A computer-implemented method for maintaining a spacecraft near an orbit comprises steps of detecting that a distance from the spacecraft to the orbit is greater than a spacecraft threshold and in response, linearizing dynamics of the spacecraft from a current time over a time horizon with respect to a high-fidelity reference trajectory to produce a state transition matrix (STM) for an uncontrolled motion of the spacecraft within the time horizon. The STM includes non-expanding eigenvectors with magnitudes less than or equal to one and expanding eigenvectors with magnitudes greater than one. The method further comprises determining a control action that changes an upcoming state of the spacecraft to a linear combination of the non-expanding eigenvectors of the STM and generating a control command to an actuator of the spacecraft.


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    Titel :

    EIGENMOTION CONTROL FOR NEAR RECTILINEAR HALO ORBITS


    Weitere Titelangaben:

    EIGENBEWEGUNGSSTEUERUNG FÜR FAST GERADLINIGE HALO-UMLAUFBAHNEN
    COMMANDE DE MOUVEMENT PROPRE POUR DES ORBITES EN HALO QUASI RECTILIGNES


    Beteiligte:
    WEISS AVISHAI (Autor:in) / ELANGO PURNANAND (Autor:in) / DI CAIRANO STEFANO (Autor:in) / KALABIC UROS (Autor:in)

    Erscheinungsdatum :

    2024-05-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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