Calculation of Orbit Shading for Long-Period Orbits in Vicinity of Earth-Moon L2 Point

In this paper, the long-period Lissajous orbit in the vicinity of the libration point L_2 system Earth-Moon are investigated with the aim of determining the relationship between the parameters of the orbits and intervals of their shade. An algorithm for searching the initial state vector of the SPACECRAFT, that corresponds to long-period orbits, was developed and applied in the conditions of the three-body problem. The solution obtained in the circular restricted three body problem was analyzed and then transferred to the ephemeris model of the solar system, taking into account the gravitational influence exerted by the Sun. An algorithm for finding areas of shading of orbits is constructed. For each of the long-period orbits obtained, the shading intervals were found, and the maximum, minimum and total time of the SC in the shadow were calculated. The visualization of the spacecraft flight trajectory from these orbits is performed in a rotating coordinate system. The study was carried out by using the SPICE information system and the MATLAB package.