Numerical Calculation of Transfer Trajectories Between Bounded Orbits Near Collinear Lagrange Points

The main aim of this study is the motion of the spacecraft in the vicinity of the Lagrange points L2 and L1 of the Sun-Earth system. The object of the study is the trajectory of the flight from the halo orbit in the vicinity of the point L2 to the orbit in the vicinity of L1. The calculation of the flight trajectories, an algorithm based on the numerical integration and calculation of the moments of crossing the trajectory of certain planes is constructed. The intersection of these planes by the trajectory of the spacecraft (SC) allowed to separate those, the motion on which is directed to the vicinity of the point L1 from the others. The algorithm is implemented in Python and applied to the calculation of flight trajectories from three halo orbits of different amplitudes. The results of the calculations are presented in the form of graphs of time of flight, the magnitude of the required correction pulse, the amplitudes of the final orbit from the moment of departure from the original orbit. The view of flight trajectories in the projection on the Ecliptic plane is shown. A comparative analysis of the results for the three halo orbits is performed.