Abstract
The problem of the minimum time low-thrust transfer of a spacevehicle (SV) between arbitrary elliptic orbits in strong central Newtonian gravity field is under consideration. An approach is proposed to compute closer to optimal numerical solution of motion equations of a low-thrust SV, which realizes multiturn transfer. Both cases of variable and constant in magnitude rocket thrust are assumed. The examples of solutions of exact motion equations are given, which prove the validity of the proposed approach in combination with the use of the averaged solutions.
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