The problem of optimization of multi-revolution trajectories between elliptical noncoplanar orbits is considered. The necessary conditions of optimality in the thrust minimization problem are given, which is used to diagnose the existence of a solution to the trajectory optimization problem of a spacecraft with limited thrust. A general scheme for solving the trajectory optimization problem with a limited thrust engine and numerical examples are given.


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    Title :

    Optimization of Multi-revolution Flights Between Elliptical Non-complanar Orbits


    Additional title:

    Studies in Systems, Decision and Control


    Contributors:


    Publication date :

    2025-05-29


    Size :

    17 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English