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

• Published in: Acta astronautica 2014-05, Vol.98, p.120-127
• Main Authors: Rubio Hervas, Jaime, Reyhanoglu, Mahmut
• Format: Article
• Language: English
• Subjects: Dynamical systems; Dynamics; Fuels; Lyapunov methods; Mathematical analysis; Nonlinear dynamics; Propellant slosh; Rockets; Spacecraft; Thrust-vector control; Vectors (mathematics)
• ISSN: 0094-5765; 1879-2030
• DOI: 10.1016/j.actaastro.2014.01.022

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. •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.