Method for optimization of trajectories including gravitational maneuvers of a spacecraft with a solar sail

A method for simulation and optimization of flight trajectories including multiple maneuvers of spacecrafts equipped with a solar sail is considered. The proposed method provides a possibility of formation of the general approach to solution of optimization problems of interplanetary missions using a solar sail. The problems of optimization of flight trajectories to Mercury and to a vicinity of the Sun on the basis of the inexpensive conversion Dnepr launch vehicle are solved using the proposed method.