Abstract
An adaptive, semi-analytical, and geometrically clear method for synthesis of sequences of Venusian gravity-assist maneuvers setting the desired inclination of a spacecraft orbit is proposed. The geometric constraint on the maximum possible inclination of a spacecraft orbit, which depends on the asymptotic spacecraft velocity relative to Venus, and the dynamic constraint (arising when a gravity-assist maneuver is performed) on the angle of rotation of the vector of asymptotic velocity relative to Venus are considered simultaneously.
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Translated by D. Safin
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Golubev, Y.F., Grushevskii, A.V., Koryanov, V.V. et al. Synthesizing Spacecraft Orbits with High Inclinations Using Venusian Gravity Assists. Dokl. Phys. 64, 24–26 (2019). https://doi.org/10.1134/S1028335819010087
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DOI: https://doi.org/10.1134/S1028335819010087