Abstract This paper studies the thrust vector control problem for an upper-stage rocket with fuel slosh dynamics. The dynamics of a three-axis stabilized spacecraft with a single partially-filled fuel tank are formulated and the sloshing propellant is modeled as a multi-mass–spring system, where the oscillation frequencies of the mass–spring elements represent the prominent sloshing modes. The equations of motion are expressed in terms of the three-dimensional spacecraft translational velocity vector, the attitude, the angular velocity, and the internal coordinates representing the slosh modes. A Lyapunov-based nonlinear feedback control law is proposed to control the translational velocity vector and the attitude of the spacecraft, while attenuating the sloshing modes characterizing the internal dynamics. A simulation example is included to illustrate the effectiveness of the control law.

    Highlights Equations of motion for a three-axis stabilized spacecraft with fuel slosh are obtained. Thrust-vector control problem for an upper-stage rocket is formulated. A Lyapunov-based nonlinear feedback control law is designed. Simulation results are included to illustrate the effectiveness of the controller.


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    Titel :

    Thrust-vector control of a three-axis stabilized upper-stage rocket with fuel slosh dynamics


    Beteiligte:

    Erschienen in:

    Acta Astronautica ; 98 ; 120-127


    Erscheinungsdatum :

    2014-01-26


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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