Design of active flutter suppression and wind-tunnel tests of a wing model involving a control delay |
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| Affiliation: | 1. Japan Aerospace Exploration Agency, Mitaka, Tokyo 181-0015, Japan;2. Department of Aeronautics and Astronautics, University of Tokyo, Hongo, Tokyo 113-8656, Japan;3. Department of Aerospace Engineering and Mechanics, University of Alabama, Box 870280, Tuscaloosa, AL 35487-0280, USA;1. State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace, Xi’an Jiaotong University, Xi’an 710049, China;2. Shannxi Key Laboratory for Environment and Control of Flight Vehicle, School of Aerospace, Xi’an Jiaotong University, Xi’an 710049, China;3. Faculty of Engineering and the Environment, University of Southampton, Southampton SO17 1BJ, UK;1. School of aeronautics, Northwestern Polytechnical University, 127 Youyixi Road, Xi׳an, Shaanxi 710072, PR China;2. University of Toronto Institute for Aerospace Studies, 4925 Dufferin Street, Toronto, ON, Canada M3H 5T6;3. Mitsubishi Electric Research Laboratories (MERL), Cambridge, MA 201 Broadway, Cambridge, MA, 02139, USA |
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| Abstract: | In this study, a delayed controller was designed for active flutter suppression of a three-dimensional wing model. The design of controller can be divided into two steps. At the first step, a short time delay was artificially introduced into the control loop and the dynamic equations of the aeroelastic system with delayed control were converted into a set of delay-free state-space equations by using a state transformation. At the second step, the control law was synthesized by using the theory of optimal control for the delay-free state-space equations. To demonstrate the performance of the delayed controller, the margin of time delay was studied. The numerical results showed that the delayed controller had good robustness with respect to the time delay. Moreover, the delayed controller was digitally implemented and tested for the three-dimensional wing model in NH-2 subsonic wind-tunnel. The experimental results illustrated that the critical flow speed of flutter instability of the wing model could be effectively increased from 36.5 m/s to 39 m/s. |
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| Keywords: | Flutter Time delay Aeroelastic control Wind-tunnel tests |
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