Optimization of flights ballistic schemes between non-coplanar orbits by means of the combination of high and low thrust engines

The problem of a choice of spacecraft flight optimum ballistic schemes into a geostationary orbit with use of high and low thrust engines is investigated. The scheme of optimization multicriterial problem decision for the combined flights into a geostationary orbit is offered: as the main criteria are accepted weight of payload in a target orbit and duration of flight, and other criteria (the general time of spacecraft stay in the Earth radiating belts and duration of shadow sites) are translated in the category of restrictions. At the first stage the twocriterial problem of optimization by means of generation of Pareto optimum decisions, at the second stage check of performance of restrictions is carried out. At the third stage synthesis of design ballistic characteristics of flight as a whole, taking into account restrictions is carried out. The method of a dynamic part problem decision consists in use of an expansion principle of admissible conditions and controls at transition from an optimization problem in strict statement (according to a Pontrjagins maximum principle) to a problem of local optimization. Results of numerical modeling of the flights combined schemes, optimization of their design ballistic characteristics, calculation of design parameters of the interorbital transport spacecraft are resulted.