Abstract
The paper presents solutions of the problem of choosing flights of a spacecraft from high elliptic orbits to a geostationary orbit using a stationary plasma engine. The problem of optimal variation of the semi-major axis, eccentricity and inclination, minimizing the discrepancies in these elements with the use of a locally optimal control law that ensures a joint change of these parameters is also solved. An algorithm for determining the weighting coefficients is given; the algorithm ensures simultaneous fulfillment of boundary conditions for the semi-major axis, eccentricity and inclination is given. The results of numerical simulation based on the results of optimization of flights of a communication satellite from a highly elliptical orbit to the geostationary orbit are presented. Based on the results of numerical simulation, plots of the orbit parameters against time are constructed. The results of the data obtained make it possible to draw a conclusion about the possibility of applying a scheme of joint changes in the orbit parameters.
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