Optimization design and ballistic parameters of spacecraft with solar thermal propulsion system for the formation and correction low-earth orbit

The problem of optimizing the design and ballistic parameters of the spacecraft with solar thermal propulsion system for interorbital maneuvers in non-central gravitational field of the Earth is considered. A model of a spacecraft with a fixed engine of limited power with power storage is used. The overall objective is divided into dynamic and parametric parts. Using the averaged model of the motion detection algorithm obtained approximately-optimal control. Optimization of design parameters is reduced to an iterative procedure. The efficiency of the propulsion system for the formation and correction of low-Earth orbit is shown.