Analysis of results of modelling of interplanetary flights with electric propulsion engines

Statement of a problem of design ballistic optimization of interplanetary flights for the spacecraft with electric propulsion engines is given in article. The method of optimization of heliocentric trajectory part of the spacecraft is described. With use of a formalism of Pontryagin's maximum principle, solutions of a boundary value problem on a self optimizing control for flight with the minimum expenses of a working body are received at the fixed duration. Flights between circular coplanar orbits are considered. The analysis of the received data is carried out, the corresponding graphic dependences are given.