The optimization method of interplanetary flights of spacecraft with limited-thrust engine is developed. The optimization criterion is the combined functional proposed by K.G. Grigoriev, which combines fuel costs and flight time. The method of sorting unknown initial conditions of the boundary value problem using I.M. Sobol sequences is applied. The problem of 'fast' flight from the circular orbit of an artificial satellite of the Earth to the circular orbit of an artificial satellite of the Moon is solved.

maximum principle, combined functional, Sobol sequences

Mathematical modelling in actual problems of science and technics