• Proceedings of the Computational Structural Engineering Institute Conference
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• 2010.04a
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• pp.636-639
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• 2010

본 논문에서는 준정상 상태법을 이용한 열전도도 측정장치의 불확실도를 분석하고 측정된 열전도도의 불확실도에 가장 큰 영향을 미치는 요인이 온도 측정 센서의 정확도와 측정유체의 윗면과 아랫면의 온도 차임을 알아내었다. 특히 온도 측정센서의 정확도가 $0.1^{\circ}C$일 때 측정유체의 윗면과 아랫면의 온도차가 $18^{\circ}C$이상이면 준정상 상태법을 이용한 열전도도 측정장치의 불확실도가 ${\pm}1%$이내로 들어옴을 알 수 있었다. 따라서 온도 측정센서가 $0.1^{\circ}C$의 정확도를 가지며 측정유체의 윗면과 아랫면의 온도차가 $18^{\circ}C$이상이 되는 불확실도 ${\pm}1%$을 갖는 준정상 상태법을 이용한 나노유체의 열전도도 측정장치를 개발하였다. 개발된 실험장치의 검증을 위하여 DI-Water의 열전도도와 $Al_2O_3$ 나노유체의 열전도도를 각각 측정하여 기존 문헌 및 선행 연구자의 결과와 비교하여 보았고 개발된 장치가 ${\pm}1%$ 이내의 불확실도를 가지고 나노유체의 열전도도를 측정할 수 있음을 확인하였다.

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.19-22
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• 2016

본 연구는 박각시 나방 유연날개의 준정상 공력 모델링을 위한 공력측정실험을 진행하였다. 두 개의 서보모터로 이루어진 동역학적 로봇 모델은 3톤 수조 내부에서 날갯짓 운동을 구현하였고, 6축 센서가 날개 모델의 뿌리에 장착되어 공력 측정을 시행하였다. 날개 모델은 다른 두께의 폴리카보네이트 평판으로 제작되었고, 3mm 두께의 강체날개와 0.8mm 두께의 유연날개로 구성되었다. 공력측정은 각 날개 모델별 받음각을 -5도에서 95도까지 5도씩 변경하여 진행하였고, 이를 바탕으로 준정상 공력 모델링을 시도하였다. 날개 두께별 준정상 공력 모델링을 통해 특정 두께를 가진 유연날개는 강체날개보다 높은 공력효율을 가짐을 알 수 있었고, 날개 유연도 역시 준정상 가정을 기반으로 모델링 할 수 있을 것으로 기대된다.

• 한국방재학회:학술대회논문집
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• 2008.02a
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• pp.295-298
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• 2008

유체내에 잠겨있는 물체의 진동은 공기력을 유발시키며 이러한 공기력에 의해 발생되는 진동을 물체의 거동에 의해 발생되는 가진이라 한다. 또한 물체에 작용하는 외부 공기력이 없이도 물체의 주기적인 움직임에 의해 발생되는 에너지로부터 공기력을 생성시킨다. 이러한 메커니즘에 의해 생성되는 공기력을 공기자발력(self-excited force) 이라 하며 교량의 내풍안정성과 관련이 있다. 본 논문에서는 MIE 메커니즘에 의해 발생되는 플루터 현상을 수학적으로 살펴보고, 단일모드에 대한 플러터계수를 이용한 플러터 발생풍속 산정식을 유도하였다. 또한 준정상 이론을 적용하여 단일모드에 대한 플러터 발생 예측식을 간략화하였다. 제안된 식의 플러터 발생풍속을 구조물의 진동수비가 서로 다른 3개의 $\pi$형 단면에 대해 검토하였다.

• Journal of the Korea Institute of Information Security & Cryptology
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• v.32 no.4
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• pp.647-660
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• 2022

Recent works demonstrate that the semi-supervised anomaly detection method functions quite well in the environment with normal data and some anomalous data. However, abnormal data shortages can occur in an environment where it is difficult to reserve anomalous data, such as an unknown attack in the cyber security fields. In this paper, we propose ADA-PH(Abnormal Data Augmentation Method using Perturbation based on Hypersphere), a novel anomalous data augmentation method that is applicable in an environment where abnormal data is insufficient to secure the performance of the semi-supervised anomaly detection method. ADA-PH generates abnormal data by perturbing samples located relatively far from the center of the hypersphere. With the network intrusion detection datasets where abnormal data is rare, ADA-PH shows 23.63% higher AUC performance than anomaly detection without data augmentation and even performs better than the other augmentation methods. Also, we further conduct quantitative and qualitative analysis on whether generated abnormal data is anomalous.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2005.05a
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• pp.301-307
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• 2005

In this study, simplified whirl flutter analyses using quasisteady aerodynamic theory have been performed for a 2-DOF tilt-rotor system with both pitch and yaw motions of a rotor-nacelle. The present dynamic system consists of the rotor (propeller), forming the gyroscopic and aerodynamic element, supported horizontally by a pylon that is pivoted at some wing attachment point. Several design parameters (or rotor-nacelle system are considered and the effect of whirl flutter stability are also investigated for various design parameters.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.15 no.7 s.100
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• pp.843-850
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• 2005

In this study, simplified whirl flutter analyses using quasisteady aerodynamic theory have been Performed for a 2-DOF tiIt-rotor system with both pitch and Yaw motions of a rotor-nacelle. The present dynamic system consists of the rotor (propeller) , forming the gyroscopic and aerodynamic element, supported horizontally by a pylon that is pivoted at some wing attachment point. Several design parameters for rotor-nacelle system are considered to practically investigate the effects of whirl flutter stability.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.1
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• pp.1-9
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• 2017

In this paper, we present and verify an aerodynamic reduced-order model (ROM) based on a quasi-steady flow method to reduce the computational cost of supersonic aeroelastic analysis. For supersonic flows, especially when the characteristic time scale of the flow is small compared to that of the structural motion, the unsteadiness of flow can be negligible, and quasi-steady solutions can be used instead of the unsteady solutions for the aeroelastic analysis. Kriging method is used to build the ROM of the aerodynamics. The surface solutions from the ROM are used as the boundary conditions for the structural analysis at each time-step. The ROM is validated against the unsteady solutions.

• Membrane Journal
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• v.13 no.2
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• pp.88-100
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• 2003

A change of filtrate flux in Taylor vortex flow filtration was investigated experimentally by rotating speed of inner cellulose ester membrane cylinder (average pore size: 1.2 ${\mu}m$), slurry concentration, and particle size. The filtrate flux was a direct proportion relation with TMP, but an inverse relation with resistances. A change of cake resistance with time was examined by rotating speed, slurry concentration, and particle size. Initial resistance increased dramatically as raising slurry concentration, and the pseudo-steady state was maintained at high resistance value. However, times to reach the pseudo-steady state did not depend on slurry concentration. The resistance was larger as smaller particle size, because possibility of pore blocking inside membrane could be higher and shear effect should be lower as smaller particle size. A model equation suggested in this study was composed of particle deposition and removal terms, and could confirm well experimental data using average values of experimental coefficients.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.30 no.6
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• pp.495-500
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• 2017

In the boundary layer of supersonic or hypersonic vehicles, there is the conversion from kinetic energy to thermal energy, called aerodynamic heating. Aerodynamic heating has to be considered to design supersonic vehicles, because it induces severe heat flux to surface. Transient heat transfer analysis with CFD is used to predict thermal response of vehicles, however transient heat transfer analysis needs excessive computing powers. Loosely coupled method is widely used for evaluating thermal response, however it needs to be revised for overestimated heat flux. In this research, quasi-transient method, which is combined loosely coupled method and conjugate heat transfer analysis, is proposed for evaluating thermal response with efficiency and reliability. Defining reference time of splitting flight scenario for transient simulation is important on accuracy of quasi-transient method, however there is no algorithm to determine. Therefore the research suggests the algorithm with various flow conditions to define reference time. Supersonic flow field of blunt body with constant acceleration is calculated to evaluate quasi-transient method. Temperature difference between transient and quasi-transient method is about 11.4%, and calculation time reduces 28 times for using quasi-transient method.

• 건강소식
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• v.11 no.9 s.106
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• pp.38-40
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• 1987