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   <subfield code="a">Optimal injection of a satellite into geostationary orbit using a limited number of thruster firings</subfield>
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   <subfield code="c">[A. Bortakovskii, A. Konovalova]</subfield>
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   <subfield code="a">The problem of optimal injection of a satellite into a geostationary orbit using a limited number of thruster firings is considered. It is formulated as an optimal control problem for a continuous-discrete system with automaton-type discrete part. The application of necessary optimality conditions reduces this problem to a finite-dimensional minimization problem. Taking into account the practical accuracy of executing the thruster firing and shutdown commands, the constrained minimization problem to be solved becomes discrete. Various flight sequences with the number of main engine firings not exceeding nine are investigated. Each sequence is optimized so as to minimize fuel consumption and find the optimal times of the engine firings and shutdowns. Parameters of the transfer orbits and deviations of the final orbit from the geostationary one are calculated. The results are compared with the scheme that is normally used in practice.</subfield>
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