Optimization methods of near-Earth and interplanetary flights with low thrust.

The problem of improving the efficiency of space transport operations and control modes of the orbits of spacecraft now is particularly relevant. One possible solution of this problem is the use of propulsion systems on the basis of the low-thrust electro-jet engines. Authors provides methods for the design-ballistic optimization of space missions. The optimization problem is divided into two independent: dynamic - is finding the optimal control programs; parametric - finding the optimal design parameters of the spacecraft and ballistic mission parameters. [ABSTRACT FROM AUTHOR]