27 March 2012 Novel controller design demonstration for vibration alleviation of helicopter rotor blades
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This paper presents an advanced controller design methodology for vibration alleviation of helicopter rotor sys- tems. Particularly, vibration alleviation in a forward ight regime where the rotor blades experience periodically varying aerodynamic loading was investigated. Controller synthesis was carried out under the time-periodic H2 and H framework and the synthesis problem was solved based on both periodic Riccati and Linear Matrix Inequality (LMI) formulations. The closed-loop stability was analyzed using Floquet-Lyapunov theory, and the controller's performance was validated by closed-loop high-delity aeroelastic simulations. To validate the con- troller's performance an actively controlled trailing edge ap strategy was implemented. Computational cost was compared for both formulations.
© (2012) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Fatma Demet Ulker, Fatma Demet Ulker, Fred Nitzsche, Fred Nitzsche, } "Novel controller design demonstration for vibration alleviation of helicopter rotor blades", Proc. SPIE 8341, Active and Passive Smart Structures and Integrated Systems 2012, 834108 (27 March 2012); doi: 10.1117/12.917520; https://doi.org/10.1117/12.917520


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