Abstract This paper considers the nonlinear interaction of the rigid body dynamics of a spacecraft with the sloshing dynamics of the liquid propellant in its partially filled spherical tank during an orbital transfer. Fuel slosh dynamics are described by a three-dimensional two-pendulum model characterizing the first two sloshing modes, and the coupled equations of motion of the vehicle and the fuel masses are derived by means of quasi-Lagrangian equations. In addition, this paper studies active nonlinear control methods to control the attitude of the spacecraft while suppressing the sloshing of fuel. Simulations are conducted to illustrate the effectiveness of these control methods.
Highlights Equations of motion for a spacecraft with fuel slosh are obtained. Fuel slosh dynamics are described by a two-spherical-pendulum model characterizing the first two sloshing modes. Sliding mode, fuzzy logic, and Lyapunov-based feedback control laws are designed. Simulation results are included to illustrate the effectiveness of the controllers.
Modeling and control of a nonlinear coupled spacecraft-fuel system
Acta Astronautica ; 162 ; 436-446
2019-06-22
11 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Adaptive Nonlinear Dynamic Inversion for Spacecraft Attitude Control with Fuel Sloshing
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