• The Journal of the Acoustical Society of Korea
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• v.28 no.3
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• pp.208-212
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• 2009

Ground wave is an acoustic wave propagating at a sediment sound speed in the case that sediment sound speed is constant with depth, which is explained by modal dispersion effects. In this paper, the ground wave in time domain is simulated using the ray-based approach, which is possible because the modal dispersion can be explained by the guiding of energy caused by reflection and refraction in the waveguide geometry. For a Pekeris waveguide, the ground wave can be interpreted as a sequence of head waves, called a head wave sequence [Choi and Dahl, J. Acoust. Soc. Am. 119, 3660-3668 (2006)]. The ground wave is simulated by convolution of the source signal with a channel impulse response of the head wave sequence, which is compared with simulated signals obtained via a Fourier synthesis of a complex parabolic equation (PE) field.

• Proceedings of the Acoustical Society of Korea Conference
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• 1984.12a
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• pp.52-56
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• 1984

파동 이론에 의한 수중에서의 저주파 음파전달은 음향학적 경계 조건에 의해 결정되는 Normal Mode로 특징지어 진다. Normal Mode는 수층(Water Layer)뿐만 아니라 수직적으로 층상 구조인 해저 퇴적층(Subatrate)의 음향 특성을 포함하여 결정되는 파동 방정식의 해로서 이에 의해 수층 및 해저 퇴적층에서의 음압 분포와 감쇠를 계산할 수 있다. 본 논문은 저주파 음파 전달에 관한 Normal Mode 이론에 의하여 음원의 주파수와 해저 퇴적층에서의 음속 분포등에 따른 각 Mode의 음압 분포, 감쇠등에 관한 음향학적 해석으로 원거리까지 진행하는 수중 음파의 해저 퇴적층 투과 심도를 추출하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.05a
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• pp.41-47
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• 1996

데토네이션 현상은 화학반응면이 음속 이상으로 진행하는 경우로 연소와는 다른 분야로 취급된다. 국내에서는 발파나 무기에 응용되고 있지만 이 분야의 선진국에서는 산업의 여러 분야에 적용되며 이 분야에 많은 기초연구가 행해져 왔다. 본 연구는 이러한 데토네이션 현상을 콘크리이트나 금속의 절단이나 노화된 구조물의 해체에 응용하는 것에 관한 내용으로 고체폭약에 비해 위험하여 취급이 어려운 액체 폭약을 보다 안전하고 현상변화가 자유로운 액체의 잇점을 살려 절단에 있어 최대의 효율을 내는 형상을 단지 케이스의 가공만으로 가능하므로 경제적이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.4
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• pp.295-301
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• 2007

The aeroelastic characteristics of a wing with control surface freeplay are investigated. The transonic small disturbance equation is used for unsteady aerodynamic forces in subsonic/transonic region. The fictitious mass method is introduced to apply a modal approach to nonlinear structural models. Nonlinear aeroelastic time responses are calculated by the coupled time integration method. Using these methods, an efficient aeroelastic analysis is achieved for aerodynamic and structural nonlinearities simultaneously. The effects of the aerodynamic nonlinearity, initial flap amplitude, and freeplay magnitude in aeroelastic characteristics are investigated in this study.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.95-100
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• 2014

In hypersonic aircraft, increase of aerodynamic heat and engine heat leads heat loads in airframe. It could lead structural change of aircraft's component and malfunctioning. Endothermic fuels are liquid hydrocarbon fuels which are able to absorb the heat load by undergoing endothermic reactions. In this study, exo-tetrahydrodicyclopentadiene was selected as a model endothermic fuel and experiments on endothermic properties were investigated with pore structure controlled zeolite catalyst using metal deposition. We secured the catalyst that had better endothermic performance than commercial catalyst. The object of this study is inspect catalyst properties which have effect on heat absorption improvement. Synthetic catalyst could be applied to system that use exo-THDCP as endothermic fuel instead of other commercial catalyst.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.136-140
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• 2005

By extending one-dimensional ZND detonation structure analysis model, a simple model for two-dimensional oblique detonation wave structure analysis is presented by coupling Rankine-Hugoniot relation and chemical kinetics for oblique shock wave and oblique detonation wave. Base on this study, two-dimensional fluid dynamics analysis is carried out to investigate the detailed unsteady structure of oblique detonation waves involving triple point, transverse waves and cellular structures. CFD results provide a deeper insight into the detailed structure of oblique detonation waves, and the simple model could be used as a unified design tool for hypersonic propulsion systems employing oblique detonation wave as combustion mechanism.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.14 no.2
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• pp.17-26
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• 2006

The flutter characteristics of all movable tail wing with honeycomb sandwich structure have been studied in this study. The present wing model has a airfoil cross section and the linear variation of spanwise thickness. Structural vibration analysis is performed based on the finite element method using sandwich and beam elements. Unsteady aerodynamic technique used on the doublet lattice method has been effectively used to conduct the frequency-domain flutter analyses. The parametric flutter studies have been performed for various structural design parameters. Computational results on flutter stability due to the variation of structural parameters are presented and its related characteristics are investigated through the comparison of results.

• Proceedings of the Acoustical Society of Korea Conference
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• spring
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• pp.365-368
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• 2002

수중에서와 같이 전자기파의 사용이 곤란한 환경에서 정보의 전달 방법으로 초음파를 사용하는 것이 일반적이다. 그러나 기존의 방법은 음파의 전파 경로 상에 있어서 잡음, 온도, 음속 등의 환경에 많은 영향을 받기 때문에 정확한 정보의 전달이 곤란한 경우가 있다. 본 연구에서는 전기적 용량으로 특성을 제어할 수 있는 2층 구조 압전 트랜스듀서에 있어서 전기적 용량 변화에 따른 공진 모드간의 효율 비의 변화를 이용하여 전파 경로 상의 환경 변화에 독립적인 원격 물리 계측법을 제안하고 그 가능성을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.2
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• pp.127-134
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• 2020

High supersonic aircraft are exposed to high temperature environments by aerodynamic heating during supersonic flight. Thermal protection system structures such as double-panel structures are used on the skin of the fuselage and wings to prevent the transfer of high heat into the interior of an aircraft. The thin-walled double-panel skin can be exposed to acoustic loads by supersonic aircraft's high power engine noise and jet flow noise, which can cause sonic fatigue damage. Therefore, it is necessary to examine the behavior of supersonic aircraft skin structure under thermal-acoustic load and to predict fatigue life. In this paper, we designed and fabricated thermal-acoustic test equipment to simulate thermal-acoustic load. Thermal-acoustic testing of the titanium specimen under thermal-acoustic load was performed. The analytical model was verified by comparing the thermal-acoustic test results with the finite element analysis results.

• Journal of the Korean Society for Nondestructive Testing
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• v.36 no.6
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• pp.474-482
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• 2016

A Kelvin foam plate - widely used in the energy and transport industries as a lightweight structural material - was examined to estimate its Young's modulus using ultrasound. An isotropic tetrakaidecahedron foam structure was designed in SolidWorks and printed using 3D printer with an ABS plastic material. The 3D printed foam structure was used to build a foam plate with a 14 mm thickness ($50mm{\times}100mm$ in size) for the ultrasonic test. The Kelvin foam plate, a significantly porous medium, was completely filled with paraffin wax to enable the ultrasound to penetrate through the porous medium. The acoustic wave velocity of the wax-filled Kelvin foam was measured using the time of flight (TOF) method. Furthermore, the elastic modulus of the Kelvin foam was estimated based on an elastic structural model developed in this study. The Young's modulus of the produced Kelvin foam was observed to be approximately 3.4% of the bulk value of the constituent material (ABS plastic). This finding is consistent with experimental and theoretical results reported by previous studies.