ATTITUDE CONTROL SYSTEM DESIGN FOR A RIGID-FLEXIBLE SATELLITE USING THE H-INFINITY METHOD WITH PARAMETRIC UNCERTAINTY

Authors

  • Alain Giacobini de Souza INPE /DMC
  • Luiz Carlos Gadelha de Souza UnB

DOI:

https://doi.org/10.26512/ripe.v2i19.15022

Abstract

This paper presents the Attitude Control System (ACS) design for a rigid-flexible satellite with two vibrations mode, using the H infinity method considering the parametric uncertainty over the mass matrix. Usually the mathematic model obtained from the linearization and/or reduction of the rigid flexible model loses information about the flexible dynamical behavior and introduces some uncertainty. As a result, the ACS performance can be degraded when controlling large angle maneuvers. One way to recovery the dynamics
information is to include in the ACS design the parametric and not parametric uncertainties of the system. The rigid flexible satellite dynamics can be represented by an ordinary differential equation (EDO), which coefficients are the matrices mass, damping and rigidly. In this paper one investigates the influence of the uncertainty in the mass matrix in the control law performance designed by the H infinity control methodology. The results of the simulations have shown that the control law designed using the H-infinity control method
considering the parametric uncertainty is robust since the ACS performance has been improved in controlling the rigid flexible satellite attitude and suppressing vibrations.
Keywords: ACS, Satellite rigid-flexible, Uncertain, H infinity

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References

Bigot, P. G.; Souza, L. C. G. Design of non-linear controller for a flexible rotatory beam using state-dependent riccati equation (sdre) control. Proceedings of the 2013 International Conference on Systems, Control and Informatics, p. 288 ”“ 295, 2013.

Gasbarri P., R. Monti, C. De Angelis, M. Sabatini, Effects of uncertainties and flexible dynamic contributions on the control of a spacecraft full-coupled model, Acta Astronautica, Volume 94, Issue 1, January”“February 2014, Pages 515-526, ISSN 0094-5765, http://dx.doi.org/10.1016/j.actaastro.2012.08.018.

Gu D.W., P. P. G.; M.M., K. Robust control design: with matlab. London, UK: Springer, 2005

Junkins, J. L, Kim, Y. "Introduction to dynamics and control of flexible structures". Washington, DC: American Institute of Aeronautics and Astronautics (AIAA), 1993.

Mainenti, L ; Souza, L.C. G ; De Souza, F. L. A comparative study between control strategies for a solar sailcraft in an Earth-Mars transfer. Mechanical Systems and Signal Processing, v. 1, p. 10, 2016.

Pinheiro, E.R., Souza L.C.G, Design of the Microsatellite Attitude Control System Using the Mixed H2/H∞ Method via LMI Optimization, Mathematical Problems in Engineering, vol. 2013, Article ID 257193, 8 pages, 2013. doi:10.1155/2013/25719.

Sidi, M. J. Spacecraft dynamics and control: A pratical engineering approach. NewYork, NY: Cambridge University Press, 1997.

Skogestad, S, Postlethwaite, I. Multivariable feedback control: analysis and design. Chichester, UK: John Wiley and Sons, 2001.

Souza, A.G, Souza, L. C. G, H infinity controller design to a rigid-flexible satellite with two vibration modes, Journal of Physics: Conference Series, vol. 641, pp. 012030, 2015.

Souza, L.C.G, Souza, A.G. Satellite Attitude Control System Design considering the Fuel Slosh Dynamics, Shock and Vibration, vol. 2014, 8, pages, 2014. doi:10.1155/2014/260206

Souza, L G C; Bigot, P. An adaptive method with weight matrix as a function of the state to design the rotatory flexible system control law. Mechanical Systems and Signal Processing, v. 1, p. 1, 2016.

Souza, L. C. G. Design of Satellite Control System Using Optimal Nonlinear Theory. Mechanics based design of structures and machines, 34(4), 351-364.2006

Zhou, K, Doyle, J. C, Essentials of robust control. Upper Saddle River, NJ:Prentice-Hall, 1998.

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Published

2017-02-08

How to Cite

Souza, A. G. de, & Souza, L. C. G. de. (2017). ATTITUDE CONTROL SYSTEM DESIGN FOR A RIGID-FLEXIBLE SATELLITE USING THE H-INFINITY METHOD WITH PARAMETRIC UNCERTAINTY. Revista Interdisciplinar De Pesquisa Em Engenharia, 2(19), 84–90. https://doi.org/10.26512/ripe.v2i19.15022

Issue

Vol. 2 No. 19 (2016): MODELING SIMULATION AND CONTROL OF AEROSPACE AND NAVAL STRUCTURES DYNAMICS (I)

Section

Artigos

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