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DINAME2019
DINAME2019
Attitude and vibration control of satellites featuring flexible panels combining reaction wheels and viscoelastic materials
Submission Author:
Domingos Rade , SP , Brazil
Co-Authors:
Thiago de Paula Sales, Ijar DA FONSECA, Lewton Machado Rodrigues, Domingos Rade
Presenter: Thiago de Paula Sales
doi://10.26678/ABCM.DINAME2019.DIN2019-0199
Abstract
It is widely known that elastic vibrations of highly flexible appendages, such as solar panels, can jeopardize the pointing accuracy of spacecraft, which can be subjected to very strict requirements in a number of practical situations. In this context, this paper addresses the attitude and vibration control of artificial satellites featuring flexible solar panels, by combining reaction wheels for attitude control and viscoelastic materials for the attenuation of elastic vibrations of the panels. First, a high-fidelity three-dimensional finite element model developed for the modeling of the flexible parts of the satellite is presented. The model accounts for the presence of viscoelastic dampers either in the form of springs interconnecting the segments of the panels, or as one of the layers that compose the frames that make up the structure of the panels. The viscoelastic behavior is modeled by using a constitutive model based on derivatives of fractional order, which is convenient for both frequency domain and time domain simulations. The finite element model is associated to the rigid-body equations of motion, which enable to represent the attitude motion of the satellite in terms of Euler’s angles. For a previously selected attitude correction maneuver driven by the activation of the reaction wheels commanded by a proportional-integral-derivative controller, the model is used to investigate the benefits that the use of viscoelastic dampers can provide in terms of reduction of vibration levels of the panel, and minimization of attitude perturbations.
Keywords
attitude control, Vibration control, viscoelastic damping, flexible spacecraft
