Optimal Control Procedure Application for Dynamic Response of Adaptive Aircraft Wings Modeled as Thin-Walled Composite Beams

Kaan Yildiz; Seher Eken; Metin Orhan Kaya

doi:10.4028/www.scientific.net/AMM.798.292

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 798Optimal Control Procedure Application for Dynamic...

Optimal Control Procedure Application for Dynamic Response of Adaptive Aircraft Wings Modeled as Thin-Walled Composite Beams

Abstract:

In this study we investigated the dynamical behavior of aircraft wings and using piezoelectric actuation we implemented active vibration control. The aircraft wing is modeled as a thin-walled composite beam having a cross section of diamond shaped. The dynamic response of the beam under varying proportional and velocity feedback gain parameters is obtained and shown to be enhanced with optimal control procedure, minimizing the control effort and response.

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Periodical:

Applied Mechanics and Materials (Volume 798)

Pages:

292-296

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.798.292

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Online since:

October 2015

Authors:

Kaan Yildiz*, Seher Eken, Metin Orhan Kaya

Keywords:

Active Vibration Control, Composite Beam, Dynamic Analysis, Optimal Control, Thin-Walled

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References

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