For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method further iteratively calculates an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. In response to determining the inner polytope boundary will be breached, the method maneuvers the given spacecraft to within the inner polytope boundary based on a switching condition, a guidance law, and model predictive control to minimize fuel consumption.


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    Title :

    Maneuvering a spacecraft using an optimized guidance trajectory and model predictive control


    Contributors:
    SMITH TYSON (author) / AKAGI JOHN (author) / DROGE GREG (author)

    Publication date :

    2025-05-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



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