The article presents the results of studies on low-energy "detour" transfer trajectories to an artificial lunar satellite orbit in the Earth-Moon-Sun system for spacecraft launched from a Russian space canter. In this type of trajectories, the spacecraft (SC) first flies beyond the Moon's orbit, out of the Earth's sphere of influence. Its trajectory parameters are altered by the Sun's gravitational perturbations, which enables lunar gravitational capture of the SC to take place, reducing the delta-V budget of the mission. The SC velocity is required to be low enough when approaching the Moon's sphere of influence, which limits incoming trajectory inclination with respect to the Moon's geocentric orbit plane. Therefore, supplementary studies of "detour" trajectories for launches from Russian space centres are necessary. Calculations conducted in this research confirm the possibility of lunar gravitational capture for SC launched from Russian space centers onto a "detour" trajectory. In some of the trajectories considered, a gravity assist maneuver with the Moon is used to increase SC energy and change its orbit inclination.