Active control of panel flutter with piezoelectric transducers

Frampton, Kenneth D.; Clark, Robert L.; Dowell, Earl H.

doi:10.2514/3.47013

Cited by 34 publications

(20 citation statements)

References 12 publications

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“…In particular, the fast-responding piezo-electric materials have advantageously been integrated into the conventional structural systems as distributed sensors and actuators for active panel flutter suppression. For instance, Frampton et al [17] studied active control of linear panel flutter in the transonic and low supersonic flow regime by using a collocated direct rate feedback controller with a self-sensing piezo-electric segment. Sadri et al [42] applied the linear quadratic Gaussian (LQG) control methodology with optimally placed piezo-electric actuators for active flutter suppression of an aerospace panel structure.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow

Hasheminejad

Motaaleghi

2015

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 99%

Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow

Hasheminejad

Motaaleghi

2015

Aerospace Science and Technology

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“…͑37͒. The curved piezo-structure model can be validated through comparison with the flat piezo-structure model developed by Frampton et al, 7 by allowing the radius of curvature of the curved panel to approach infinity. Figures 2-4 show the reduction of the curved piezo-structure model to the flat piezo-structure model as the radius of curvature approaches infinity.…”

Section: A Model Validationmentioning

confidence: 99%

A curved piezo-structure model: Implications on active structural acoustic control

Henry

Clark

1999

The Journal of the Acoustical Society of America

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Current research in Active Structural Acoustic Control (ASAC) relies heavily upon accurately capturing the application physics associated with the structure being controlled. The application of ASAC to aircraft interior noise requires a greater understanding of the dynamics of the curved panels which compose the skin of an aircraft fuselage. This paper presents a model of a simply supported curved panel with attached piezoelectric transducers. The model is validated by comparison to previous work. Further, experimental results for a simply supported curved panel test structure are presented in support of the model. The curvature is shown to affect substantially the dynamics of the panel, the integration of transducers, and the bandwidth required for structural acoustic control.

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“…1, Npr { N }T . (8) Since the values of the tensile stress resultants are known, Hooke's law can be used to obtain an expression for the strain vector in terms of the tensile stress resultants:…”

Section: (5)mentioning

confidence: 99%

<title>Smart aircraft panels: the effects of internal pressure loading on panel dynamics</title>

Henry

Clark

1999

SPIE Proceedings

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Research is currently underway on the development of smart aircraft panels for the reduction of interior cabin noise. This research seeks to adapt previous Active Structural Acoustic Control (ASAC) research on flat plates with attached piezoelectric actuators to the curved panels that compose the exterior skin of an aircraft. In order to predict accurately the closed ioop performance of ASAC systems for interior cabin noise reduction, efforts are being made to consider complicating factors in the dynamics of aircraft panels. As part of this research, a state-space model of a curved piezostructure was developed and used to investigate the effects of curvature on panel dynamics. Panel curvature was shown to increase control system bandwidth and to affect transducer coupling. In the present work, the effects of internal pressure loading on the dynamics of a curved piezostructure are investigated through the extension of the previously developed state-space model. The internal pressure model is verified based upon previous work. Pressure loading is shown to increase panel stiffness, thus increasing the natural frequencies of the panel. Further, pressure loading is shown to affect certain modes more than others, resulting in modal reordering. The increased natural frequencies and the modal reordering significantly affect control system bandwidth and raise further issues in control design.

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Active control of panel flutter with piezoelectric transducers

Cited by 34 publications

References 12 publications

Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow

Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow

A curved piezo-structure model: Implications on active structural acoustic control

<title>Smart aircraft panels: the effects of internal pressure loading on panel dynamics</title>

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