Electric propulsion spacecraft guidance for maintenance of the lunar base infrastructure

Motion simulation of the electric powered spacecraft is considered. Guidance program consists of guidance and navigation mathematical motion model and developed control laws. The findings of the work include the spacecraft trajectories and time dependencies of the control angles. The usage of the Fedorenko successful linearization method along with the gradient method in the three-body task framework are used to obtain optimal steering and the motion trajectories for spacecraft with low-thrust engines. The functional to optimize was chosen as a sum of the fuel used during the transfer and the components accounting for the conditions of the spacecraft final orbit insertion.