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TECHNICAL PAPERS

Genetic Spatial Optimization of Active Elements on an Aeroelastic Delta Wing

[+] Author and Article Information
Robert E. Richard, John A. Rule, Robert L. Clark

Department of Mechanical Engineering and Material Science, Duke University, Durham, NC 27708-0302

J. Vib. Acoust 123(4), 466-471 (May 01, 2001) (6 pages) doi:10.1115/1.1389458 History: Received September 01, 2000; Revised May 01, 2001
Copyright © 2001 by ASME
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References

Rule, J. A., Richard, R. E., and Clark, R. L., 2000, “Experimental Investigation of Delta Wing Flutter Control,” AIAA J.,
Smith, G. C., 2000, “Design Methodologies for Optimum Spatial Compensation of Adaptive Structures,” Ph.D. Dissertation, Duke University, Durham, NC.
Lim,  K. B., and Gawronski,  W., 1996, “Hankel Singular Values of Flexible Structures in Discreet time,” J. Guid. Control Dyn. , 19(6), pp. 131–145.
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Clark,  R. L., and Cox,  D. E., 1999, “Band-Limited Actuator and Sensor Selection for Disturbance Rejection: Application to Structural Acoustic Control,” J. Guid. Control Dyn. , 22(5), pp. 740–743.
Rule, J. A., Richard, R. E., and Clark, R. L., 2000, “Design of an Aeroelastic Wing Model for Active Flutter Control,” J. Guid. Control Dyn.
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Clark, R. L., Saunders, W. R., and Gibbs, G. P., 1998, Adaptive Structures, John Wiley and Sons, Inc., New York, N.Y.
Rule, J. A., Cox, D. E., and Clark, R. L., 2000, “Aerodynamic Model Reduction Through Balanced Realization,” AIAA Journal.
Hagood, N. W., Chung, W. H., and Von Flotow, A., 1990, “Modeling of Piezoelectric Actuator Dynamics for Active Structural Control,” Proceedings of the 31st AIAA/ASME/ASCE/AHS Structures, Structural Dynamics and Materials Conference, April 2–4, pp. 2242–2256, AIAA-90-1087-CP.
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Figures

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Block diagram of aeroelastic system
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Migration of the open-loop aeroelastic poles with flow speed. Instability was predicted where the second mode moved into the right half plane corresponding to 31.5 m/s at 18 Hz.
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Conversion of the ten parameter patch-pair description vector to normalized binary form
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Plot shows contrast in goal convergence between routine with best parent retained and discarded
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Results comparison of four independent optimization runs showing patch placement and associated response plots. The contours around the patches indicate areas of high likelihood for patch construction. The vertical axes correspond to magnitudes of (v/v).
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Comparison between pairs determined by alternate optimization methods
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Block diagram of two-port for controller design
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Predicted open and closed-loop response of the wing in pre-flutter flow (31 m/s) with the selected patch pair
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Closed-loop aeroelastic pole migrations (parameterized by flow velocity), showing a 17 Hz instability at 38.3 m/s.
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Open-loop vs. closed-loop response of wing at 38 m/s with clearly visible harmonics in the uncontrolled case

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