Aspects of applying combined mass–time functional in solving the problem of optimizing the multiple-burn transfer of a spacecraft into a high-energy orbit
Authors: Kiriliuk E.V., Stepanov M.N.
Published in issue: #3(123)/2022
DOI: 10.18698/2308-6033-2022-3-2164
Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control
Through the example of a non-coplanar transfer of an orbital unit with a low reference to a geostationary orbit, the paper describes the main aspects of applying the combined mass–time functional to the problem of optimizing multiple-burn transfer using the maximum principle. The study analyzes the saturation of the dependence of the orbital unit’s mass in the target orbit on the weight coefficient for a wide range of the orbital unit’s mass-energy characteristics of upper stages for a given structure of the optimal trajectory. Furthermore, a similar analysis was carried out for structures of optimal trajectories containing a different number of perigee active sections, with fixed mass-energy characteristics of the upper stage. The ranges of variation of the weight coefficient are demonstrated, in which there are optimal schemes containing a different number of perigee active sites. Recommendations are given for setting the saturation coefficient, at which the solution of the problem with the combined functional can be considered coinciding with the solution of the problem of maximizing the finite mass of the orbital block.
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