Optimal Design of Smart Skin Structures for Thermo-Mechanical Buckling and Vibration using a Genetic Algorithm

Yoo, Kwangkyu; Kim, Ji‐Hwan

doi:10.1080/01495739.2011.601261

Cited by 9 publications

(10 citation statements)

References 19 publications

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“…Additionally, the above angles are applied to top, face and bottom composite layers. The natural frequencies are decreased as the dielectric portion is increased, and then the present results are good agreement with reference [15]. Next, Figure 3 represents the limit cycle amplitudes of the panel to check the validity of time integration routine.…”

Section: Verificationsupporting

confidence: 72%

“…Until recently, various smart skin models have been investigated in terms of the staking sequences and shapes of dielectric layer [10][11][12][13][14][15][16]. In this work, the skin is modeled as multi-layered sandwich structure as in reference [14].…”

Section: Numerical Results and Discussionmentioning

confidence: 99%

“…Also, honeycomb core transmits shear between the sheets, and provides an air gap to the structure as shown in Ref. [15,16]. Furthermore, the dielectric layer has special characteristics to reduce the radar cross section (RCS) and increase stealth functions.…”

Section: Introductionmentioning

confidence: 99%

“…Further, Yoon et al [14] made a structure, and compared with the experiments and numerical results for unidirectional compressed status. Currently, Yoo and Kim [15] investigated optimal design of smart skin structures for thermo-mechanical buckling and vibration using genetic algorithm. Also, Lee et al [16] performed the design, and experimentally validated the skin model.…”

Section: Introductionmentioning

confidence: 99%

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Thermal Stability Characteristics and Limit Cycle Oscillation of Smart Skin Structures

Lee

Kim

2013

Journal of Thermal Stresses

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Smart skin structures are analyzed for thermal stability behaviors and limit cycle oscillations in supersonic range of airflows. The skin is made up of multi-layered sandwich panel using carbon/epoxy, glass/epoxy, and dielectric polymer layers. And the model is based on the first-order shear deformation plate theory, and von Karman strain-displacement relationships are used to consider the moderate geometrical nonlinearity of the structure. In order to study the effects of the airflow, first-order piston theory is adopted to represent the pressures. Also, Newmark time integration method is applied to obtain the numerical results in this work. To check the validity of present outcomes, results are compared with previous data. Specifically, the stability boundaries are obtained for various ranges of temperatures and aerodynamic pressures. Then, the regions for buckling, post-buckling, dynamic instability, and limit cycle oscillation of the structures are clearly discussed. For more analysis, the smart skin is investigated for the different sizes and shapes of dielectric portion within enclosure layer in detail.

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Section: Verificationsupporting

confidence: 72%

Section: Numerical Results and Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Thermal Stability Characteristics and Limit Cycle Oscillation of Smart Skin Structures

Lee

Kim

2013

Journal of Thermal Stresses

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“…Lee and Kim studied the thermal stability regions and obtained the limit cycle oscillation behaviors of smart skin antenna structures [6]. Further, Yoo and Kim [7] investigated optimal conditions of models for thermal buckling and vibration. Up to now, numerous works have studied the dynamic responses of structures under aerodynamic loads.…”

Section: Introductionmentioning

confidence: 99%

Active Flutter Suppression of Smart-Skin Antenna Structures with Piezoelectric Sensors and Actuators

Lee

Kim

2021

Aerospace

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A smart-skin antenna structure is investigated for active flutter control with piezoelectric sensors and actuators. The skin antenna is designed as a multilayer sandwich structure with a dielectric polymer to perform the role of antenna or radar structures. The governing equations are developed according to the first-order shear deformation theory, and von Karman strain–displacement relationships are used for the moderate geometrical nonlinearity. To consider the supersonic airflow, first-order piston theory is performed for the aerodynamic pressures. The linear quadratic regulator (LQR) method is applied as a control algorithm, and Newmark’s method is studied to obtain the numerical results. In the present study, the effects of placements and shape of piezoelectric patches are discussed on the flutter control of the model in detail. In addition, the numerical results show that the skin antenna model can effectively suppress the panel flutter behaviors of the model, optimal conditions of piezoelectric patches are obtained for skin antenna structures.

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Parallel Computing for Improving Optimization Performance of Laminated Composite Structures Application: Thermal Buckling

Majdoubi

Abdoun

2022

Advanced Intelligent Systems for Sustainable Development (AI2SD’2020)

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Optimal Design of Smart Skin Structures for Thermo-Mechanical Buckling and Vibration using a Genetic Algorithm

Cited by 9 publications

References 19 publications

Thermal Stability Characteristics and Limit Cycle Oscillation of Smart Skin Structures

Thermal Stability Characteristics and Limit Cycle Oscillation of Smart Skin Structures

Active Flutter Suppression of Smart-Skin Antenna Structures with Piezoelectric Sensors and Actuators

Parallel Computing for Improving Optimization Performance of Laminated Composite Structures Application: Thermal Buckling

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