• Proceedings of the Computational Structural Engineering Institute Conference
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• 2011.04a
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• pp.119-122
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• 2011

분자동역학 전산모사를 통하여 에폭시에 다양한 반경의 구형 실리콘 카바이드를 삽입한 나노복합재를 모델링하고, 이들의 기계적 물성과 열적 물성 해석을 다양한 온도조건 하에서 수행하였다. 전산모사 결과 동일한 체적분율 하에서 나노복합재는 입자의 크기가 작아질수록 탄성계수와 전단계수가 상승하는 동시에 선팽창계수는 감소하는 입자의 크기효과를 보였다. 또한 온도 상승에 따른 기계적 물성의 하락이 잘 관찰되었다. 본 연구에서는 이러한 분자동역학 해석 결과를 바탕으로 다양한 온도조건 하에서의 입자의 크기효과를 고려한 멀티스케일 3상 모델을 제시하였다. 유리상 조건 범위에서 온도 변화에 따른 나노복합재 계면의 열응력텐서와 열변형률텐서의 정보를 통해 복합재 내에서 계면이 차지하는 부피비를 온도에 대한 함수로 고려하고, 이를 멀티스케일 모델에 반영함으로써 다양한 온도조건에 대한 나노복합재 열탄성 물성의 예측해를 제시하였다. 본 연구에서 제시한 모델에서 계산된 3상 복합재의 물성은 분자동역학 전산모사의 결과에서 나타나는 나노입자의 크기효과를 잘 반영하였다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2013.04a
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• pp.528-532
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• 2013

In this study, an analytical model of micro-beam structure including thermoelastic damping with irregularly distributed masses is investigated. The significance of thermoelastic damping for micro-scale mechanical resonators is evaluated to design -with high quality factor(Q-factor). The beam model of this work is based on Euler-Bernoulli beam theory. In order to determine the natural frequency of the model, energy method is applied. Also, the thermoelatic damping effects are considered by using heat conduction equations, and the Q-factor can be determined. To derive the equation of motion, non-dimensionalization is employed for systematic analysis. Results of the model are verified, and present mode shapes and Q-factors for the micro-beam with thermoelastic damping including random point masses.

• Journal of the Korean Society for Precision Engineering
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• v.23 no.10
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• pp.30-35
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• 2006

• Transactions of the Korean Society of Mechanical Engineers A
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• v.21 no.3
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• pp.393-404
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• 1997

SPATE(Stress Pattern Analysis by Thermal Emission) can be effectively used to analyze the stress distributions of isotropic structure under the repeated load by non-contact. In this research, the measuring method and the measuring concept of stress intensity factor of isotropic material by SPATE are suggested. The validity of the method and the concept was certified through SPATE experiment.

• Proceedings of the Optical Society of Korea Conference
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• 2005.02a
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• pp.42-43
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• 2005

• Composites Research
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• v.25 no.2
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• pp.34-39
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• 2012

A thermo-poro-elastic constitutive model of unidirectionally fiber-reinforced composite materials is suggested by extending the unmixing-mixing scheme which is based upon composite micromechanics. The strain components of thermal expansion due to a temperature change, gas pressure in pores, and chemical shrinkage are included in the constitutive model. On purpose to verify the derived constitutive relations, the representative volume element of two-dimensional lamina subject to various loading conditions is analyzed by the finite element method. The overall stress and strain responses are obtained, and compared with the predicted values by the unmixing-mixing scheme. The numerical results show the usefulness of the proposed model to predict the thermoelastic behavior of porous composites.

• The Journal of the Acoustical Society of Korea
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• v.38 no.4
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• pp.459-466
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• 2019

When a laser pulse is irradiated on a CNT (Carbon Nanotube) and PDMS (Poly dimethylsiloxane) composite coated on a transparent PMMA (Poly methyl methacrylate) substrate, a strong ultrasonic wave is generated due to the thermoelastic effect. In this paper, the thermoacoustic theory related to the wave generation by the CNT/PDMS composite was established. The waveforms of ultrasonic waves when a laser pulse having a Gaussian waveform is irradiated on the composite with a thickness of $20{\mu}m$ were numerically simulated. From the results, it was confirmed that ultrasonic shock waves can be generated from the CNT/PDMS composite and the waveforms are changed little even if the physical properties of the composite are changed by ${\pm}20%$. It was found that the peak positive and negative pressures increase as the thermal expansion coefficient increases, or as density, heat capacity and sound speed decreased. However, those changes were not so sensitive with thermal conductivity. In addition, the physical properties of the CNT/PDMS composite fabricated in this study were estimated from the comparison of the measurement and simulation results.

• Journal of the Korean Society for Nondestructive Testing
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• v.26 no.5
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• pp.315-320
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• 2006

This paper describes stress analysis and fatigue limit evaluation of plate with V-notch and hole-notch by lock-in infrared thermography. Temperature variation of a specimen under cyclic loading is negatively proportional to the sum of principle stress change and the surface temperature measured by infrared camera is calculated to the stress of notch specimens, based on thermoelastic equation. And also, fatigue limitation can be evaluated by the change of intrinsic energy dissipation. Fatigue limitation of two notch specimens is evaluated as 164 MPa and 185 MPa, respectively and the stress measured by Lock-in infrared Thermography show good agreement within 10% error.

• Proceedings of the Optical Society of Korea Conference
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• 2003.07a
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• pp.144-145
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• 2003

열상카메라는 빛이 전혀 없는 야간에도 선명한 영상을 획득할 수 있도록 구성된 장비이다. 이러한 열상카메라는 야간 영상 획득에 있어서 많은 분야에서 사용되고 또한 반드시 사용되어야만 한다. 또한 열상카메라를 구성하기 위하여 사용되는 렌즈의 재질은 온도에 대한 굴절률의 변화가 크고 경도가 낮아 외부 환경에 대한 영향성이 크다. 열상카메라의 성능에 영향을 주는 외부 환경 요소로는 열상카메라가 사용되는 환경에서 발생하는 진동의 요인과 내부 및 외부로부터 받는 온도에 대한 요인이다. (중략)

• Composites Research
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• v.15 no.3
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• pp.52-61
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• 2002

For the aerothermoelastic analysis of cylindrical piezolaminated shells, geometrically nonlinear finite elements based on the multi-field layerwise theory hale been developed. Applying a Han Krumhaar's supersonic piston theory, supersonic flutter analyses are performed for the cylindrical piezolaminted shells subject to thermal stresses and deformations. The possibility to increase flutter boundary and reduce thermoelastic deformations of piezolaminated panels is examined using piezoelectric actuations. Results show that active piezoelectric actuations can effectively increase the critical aerodynamic pressure by retarding the coalescence of flutter modes and compensating thermal stresses.