Features of optimization of interplanetary flights with low-thrust engines

The method of design-ballistic optimization developed by authors assumes the solution of a task on a self-optimizing control. The Pontryagin´s maximum principle is applied to transition to a boundary-value problem. Runge-Kutta-4 method is used for direct modeling of operated movement. Optimization of parameters is carried out by means of downhill simplex method. Solutions of a boundary-value problem on a self-optimizing control for flight of the minimum duration and the minimum expenses of a propellant are received with the fixed duration. Change of an expense of a gas working fluid on flight Earth Mars is analyzed at various parameters of the spacecraft.