ИСТИНА

The optimal control problem of the spacecraft noncoplanar interplanetary transfer from the artificial Earth satellite orbit to the artificial Mars satellite orbit is considered. All orbits are circular. The control is realized by two pulses and a low thrust jet engine vector. Total flight time is minimized. Solution of the 42nd order boundary value problem with selection of 13 parameters is constructed with the use of three different reference frames. The spacecraft performs a sixty-six and a nineteen many-revolution braking near Mars at constructed trajectories in problems of transition to orbits which are close approximates Phobos and Deimos orbits respectively.