Active control for flutter suppression: an experimental investigation
Active control for flutter suppression: an experimental investigation
This paper describes an experimental study involving the implementation of the method of receptances to control binary flutter in a wind-tunnel aerofoil rig. The aerofoil and its suspension were designed as part of the project. The advantage of the receptance method over conventional state-space approaches is that it is based entirely on frequency response function measurements, so that there is no need to know or to evaluate the system matrices describing structural mass, aeroelastic and structural damping and aeroelastic and structural stiffness. There is no need for model reduction or the estimation of unmeasured states, for example by the use of an observer. It is demonstrated experimentally that a significant increase in the flutter margin can be achieved by separating the frequencies of the heave and pitch modes. Preliminary results from a complementary numerical programme using a reduced-order model, based on linear unsteady aerodynamics, are also presented
Papatheou, E.
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Tantaroudas, N. D.
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Da Ronch, A.
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Cooper, J. E.
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Mottershead, J. E.
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June 2013
Papatheou, E.
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Tantaroudas, N. D.
12303349-1026-48e8-ba09-8c4d59f65d43
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Cooper, J. E.
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Mottershead, J. E.
a6691044-dc2b-4ac0-8249-ee5d8b445150
Papatheou, E., Tantaroudas, N. D., Da Ronch, A., Cooper, J. E. and Mottershead, J. E.
(2013)
Active control for flutter suppression: an experimental investigation.
International Forum on Aeroelasticity and Structural Dynamics (IFASD), Bristol, United Kingdom.
24 - 27 Jun 2013.
14 pp
.
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Conference or Workshop Item
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Abstract
This paper describes an experimental study involving the implementation of the method of receptances to control binary flutter in a wind-tunnel aerofoil rig. The aerofoil and its suspension were designed as part of the project. The advantage of the receptance method over conventional state-space approaches is that it is based entirely on frequency response function measurements, so that there is no need to know or to evaluate the system matrices describing structural mass, aeroelastic and structural damping and aeroelastic and structural stiffness. There is no need for model reduction or the estimation of unmeasured states, for example by the use of an observer. It is demonstrated experimentally that a significant increase in the flutter margin can be achieved by separating the frequencies of the heave and pitch modes. Preliminary results from a complementary numerical programme using a reduced-order model, based on linear unsteady aerodynamics, are also presented
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IFASD-2013-8D.pdf
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Published date: June 2013
Additional Information:
Paper 2013-8D
Venue - Dates:
International Forum on Aeroelasticity and Structural Dynamics (IFASD), Bristol, United Kingdom, 2013-06-24 - 2013-06-27
Organisations:
Aerodynamics & Flight Mechanics Group
Identifiers
Local EPrints ID: 353428
URI: http://eprints.soton.ac.uk/id/eprint/353428
PURE UUID: caca007b-6ba8-448f-a101-66aadd35afaa
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Date deposited: 06 Jun 2013 13:35
Last modified: 15 Mar 2024 03:46
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Contributors
Author:
E. Papatheou
Author:
N. D. Tantaroudas
Author:
J. E. Cooper
Author:
J. E. Mottershead
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