The method of design-ballistic optimization developed by authors assumes the solution of a task on a self-optimizing control. The Pontryagin's maximum principle is applied to transition to a boundary-value problem. Runge-Kutta-4 method is used for direct modeling of operated movement. Optimization of parameters is carried out by means of downhill simplex method. Solutions of a boundary-value problem on a self-optimizing control for flight of the minimum duration and the minimum expenses of a propellant are received with the fixed duration. Change of an expense of a gas working fluid on flight Earth Mars is analyzed at various parameters of the spacecraft.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Features of optimization of interplanetary flights with low-thrust engines


    Beteiligte:
    Kurochkin, D.V. (Autor:in) / Starinova, O.L. (Autor:in)


    Erscheinungsdatum :

    01.06.2013


    Format / Umfang :

    712661 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch