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.
Thrust-vector control of a three-axis stabilized upper-stage rocket with fuel slosh dynamics
Acta Astronautica ; 98 ; 120-127
2014-01-26
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Thrust-vector control of a three-axis stabilized upper-stage rocket with fuel slosh dynamics
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