Abstract
In this paper a flexible smart wing is presented. The aileron wing with aileron was tested in the INCAS Subsonic Wind Tunnel with the aim of flutter mitigation and vibrations attenuation. The work takes over some of the results of the active anti-flutter control tests performed in the wind tunnel based on the receptance method. More specifically, the mathematical models in the time domain, necessary for the synthesis of control laws, are obtained from experimentally identified transfer functions. The main part of the paper presents the synthesis and analysis of the robustness of the control laws LQG, LQG/LTR, 𝐻𝐻∞ standard and 𝐻𝐻∞ robust from which the optimal solution will be chosen in a later work for the active vibration control tests on this smart wing model.
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