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ISSN Druckformat: 1064-2315
ISSN Online: 2163-9337
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Use of Equinoctial Orbital Elements as Variables in the Problem of Minimal Time Orbit-to-Orbit Transfer in Strong Gravitational Field under Fixed-Value Thrust
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ABSTRAKT
A problem of minimal time transfer between elliptic orbits of a spacecraft (SC) with a small constant magnitude and regulated direction thrust in a central gravitational field is considered. Unlike earlier papers [1, 2], for obtaining averaged equations of optimal motion, in this work the authors used a system of equinoctial orbital elements. This technique enables one to eliminate singularities associated with zero values of either eccentricity or inclination of elliptic orbit in equations of motion.
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Kiforenko Boris M., Vasil’ev Igor Yu., Quasioptimal interorbit transfers of a low-thrust spacecraft in strong central Newtonian gravity field, Acta Astronautica, 65, 1-2, 2009. Crossref
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Kiforenko Boris N., Vasil'ev Igor Yu., Tkachenko Yaroslav V., On the problem of optimal control of the thrust value of the electric propulsion rocket with solar energy source, Acta Astronautica, 89, 2013. Crossref