Abstract
Based on a previous theoretical work, this paper focuses on the experimental validation of a sliding mode control (SMC) technique applied to an aerodynamic angular system (AAS). To do so, an aerodynamic experimental platform is presented together with its electronic interface and its closed-loop behavior generated by the aforementioned SMC strategy. The control performance is widely reviewed under different regulation tasks and gain variations. Experimental results prove that the control strategy guarantees a stable behavior. Moreover, the robustness of the control strategy is proved when the system is subject to the influence of external disturbances.
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