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Satellite attitude PDE-based controller design considering fluid fuel sloshing in planar maneuver

Jokar, M ; Sharif University of Technology | 2022

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  1. Type of Document: Article
  2. DOI: 10.1016/j.ast.2022.107366
  3. Publisher: Elsevier Masson s.r.l , 2022
  4. Abstract:
  5. Due to significance of high-accuracy attitude control, the fuel sloshing effects on the satellite attitude should be considered, more precisely. This work deals with the attitude control of a liquid propellant-filled satellite considering the incompressible fuel sloshing in the planar maneuver. The satellite consists of a rigid body, a partially-filled tank and a flexible diaphragm. Hamilton's principle is employed to derive nonlinear coupled PDEs-ODEs governing the coupled satellite-diaphragm propellant tank system. Afterwards, to dispense with the spillover instability, a PDE-based controller is designed to realize the satellite attitude control while tracking a desired pitch angle and suppressing the sloshing of the fuel. One of the main benefits of the introduced controller is stabilization of the infinite-degree-of-freedom system without any simplification which is fulfilled using only one control torque applied to the rigid satellite. In addition, the closed-loop system stability is proven using Lyapunov stability approach, even if the viscosity of the fuel and any environmental damping are disregarded. Assessing of the proposed controller capability and its effectiveness indicates that the present study can pave the way toward more accurate satellite attitude maneuvers. © 2022 Elsevier Masson SAS
  6. Keywords:
  7. Fuel sloshing ; Nonlinear coupled PDEs-ODEs ; Attitude control ; Closed loop systems ; Controllers ; Degrees of freedom (mechanics) ; Fuels ; Liquid sloshing ; Ordinary differential equations ; Spacecraft propulsion ; System stability ; Tanks (containers) ; Controller designs ; Coupled PDEs ; Fluid fuel ; High-accuracy ; Lyapunov stability ; Nonlinear coupled PDE-ODE ; PDE-based control ; Rigid body ; Satellite attitude ; Sloshing effects ; Satellites
  8. Source: Aerospace Science and Technology ; Volume 122 , 2022 ; 12709638 (ISSN)
  9. URL: https://www.sciencedirect.com/science/article/abs/pii/S1270963822000402