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.


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    Title :

    Features of optimization of interplanetary flights with low-thrust engines


    Contributors:


    Publication date :

    2013-06-01


    Size :

    712661 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English