• 한국학교수학회논문집
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• 제13권4호
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• pp.595-618
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• 2010

미래 지식기반 사회에 필요한 합리적이고, 창의적인 인재를 육성하기 위하여 학생들은 상상력과 창의력이 필요하고, 교사들이 이를 실용적으로 지도할 수 있는 분야가 수리과학이다. 학생들에게는 새로운 현상에 대한 호기심과 집중력, 문제해결을 통한 연구와 독창성을 기르는 활동이 필요한데, 4D-프레임을 이용하여 공간도형을 활용한 갖가지 모형 만들기를 통해 상상력과 창의력을 향상시키고자 하였다. 이러한 활동은 학생들의 수학에 대한 정의적 측면의 긍정적 효과뿐만 아니라 건축 및 우주 과학자의 소양을 담은 담화를 생성할 수 있었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.713-721
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• 2004

Variable air intake and variable exhaust nozzle of hypersonic engines are designed and tested in this study. Dimensions for variable geometry air intake, ram combustor and variable geometry exhaust nozzle are defined based on the requirements of a pre-cooled turbojet engine. Hypersonic Ramjet Engine is designed as a scaled test bed for each component. Actuation forces of moving parts for variable intake and variable nozzle are reduced by balancing the other force in the opposite direction. A demonstrator engine which includes variable intake and variable nozzle is designed and the components are fabricated. Composite material with silicone carbide is applied for high temperature parts under oxidation environment such as leading edge of the variable intake and combustor liner. Internal cooling structure is adopted for both moving and static parts of the variable nozzle. Pressure recovery and mass capture ratio of the variable intake at Mach 5 is obtained by a hypersonic wind tunnel test. Flow characteristics of the variable nozzle are obtained by a low temperature flow test. Wall temperature and heat flux of the nozzle at Mach 3 is obtained by a firing test. As results, the intake and the nozzle are proved to be used at designed pressure and temperature environment.

• Architectural research
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• 제4권1호
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• pp.1-6
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• 2002

Every year new tall buildings are being conceived, designed, and built with new schemes. Thus it is important to explore the factors that affect tall building design. Thus it is important to explore the tall building design factors. The planning and design of tall buildings require different criteria than those that exist in regular size buildings. Tall buildings are uniquely expressed by their structural systems where exterior esthetic and requirements of space drive the form and composition of the structural systems. Therefore the exploration of design factors is the key to achieve optimum building systems. Optimization as mentioned here is associated with the efficiency of the different building systems. To achieve an optimal system, there is a need for an understanding of the factors that affect on overall tall building design such as planning module, building function, lease span, floor-to-floor-height, building height (aspect ratio), structural system, environmental systems. In this paper a statistical approach will be used and will be based on data collected from the practice through a rigorous survey taken. This information is tabulated and analyzed. The major target of investigation will be lease span related to space requirement in the tall building planning. Factors related to lease spans, such as function, floor-to-floor height, planning module, building height, overall plan dimension, and plan ratio (building geometry), will be looked at carefully. IN conclusion, this approach of optimization can introduce a preliminary design guideline for tall building projects. The purpose of the paper should shed some light on the optimum tall building design criteria.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.109-114
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• 2008

This paper presents the development status of a subscale precooled turbojet engine "S-engine" for the hypersonic cruiser and space place. S-engine employs the precooled-cycle using liquid hydrogen as fuel and coolant. It has $23cm{\times}23cm$ of rectangular cross section, 2.6 m of the overall length and about 100 kg of the target weight employing composite materials for a variable-geometry rectangular air-intake and nozzle. The design thrust and specific impulse at sea-level-static(SLS) are 1.2 kN and 2,000 sec respectively. After the system design and component tests, a prototype engine made of metal was manufactured and provided for the system firing test using gaseous hydrogen in March 2007. The core engine performance could be verified in this test. The second firing test using liquid hydrogen was conducted in October 2007. The engine, fuel supplying system and control system for the next flight test were used in this test. We verified the engine start-up sequence, compressor-turbine matching and performance of system and components. A flight test of S-engine is to be conducted by the Balloon-based Operation Vehicle(BOV) at Taiki town in Hokkaido in October 2008. The vehicle is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high-altitude observation balloon. After 40 second free-fall, the vehicle pulls up and S-engine operates for 60 seconds up to Mach 2. High altitude tests of the engine components corresponding to the BOV flight condition are also conducted.

• 한국터널지하공간학회 논문집
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• 제4권4호
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• pp.301-317
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• 2002

최근 지반물리탐사기술은 자원조사분야에서뿐 만 아니라 토목공학분야에서도 활용빈도가 증대되고 있는 실정이다. 이러한 기술을 토목기술자들이 활용하는 경우 물리탐사기법의 기본원리와 기술적 한계를 이해하는 것은 매우 중요하다. 본 논문에서는 타원체의 성질을 이용한 3차원 구조보정기법을 이용해 터널내 탄성파탐사(TSP)로부터 터널막장 전방에 위치한 파쇄대의 기하형상 즉, 터널축과 파쇄대간의 사이각 및 경사 등을 파악하는 기법에 관하여 기술하였다. 또한, TSP 시험을 모사하는 수치해석을 최적으로 수행하기 위하여 매개변수분석을 수행하였다. 즉, 수치해석의 안정성과 정확성을 도모하는 최적의 요소크기, 해석시간간격 및 발파진원의 동적특성 등에 대하여 연구하였다. 터널과 파쇄대를 포함한 임의의 지반을 모델화하여 수행한 예제해석으로부터 터널막장 전방에 위치한 파쇄대의 3차원적 기하형상을 타원체의 성질을 이용한 3차원구조보정기법에 의하여 적절한 예측할 수 있음을 확인하였다.

• 지구물리와물리탐사
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• 제16권1호
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• pp.59-62
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• 2013

우리는 구면일부지역에서의 퍼텐셜마당에 대하여 구면의 곡률을 고려하는 새로운 상향연속방법을 이전에 보고하였다. 그런데, 이 방법은 실제로 $r_2/r_1$의 비율(즉, 목표면의 반경 $r_2$ 대 자료면의 반경 $r_1$) 만을 달리함으로써 하향연속에도 그대로 사용될 수 있다. 한편, 이 방법에 내재된 구면의 기하학적 성질에 기인하는 문제와 그에 대한 대책을 기술하였다.

• International Journal of Quality Innovation
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• 제7권1호
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• pp.98-111
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• 2006

The paper presents the design of an optical profilometer, a device used for the reconstruction of the micro-geometry of mechanical parts in applications where high precision is needed. The design is based on Robust Design, a major' methodology for quality improvement of engineering systems. Several design solutions, namely different hardware and software setups of the device, are compared in order to select a configuration realising a desired trade-off between performance and cost. The peculiarity of the design strategy is the use of a computer model of the measurement process where the physical part of the process is simulated. This allows for an extensive exploration of the design space, thus opening the way to product innovation.

• 천문학논총
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• 제32권1호
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• pp.175-177
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• 2017

In order to reveal physical conditions of molecular gas in active galaxies (active galaxies mean both starbursts and AGNs in this paper), we carried out systematic observations (R = 19 ~ 120) of CO fundamental band at $4.7{\mu}m$ in absorption with AKARI. We also made follow-up CO absorption observations at higher spectral resolution (R = 5000 ~ 1000) with Subaru. Recently, Herschel made extensive observations of highly-excited CO lines in emission in the far-infrared. The two data sets (absorption and emission) sometimes provide us with apparently inconsistent results. One case is starburst galaxies: Subaru observations showed low temperature of molecular gas toward the starburst NGC 253, while Herschel detected highly excited CO lines in the starburst. This suggests that warm molecular clouds are more deeply embedded than newly formed star clusters. The other case is obscured AGNs; Herschel detected highly excited CO lines in emission in nearby AGNs, while AKARI and Subaru observations showed CO absorption only in some of the obscured AGNs. This could reflect the difference of nature of molecular tori in these AGNs. We propose the combination of the absorption and emission observations as an effective tool to reveal geometry of warm molecular clouds in active galaxies.

• 한국지반공학회:학술대회논문집
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• 한국지반공학회 2001년도 봄 학술발표회 논문집
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• pp.501-508
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• 2001

A graph or topographic map can often convey larger amounts of information in a shorter time than ordinary text-based methods. To visualize information precisely it is necessary to collect all the geological information at design stage, but actually it is almost impossible to bore or explore the entire area to gather the required data. So, tunnel engineers have to rely on the judgement of expert from the limited number of the results of exploration and experiment. In this study, several programs are developed to handle the results of geological investigation with various data processing techniques. The results of the typical case study are also presented. For the electric survey, eleven points are chosen at the valley to measure the resistivity using Schlumberger array. The measured data are interpolated in 3-dimensional space by kriging and the distribution of resistivity are visualized to find weak or fractured zone. The correlation length appears to be around 5 to 20 meter in depth. Regression analyses were performed to find a correlation length. No nugget effect is assumed, and the topographic map, geologic formation, fault zone, joint geometry and the distribution of resistivity are successfully visualized by using the proposed technique.

• Advances in aircraft and spacecraft science
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• 제5권5호
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• pp.581-594
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• 2018

This paper is the follow-on of a previous paper by the author where it was pointed out that the forthcoming, manned exploration missions to Mars, by means of complex geometry spacecraft, involve the study of phenomena like shock wave-boundary layer interaction and shock wave-shock wave interaction also along the entry path in Mars atmosphere. The present paper focuses the chemical effects both in the shock layer and on the surface of a test body along the Mars orbital entry and compares these effects with those along the Earth orbital re-entry. As well known, the Mars atmosphere is almost made up of Carbon dioxide whose dissociation energy is even lower than that of Oxygen. Therefore, although the Mars entry is less energized than the Earth re-entry, one can expect that the effects of chemistry on aerodynamic quantities, both in the shock layer and on a test body surface, are different from those along the Earth re-entry. The study has been carried out computationally by means of a direct simulation Monte Carlo code, simulating the nose of an aero-space-plane and using, as free stream parameters, those along the Mars entry and Earth re-entry trajectories in the altitude interval 60-90 km. At each altitude, three chemical conditions have been considered: 1) gas non reactive and non-catalytic surface, 2) gas reactive and non-catalytic surface, 3) gas reactive and fully-catalytic surface. The results showed that the number of reactions, both in the flow and on the nose surface, is higher for Earth and, correspondingly, also the effects on the aerodynamic quantities.