The problem of improving the efficiency of space transport operations and control modes of the orbits of spacecraft now is particularly relevant. One possible solution of this problem is the use of propulsion systems on the basis of the low-thrust electro-jet engines. Authors provides methods for the design-ballistic optimization of space missions. The optimization problem is divided into two independent: dynamic - is finding the optimal control programs; parametric - finding the optimal design parameters of the spacecraft and ballistic mission parameters.


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    Title :

    Optimization methods of near-Earth and interplanetary flights with low thrust



    Conference:

    ICNPAA 2016 WORLD CONGRESS: 11th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences ; 2016 ; La Rochelle, France


    Published in:

    Publication date :

    2017-01-27


    Size :

    10 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




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