化学推进,小推力推进在节约燃料方面优势明显。

Aiming at the problem of transferring to the L2 point of the Sun-Earth system,a direct collocation method based on stable invariant manifold was proposed. Firstly,the low thrust orbit and the restricted three-body problem were modeled,and the transfer orbit from the earth parking orbit to the Halo orbit around the Sun-Earth L2 pointed was studied. Then,based on the Jacobian integral constant of the restricted three-body problem,the splicing point of the burn phases and the coast phases was searched to optimize the spiral ascending orbit of the spacecraft. Finally,the simulation analysis and calculations show that the direct method optimization of low thrust orbit has the advantages of fast convergence speed and insensitivity to initial value guessing,and compared with chemical propulsion,low thrust has obvious advantages in fuel saving.