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Research Papers

Numerical Investigation on the Selection of the System Outputs for Feedback Vibration Control of a Smart Blade Section

[+] Author and Article Information
Nailu Li

Assistant Professor
Mem. ASME
School of Hydraulic,
Energy and Power Engineering,
Yangzhou University,
Yangzhou, Jiangsu 225127, China
e-mail: nlli@yzu.edu.cn

Mark J. Balas

Distinguished Professor
Fellow ASME
Aerospace Engineering,
Embry-Riddle Aeronautical University,
Daytona Beach, FL 32114-3900
e-mail: balasm@erau.edu

Hua Yang

Professor
School of Hydraulic,
Energy and Power Engineering,
Yangzhou University,
Yangzhou, Jiangsu 225127, China

Wei Jiang

Associate Professor
School of Hydraulic,
Energy and Power Engineering,
Yangzhou University,
Yangzhou, Jiangsu 225127, China

1Corresponding author.

Contributed by the Technical Committee on Vibration and Sound of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received May 11, 2015; final manuscript received February 23, 2016; published online April 15, 2016. Assoc. Editor: Walter Lacarbonara.

J. Vib. Acoust 138(3), 031013 (Apr 15, 2016) (11 pages) Paper No: VIB-15-1162; doi: 10.1115/1.4033055 History: Received May 11, 2015; Revised February 23, 2016

This study presents the possible and effective output signals for the feedback vibration control of the smart blade section undergoing different aerodynamic conditions. Equations of motions of the smart blade section are described by a typical wing section model, leading to three vibration modes (flapwise mode, edgewise mode, and torsional mode). The aerodynamics is described by an unsteady aerodynamic model and aerodynamic effects of the microtab installed on the trailing-edge of the blade section. The equations of the aeroservoelastic model are summarized into state-space equation for analysis of output choice in the feedback system. All vibration modes are proved to be fully controllable with the microtab actuation. The numerical results show that the most effective output signal is the combination of flapwise velocity and torsional velocity for the system undergoing the attached flow and the combination of all three-mode velocities for the system undergoing the stall flow. In addition, the output choice for different microtab configurations is also analyzed. The effectiveness of the proposed output signals in vibration control is confirmed by the simulation results.

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Figures

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Fig. 1

Model of the blade section with microtabs

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Fig. 2

System dynamic improvement with microtab configurations by different output choice and control gain of −1: (a) damping ratio and (b) natural frequency

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Fig. 3

System dynamic improvement with microtab configurations by different output choice and control gain of −100: (a) damping ratio and (b) natural frequency

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Fig. 4

Closed-loop system responses with proposed output choice for the system at angle of attack 2 deg: (a) edgewise deflection, (b) flapwise deflection, and (c) torsional deflection

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Fig. 5

Closed-loop system responses with proposed output choice for the system at angle of attack 12 deg: (a) edgewise deflection, (b) flapwise deflection, and (c) torsional deflection

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