Planar Problem of an Optimal Transfer of a Low-Thrust Spacecraft from High-Elliptic to Geosynchronous Orbit

Quasioptimal interorbit transfers of a low-thrust spacecraft in strong central Newtonian gravity field

“…The beginning of the practical use of the electric rocket engines as the main engines for carrying out the maneuvers in near-Earth space sets the highpriority problem on the calculation of both optimal controls and optimal transfer trajectories [1][2][3][4][5][6]. It is well known that a two-point boundary problem, to which the problem under consideration is reduced by Pontryagin's maximum principle, can be solved only with the use of the numerical methods even for the simplest model of the Newtonian central gravity field.…”

Optimal low-thrust orbital transfers in a central gravity field

“…Note that analysis (i) is necessary because the method proposed earlier in [47] for solving the problem in question is still in use, though with minor modifications [2,27]; and the analytic solutions (iii) have been obtained only with the help of approach (ii). The importance of these analytic solutions is in their describing maneuvers that are of independent practical interest.…”