Systems and methods are described for a satellite control system that exhibits improved stability and increased efficiency by implementing a non-linear dynamic inversion inner-loop control algorithm coupled with an eigen vector outer-loop control algorithm (225). Thus, the attitude determination and control system (ADACS) may operate using commands to rotate directly about an eigen vector. Additionally, the outer-loop control system (225) includes a feed-forward control element to enhance pointing accuracy when tracking moving targets.


    Access

    Download


    Export, share and cite



    Title :

    SATELLITE ATTITUDE CONTROL SYSTEM USING EIGEN VECTOR, NON-LINEAR DYNAMIC INVERSION, AND FEEDFORWARD CONTROL


    Additional title:

    SATELLITENORIENTIERUNGSTEUERUNGSSYSTEM UNTER VERWENDUNG VON EIGEN-VEKTOR, NICHTLINEARER DYNAMISCHER INVERSION UND FEEDFORWARD-STEUERUNG
    SYSTÈME DE COMMANDE D'ATTITUDE D'UN SATELLITE UTILISANT UN VECTEUR EIGEN, L'INVERSION DYNAMIQUE NON LINÉAIRE ET LA COMMANDE PRÉDICTIVE


    Contributors:

    Publication date :

    2022-06-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS