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Closed-loop flutter control using strain actuation

Published online by Cambridge University Press:  03 February 2016

S. B. Kandagal  and
K. Venkatraman
S. B. Kandagal
Affiliation:
Aeroservoelasticity Laboratory, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
K. Venkatraman
Affiliation:
Aeroservoelasticity Laboratory, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
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Abstract

The present work investigates feedback control of flutter using piezoceramic strain actuators. A two degree-of-freedom oscillating airfoil model with the air loads simulated assuming unsteady aerodynamics is considered. Various feedback measurement combinations for SISO feedback control and strain actuation in the heave and pitch direction are studied to quantify their effect on flutter. The effect of sensor placement on the airfoil, for combined pitch and heave measurement feedback, is also studied. The results show that for a given aeroelastic system, sensor location is an important parameter in realizing an increase in the flutter speed. It is demonstrated that the flutter speed can be increased by more than 50% through strain actuation in the pitch direction.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1083 , May 2004 , pp. 271 - 275
Copyright
Copyright © Royal Aeronautical Society 2004 

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References

1. Crawley, E.F. Intelligent structures for aerospace: A technology overview and assessment, AIAA J, 1994, 32, (8), pp 1689–1699.Google Scholar
2. Lowey, R.G. Recent developments in smart structures with aeronautical applications, Smart Mater and Struct, 1987, 6, pp R11-R42.Google Scholar
3. Nitzsche, F., Liberatore, S. and Zimcik, D.G. Theoretical and experimental investigations on an active control system for vertical fin buffeting allevation using strain actuation, Aeronaut J, 2001, 105, (1047), pp 277–285.Google Scholar
4. Horikawa, H. and Dowell, E.H. An elementary explanation of the flutter mechanism with active feedback controls, J Aircr, 1979, 16, (4), pp 225–232.Google Scholar
5. Lazarus, K.B., Crawley, E.F. and Lin, C.Y. Fundamental mechanism of aeroelastic control with control surface and actuation, J Guidance, Control, and Dynamics, 1995, 18, (1), pp 10–17.Google Scholar
6. Heeg, J. An analytical and experimental investigation of flutter suppression via piezoelectric actuation, AIAA-92-2106-CP, 1992.Google Scholar
7. Heeg, J. Analytical and experimental investigation of flutter suppression via piezoelectric actuation, NASA-TP-3241, 1993.Google Scholar
8. Reich, G.W. An active aeroelastic wing model for vibration and flutter suppression, AIAA-95-1193-CP, 1995.Google Scholar
9. Mcgowan, A-M.R., Wilkie, W.K., Moses, R.W., Renee, C., Flo-Rance, J.P., Wieseman, C.D., Reaves, M.C., Taleghani, P.H., Mirick, P.H. and Wilbur, M.L. Aeroservoelastic and structural dynamic research on smart structures conducted at NASA Langley Research Center, SPIE, 1998, 3326, pp 188–201.Google Scholar
10. Bisplinghoff, R.L., Ashley, H. and Halfman, R.L. Aeroelasticity, Addison-Wesley Publishing Company, Cambridge, 1955.Google Scholar
11. Fung, Y.C. An Introduction to the Theory of Aeroelasticity, John Wiley & Sons, New York, 1955.Google Scholar
12. Crawley, E.F. and De Luis, J. Use of piezoelectric actuators as elements of intelligent structures, AIAA J, 1987, 25, (10), pp 1373–1385.Google Scholar