Finite element modeling of a plate with localized piezoelectric sensors and actuators

This study presents a free vibration analysis of a laminated composite beam, based on the Euler-Bernoulli beam theory. A numerical model of the laminated composite beam was obtained for various boundary conditions based on different length-to-thickness ratios for a number of layers, using the finite element method. A planar beam bending element with two nodes, each having two degrees of freedom, was chosen according to Euler-Bernoulli beam theory. The natural frequencies of the laminated composite beam were obtained for each case, and presented in such a way as to display the effect of these changes on the natural frequencies. Eight natural frequencies of clamped-free, clamped-clamped (CC) and simple-simple (SS) composite beams were first obtained for different length-to-thickness ratios (L x /h), numbers of layers, layer angles and for their different positions. It can be seen that natural frequencies decrease for all modes with increasing length-to-thickness ratio in all cases.

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“…(24) is substituted into Eq. (18) in a matrix form and expanded for each node: (Abreu, Riberio, & Steffen, 2004),…”

Section: Development Of Shape Functionmentioning

confidence: 99%

Free Vibration Analysis of a Laminated Composite Beam with Various Boundary Conditions

Balcı¹,

Nalbant²,

Kara³

et al. 2014

Int J Automot Mech Eng

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“…(19), a is the coefficient vector and P is the interpolation polynomial term vector. The coefficient and the interpolation polynomial term vector are given in the following format (De Abreu et al, 2004):…”

Section: Development Of Shape Functionmentioning

confidence: 99%

Determination of Physical Properties of Laminated Composite Beam via the Inverse Vibration Problem Method

Balcı¹,

Gündoğdu²

2013

J MECH ENG SCI

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In this study, some physical properties of a laminated composite beam were estimated by using the inverse vibration problem method. Laminated composite plate was modeled and simulated to obtain vibration responses for different length-to-thickness ratios in ANSYS. A numerical model of the laminated composite beam with unknown parameters was also developed using a two-dimensional finite element model by utilizing the Euler-Bernoulli beam theory. Then, these two models were embedded into the optimization program to form the objective function to be minimized using genetic algorithms. After minimizing the squared difference of the natural frequencies from these two models, the unknown parameters of the laminated composite beam were found. It is observed in this study that the Euler-Bernoulli beam theory suppositions approximated the real results with a rate of %0.026 error as the thickness of the beam got thinner. The estimated values were finally compared with the expected values and a very good correspondence was observed.

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“…For the purpose of the control design for the vibration suppression discrete-time control design tools were used, such as optimal Linear Quadratic (LQ) controller incorporated in a tracking system. In reference [5] a numerical modeling of a plate structure containing bonded piezoelectric material was presented. A numerical model is developed based on Kirchhoff's plate theory.…”

Section: Introductionmentioning

confidence: 99%

Active Vibration Suppression of Acrobatic Aircraft Wing by Acceleration Feedback Controller

Ali¹,

Saeed²

2017

IJCA

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Vibration of some structures might be accepted under restricted limits depending on their design, application and many other factors. Aircraft wing is a structure need to be stable as possible, but there are many disturbances act on wing, so using of active vibration control for vibrated wing can serve to eliminate or suppress the major amount of wing oscillation. In the present work, direct acceleration feedback method is utilized to be used as a controlling technique to satisfy wing stability. Numerical model was simulated in ANSYS environment where the controlling method was totally integrated to generate necessary actuation voltage to derive piezoelectric actuators based on acceleration feedback. Six piezoelectric transducers were modeled in ANSYS by using element SOLID5. Experimental part includes manufacturing (1:6) scaled aircraft wing with two boxes inside and equipped with six piezoelectric transducers worked as sensor/actuator besides labview software inside which the controlling loop was integrated. Modal analysis was performed for numerically simulated model and includes the first six modes of vibration. Free and controlled responses of the tested wing were presented for numerical and experimental model. Results show high degree of agreement between experimental and numerical models. Results show that utilizing the acceleration feedback method for active vibration controlling method can suppress wing vibration and that will pave the way for further application of this controlling method.

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Finite element modeling of a plate with localized piezoelectric sensors and actuators

Cited by 38 publications

References 17 publications

Free Vibration Analysis of a Laminated Composite Beam with Various Boundary Conditions

Free Vibration Analysis of a Laminated Composite Beam with Various Boundary Conditions

Determination of Physical Properties of Laminated Composite Beam via the Inverse Vibration Problem Method

Active Vibration Suppression of Acrobatic Aircraft Wing by Acceleration Feedback Controller

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