Precise pointing accuracy and rapid maneuvering are two key features for attitude control missions of small spacecraft. Control moment gyroscopes (CMGs) are applied as ideal actuator for large torque output capability but are usually limited due to the problem of inherent mechanical singularity. This paper proposes a robust attitude control methodology, based on Sliding Mode Control (SMC) techniques, in presence of CMG practical restrictions and disturbances. Two second-order SMC techniques are designed, to guarantee accuracy and limited convergence time. Moreover, attitude control torques are generated by means of four single gimbal CMGs in pyramidal configuration, considering the design of an experimental testbed. The effectiveness of the proposed methodologies are shown in simulations, for different mission scenarios, including singularity points.
Design of Sliding Mode Techniques for a CMG-based Testbed Attitude Control System / D'Ortona, A.; Capello, E.; Satoh, S.. - 54:(2021), pp. 506-511. (Intervento presentato al convegno 3rd IFAC Conference on Modelling, Identification and Control of Nonlinear Systems MICNON 2021 tenutosi a jpn nel 2021) [10.1016/j.ifacol.2021.10.405].
Design of Sliding Mode Techniques for a CMG-based Testbed Attitude Control System
Capello E.;
2021
Abstract
Precise pointing accuracy and rapid maneuvering are two key features for attitude control missions of small spacecraft. Control moment gyroscopes (CMGs) are applied as ideal actuator for large torque output capability but are usually limited due to the problem of inherent mechanical singularity. This paper proposes a robust attitude control methodology, based on Sliding Mode Control (SMC) techniques, in presence of CMG practical restrictions and disturbances. Two second-order SMC techniques are designed, to guarantee accuracy and limited convergence time. Moreover, attitude control torques are generated by means of four single gimbal CMGs in pyramidal configuration, considering the design of an experimental testbed. The effectiveness of the proposed methodologies are shown in simulations, for different mission scenarios, including singularity points.File | Dimensione | Formato | |
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https://hdl.handle.net/11583/2951761