The analysis of the optimal strategies for the deployment of a spacecraft into a highly elliptic orbit is carried out by means of\r\nan indirect optimization procedure, which is based on the theory of optimal control. The orbit peculiarities require that several\r\nperturbations are taken into account: an 8 Ã?â?? 8 model of the Earth potential is adopted and gravitational perturbations fromMoon\r\nand Sun together with solar radiation pressure are considered. A procedure to guarantee convergence and define the optimal\r\nswitching structure is outlined. Results concerning missions with up to 4.5 revolutions around the Earth are given, and significant\r\nfeatures of this kind of deployment are highlighted.
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