Highlights The minimum total velocity variation between elliptic orbits is calculated with three tangential impulses. The problem is reduced to the minimization of a function of three independent variables. The reduction of problem complexity allows the global minimum solution to be easily found. The algorithm determines the best transfer strategy and the required number of tangential impulses.

    Abstract This paper introduces a mathematical model that can be used to evaluate the total velocity variation required to accomplish a given two-dimensional orbit transfer, using up to three tangential impulsive maneuvers. The problem is addressed in an optimal framework, by looking for the transfer trajectory that minimizes the total velocity variation. In particular, by exploiting the boundary nonlinear constraint equations, the total velocity variation can be calculated as a function only of the spacecraft angular position at which the impulses are applied. The small number of control variables involved in the algorithm allows the optimization problem to be solved in a simple and robust way, with a small computational effort. The algorithm is able to find the optimal transfer strategy in a generic ellipse-to-ellipse, two-dimensional, mission scenario.


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    Titel :

    Optimal transfer between elliptic orbits with three tangential impulses


    Beteiligte:

    Erschienen in:

    Advances in Space Research ; 64 , 4 ; 861-873


    Erscheinungsdatum :

    2019-05-23


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch