H infinity controller design to a rigid-flexible satellite with two vibration modes

17th Brazilian Colloquium on Orbital Dynamics

De Souza, A.G.^1 ; De Souza, L.C.G.^2

National Institute for Space Research (INPE), Av. dos Astronautas 1758, Sao Jose dos Campos, SP

12227-010, Brazil^1

Brasilia University, Campus Gama, Area Especial de Industria-A-UnB, Brasilia, DF

72444-240, Brazil^2

关键词: Flexible deformation;    Flexible solar panels;    H-infinity controller;    Mechanical manipulators;    Pointing accuracy;    Satellite attitude;    Satellite attitude control systems;    Satellite structure;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/641/1/012030/pdf
DOI  :  10.1088/1742-6596/641/1/012030

来源: IOP

【 摘 要 】

The satellite attitude control system (ACS) design becomes more complex when the satellite structure has components like, flexible solar panels, antennas and mechanical manipulators. These flexible structures can interact with the satellite rigid parts during translational and/or rotational manoeuvre damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances thus affecting the satellite attitude acquisition. This paper deals with the rigid-flexible satellite ACS design using the H infinity method. The rigid-flexible satellite is represented by a beam connected to a central rigid hub at one end and free at the other one. The equations of motions are obtained considering small flexible deformations and the Euler-Bernoulli hypothesis. The results of the simulations have shown that the H-infinity controller was able to control the rigid motion and suppress the vibrations.