Optimization is made of the trajectories, controls, and the parameters of a low-thrust constant-power engine with energy storage of a spacecraft executing the maneuver of synchronous considerable change in the semimajor axis, eccentricity, and angle of an elliptical orbit in a spherical gravitational field. The gain in payload mass due to the energy storage is estimated. The optimal control law and the optimal ratio for the masses of the propulsion system are found
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Translated from Prikladnaya Mekhanika, Vol. 46, No. 11, pp. 93–100, November 2010.
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Kiforenko, B.N., Tkachenko, Y.V. Optimization of spacecraft transfers between distant elliptical orbits. Int Appl Mech 46, 1292–1297 (2011). https://doi.org/10.1007/s10778-011-0422-9
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DOI: https://doi.org/10.1007/s10778-011-0422-9