• Bulletin of Korea Environmental Preservation Association
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• s.414
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• pp.39-39
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• 2014

• Journal of Astronomy and Space Sciences
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• v.9 no.2
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• pp.203-212
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• 1992

Geomagnetic data from 3-axis magnetometer and the IGRF model (tilite - eccentric dipole model) were used to determine the attitude of a satellite. We compared the values of the geomagnetic model with the magnetometer data and two attitude angles, called $\alpha$ -angle and $\beta$-angle respectively, were calculated. From these angles we calculated simple bounds, $\gamma1$ and $\gamma2$, on the true attitude angle $\gamma$, which is used to detemine attitude, between the z-axis and the local vertical. And then we investigated conditions of attitudes of UoSAT-11, 14, 22.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.2
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• pp.17-24
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• 2003

This paper presents results from steady wind tunnel test conducted on a $65^{\circ}$ delta wing at a root chord Reynolds number of $1.76{\times}10^6$. In these experiments, the wing was instrumented with 188 pressure taps, conjunction with powerful multi-channel data logging system, allowed the wing upper surface pressure distribution to be measured. Analysis indicates that the wing upper surface distribution can provide considerable insight into the comvined aerodynamic effects of angle of attack and sideslip on the wing. In a sideslip condition, the strength of the vortex on the windward side is much stronger than that of leeward side. This asymmetric pressure disstribution betwwen each side of wings result in a negative value of rolling moment. However, at a certatin range of angle of attck and sideslip angle(${\alpha}$=$24^{\circ}{\sim}36^{\circ}C$, ${\beta}$=$-5^{\circ}{\sim}-15^{\circ}C$) abrupt change of sign of rolling monent, rolling monent reversal, was observed.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2010.10a
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• pp.48-49
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• 2010

선박의 러더하부 끝단에서는 선회에 따른 와류로 인하여 선회력 및 후류유동에 변화를 초래한다. 이를 관측하기 위해 NACA단면 형상의 몰수체를 영각과 관측단면을 변화시키며 $Re=2.0{\times}10^4$에서 실험을 통한 순간유동장을 계측 후 그 영향을 조사하였다. 계측된 결과는 상호상관 PIV기법을 이용 Naca단면 끝단에서의 2차원 유동특성을 알아보기 위하여 상호 비교하였다. NACA단면은 영각변화에 따라 후류유동에 영향을 미친다. 동일유입유속에서 영각이 증가함에 따라 관찰단면이 중앙으로 갈수록 와류 규모가 확대되는 것을 관찰할 수 있었다.

• Information Display
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• v.5 no.5
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• pp.4-9
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• 2004

최근 비오이 하이디스에서는 무제한의 광시야각과 시야각에 따른 색변화가 최소화된 선명한 색 특성을 갖는 Advanced FFS(Fringe Field Switching) 기술을 개발하였다. 이 기술은 resin 기술적용(평탄화에 의한 고개구율)없이 종래의 FFS 기술에서 액정의 전기 광특성을 최적화하는 새로운 디자인 룰을 찾아내어 실현하였다. 진보된 화소 개념은 전극의 모서리 구조, 전극 간격/폭, 칼라 필터의 블랙 마트릭스(BM)와 전극 간격등의 key parameters들의 최적화에 의해 달성되었고 액정 셀 내의 모서리와 전기장등이 액정을 미세하게 조정할 수 있도록 있게 된 것이다. 이러한 진보된 설계 개념은 모든 FFS 제품에 반영되어 개발되었다. 뿐만 아니라 12.1" XGA 제품에서 투과율이 22% 증가하고 흑백 대비비(Contrast Ratio)는 33% 증가한 600 : 1의 세계 최고 사양을 갖는 제품을 개발하게 되었다. 특히 태블릿과 노트북용 TFT- LCD 모듈에서 단일 도메인(Single Domain) 모드로도 White상태에서 시야각에 따른 색변화가 0.02 이하의 특성을 갖고 180도/180도의 무제한 시야각을 갖고 있다. Advanced FFS 기술의 브랜드 이름과 슬로건으로 'Viewiz'와 'Vision Magic'을 정하여 마케팅 중이며 세계적인 Top Tier 고객에 제품을 판매 중이고, 2004년 3분기에는 태블릿 시장에서 점유율 70%로 1위를 차지하였다.

• Journal of Advanced Navigation Technology
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• v.9 no.1
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• pp.28-33
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• 2005

In this paper, we developed the algorithm to control longitudinal and lateral motion of UAV(Unmanned Aerial Vehicle) with Infrared heat sensors and GPS(Global Positioning System) receiver. UAV was controlled to be flown horizontally and also turned coordinately maintaining the constant altitude. Accomplishing the flight test of UAV sevral times, we were able to develope low price controller to control bank angle for lateral motion, and also pitch angle and altitude for longitudinal motion simultaneously.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.10-17
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• 2003

Dynamic stability is critically required to stabilize an airship which is statically unstable. Numerical computations were performed in order to support and confirm the foced oscillation wind tunnel tests. To analyze the low-speed flow filed around the airship, a low-Mach number preconditioned method was applied. Using two computation methods, variations of the dynamic damping coefficients were examined. Numerical results show that it is dynamically stable for three directional moments, but unstable for normal or side force. It is revealed that the damping coefficients are more sensitive to the direction of the angular rate than the angle of attack or the magnitude og angular rate.

• Solar Energy
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• v.16 no.2
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• pp.79-86
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• 1996

In order to reduce damages due to cavitation effects and to improve performance of fluid machinery, supercavitation around the cascade and the hydraulic characteristics of supercavitating cascade must be analyzed accurately. And the study on the effects of cavitation on fluid machinery and analysis on the performances of supercavitating hydrofoil through various elements governing flow field are critically important. In this study comparison of experiment results with the computed results of linear theory using singularity method was obtainable. Specially singularity points like sources and vortexes on hydrofoil and freestreamline were distributed to analyze two dimensional flow field of supercavitating cascade, and governing equations of flow field were derived and hydraulic characteristics of cascade were calculated by numerical analysis of the governing equations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.2
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• pp.121-130
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• 2009

An unsteady numerical simulation method for an autorotating rotor in forward flight was developed. The flapping and rotational equations of motion of autorotation are continuously integrated for given time steps, meanwhile the induced velocity field at disc plane is obtained by the dynamic inflow theory embodying the unteadiness. The transitions from arbitrary initial states to equilibrium states were simulated. Steady autorotations as numerical solutions of equations were predicted by using two sources of blade airfoil data. The simulations using airfoil data which were obtained by a two dimensional Navier-Stokes solver in terms of angles of attack and Reynolds numbers have shown good agreements with wind tunnel experimental results.

• The Journal of Engineering Geology
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• v.29 no.4
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• pp.565-578
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• 2019

Basic friction angles of Hwangdeung granite, Berea sandstone, Jeongsun marble, Hongcheon gneiss, Pungam shale and Eumseong sandy shale were measured by direct shear test, tilt test and pull test. Characteristics of basic friction angle and the accuracy of test methods were compared and the optimal method in measuring basic friction angle was suggested. Although basic friction angles might be measured accurately by direct shear test, the test apparatus is expensive and procedures are complicated. Tilt tests which is the suggested method for measuring basic friction angle by International Association for Rock Mechanics also provided similar basic friction angles measured by direct shear test. However, the error measured for the same rock type is higher than 7° and values by repeated measurements in one sample show different trends, such as increasing or decreasing or almost constant as measurements continued. The difference measured in one gneiss sample is higher 12°, indicating that tilt test may be not a reliable method for measuring basic friction angle. Not only pull test provided accurate and consistent results under low normal stresses, but also test apparatus is simple and inexpensive and procedure is not complicated, indicating that pull test may be the optimal method for measuring basic friction angle.