• 복식
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• 제21권
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• pp.193-206
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• 1993

Recently in the post-modernism era ethnic look tropical look or ecological look has prevailed as an important theme of fashion all over the world. The main core of these themes is based on primitivism. The purpose of this study was first to com-prehend the internal meaning and the exteral form of primitivism in modern fashion second to compare the characteristics of primitivism in art with those in modern fashion as one of the phenomena in cultural consistency. For this purpose documentary studies about primitivism in social science and art were preceded as a framework of this study and then objective studies about primitivism in modern fashion and art were analyzed. Primi-tivism expressed in clothing since the 16th century was also historically traced. the results were as follows: 1. Primitivism in modern fashion was summarized by emotionality play ecology and aboriginality as well as was represented by ex-ternal forms of open form part-to-whole re-lation planar intergration rounded form and indeterminate form It was demonstrated that the external form of primitivism in art and fashion is quite similar and is an example of cultural consistency. So it is reaffirmed that fashion is the production of culture representing zeitgeist as a genre of art. 2, Modernism in the early 20th century brought the richness of materials through the de-velopment of the mechanical culture emphasizing rationality as well as functionalism, Fashion also has been influenced by this modern-ism so it has tended to express only the beauty which emphasizes the functional aspects of clothing and excludes the decorative characters. The primitivism in recent fashion is against the flow of modernism. In a word the pursuit for the regression to nature and the recovering of hu-manity is the core of the primitivism in modern fashion.

• 한국가시화정보학회:학술대회논문집
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• 한국가시화정보학회 2003년도 추계학술대회 논문집
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• pp.39-42
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• 2003

Leading edge extension(LEX) in a highly swept shape applied to a delta wing features the modern air-fighters. The LEX vortices generated upon the upper surface of the wing at high angle of attack enhance the lift force of the delta wing by way of increased negative suction pressure over the surfaces. The present 3-D stereo PIV includes the Identification of 2-D cross-correlation equation, stereo matching of 2-D velocity vectors of two cameras, accurate calculation of 3-D velocity vectors by homogeneous coordinate system, removal of error vectors by a statistical method followed by a continuity equation criterion and so on. A delta wing model with or without LEX was immersed in a circulating water channel. Two high-resolution, high-speed digital cameras$(1280pixel\times1024pixel)$ were used to allow the time-resolved animation work. The present dynamic stereo PIV represents the complicated vortex behavior, especially, in terms of time-dependent characteristics of the vortices at given measuring sections. Quantities such as three velocity vector components, vorticity and other flow information can be easily visualized via the 3D time-resolved post-processing to make the easy understanding of the LEX effect or vortex emerging and collapse which are important phenomena occurring in the field of delta wing aerodynamics.

• Journal of Advanced Marine Engineering and Technology
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• 제34권4호
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• pp.485-490
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• 2010

MILD(Moderate and Intense Low Oxygen Dilution)연소는 연소가스의 재순환을 이용하여 화염대의 고온 형성을 최대한 억제하여 질소산화물을 생성 과정에서 저감하는 동시에 연소로의 내부온도를 균일화하여 열 이용 효율을 향상시킬 수 있는 기술이다. 본 연구에서는 MILD 연소로에서 연료 및 공기 유량으로 당량비를 조절하고, 그 변화에 따른 연소로에서 발생되는 배기가스 및 연소로 내부의 온도 계측을 통하여 MILD 연소기의 특성과 MILD 연소 시 최적 조건을 도출하고자 하였다. 본 연구를 통하여 당량비가 0.71~0.73일 때 MILD 연소가 구현되었으며 MILD 연소 조건에서 온도 균일도와 NOx 및 CO 생성 특성을 평가하였다.

• Advances in aircraft and spacecraft science
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• 제2권2호
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• pp.125-168
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• 2015

Dynamic aeroelastic behavior of structurally nonlinear Joined Wings is presented. Three configurations, two characterized by a different location of the joint and one presenting a direct connection between the two wings (SensorCraft-like layout) are investigated. The snap-divergence is studied from a dynamic perspective in order to assess the real response of the configuration. The investigations also focus on the flutter occurrence (critical state) and postcritical phenomena. Limit Cycle Oscillations (LCOs) are observed, possibly followed by a loss of periodicity of the solution as speed is further increased. In some cases, it is also possible to ascertain the presence of period doubling (flip-) bifurcations. Differences between flutter (Hopf's bifurcation) speed evaluated with linear and nonlinear analyses are discussed in depth in order to understand if a linear (and thus computationally less intense) representation provides an acceptable estimate of the instability properties. Both frequency- and time-domain approaches are compared. Moreover, aerodynamic solvers based on the potential flow are critically examined. In particular, it is assessed in what measure more sophisticated aerodynamic and interface models impact the aeroelastic predictions. When the use of the tools gives different results, a physical interpretation of the leading mechanism generating the mismatch is provided. In particular, for PrandtlPlane-like configurations the aeroelastic response is very sensitive to the wake's shape. As a consequence, it is suggested that a more sophisticate modeling of the wake positively impacts the reliability of aerodynamic and aeroelastic analysis. For SensorCraft-like configurations some LCOs are characterized by a non-synchronous motion of the inner and outer portion of the lower wing: the wing's tip exhibits a small oscillation during the descending or ascending phase, whereas the mid-span station describes a sinusoidal-like trajectory in the time-domain.

• Geomechanics and Engineering
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• 제15권3호
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• pp.851-859
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• 2018

There are two primary causes of the ground movement due to tunnelling in urban areas; firstly the lost ground and secondly the groundwater depression during construction. The groundwater depression was usually not considered as a cause of settlement in previous research works. The main purpose of this study is to analyze the combined effect of these two phenomena on the transverse settlement trough. Centrifuge model tests and numerical analysis were primarily selected as the methodology. The characteristics of settlement trough were analyzed by performing centrifuge model tests where acceleration reached up to 80g condition. Two different types of tunnel models of 180 mm diameter were prepared in order to match the prototype of a large tunnel of 14.4 m diameter. A volume loss model was made to simulate the excavation procedure at different volume loss and a drainage tunnel model was made to simulate the reduction in pore pressure distribution. Numerical analysis was performed using FLAC 2D program in order to analyze the effects of various groundwater depression values on the settlement trough. Unconfined fluid flow condition was selected to develop the phreatic surface and groundwater level on the surface. The settlement troughs obtained in the results were investigated according to the combined effect of excavation and groundwater depression. Subsequently, a new curve is suggested to consider elastic settlement in the modified Gaussian curve. The results show that the effects of groundwater depression are considerable as the settlement trough gets deeper and wider compared to the trough obtained only due to excavation. The relationships of maximum settlement and infection point with the reduced pore pressure at tunnel centerline are also suggested.

• 한국소음진동공학회논문집
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• 제24권3호
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• pp.180-188
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• 2014

현대자동차그룹은 HSM이라고 불리는 간략화된 차량 모델에 대하여 썬루프 버페팅 현상의 실험적인 조사를 시행하였다. 현대자동차그룹은 어떤 CFD솔버가 충분한 정확도를 가지고 썬루프 버페팅 현상을 예측하는지 조사하기 위해 상용CFD공급업체의 참여를 요청하였다. ANSYS Korea는 이번 조사에 참여하여 ANSYS fluent를 이용하여 HSM의 썬루프 버페팅에 대한 수치해석을 수행하였다. 먼저 유동장 검증을 위해 풍속 60 km/h에 대하여 썬루프가 닫힌 HSM모델에 대하여 해석을 수행하였다. HSM상부 면의 세 지점에서 속도 분포를 예측하였고, 이는 시험결과와 비교되었다. 그런 다음 고해상도 난류 모델인 DES를 이용한 해석이 전 풍속영역에 걸쳐 수행되었다. 버페팅 주파수와 버페팅 음압레벨이 예측되었고, 이는 시험결과와 비교되었다. 이를 통해 실제 차량 개발을 위한 CFD의 예측 가능성에 대하여 결론을 얻을 수 있었다.

• 한국화재소방학회논문지
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• 제26권2호
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• pp.53-58
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• 2012

본 연구에서는 가연성 물질을 고려한 워터커튼 시스템(Water Curtain System)의 열 및 연기유동 제어 특성을 실험적으로 분석하였다. 이를 위해서 Room Corner Tester(RCT)를 사용하여 연료의 종류가 소나무(PineWood)와 가솔린(Gasoline)인 경우 각각의 발열량(Heat Release Rate)을 구하였으며, 워터커튼용 화재실험 장치를 제작하여 화원근방에서 5m 떨어진 지점의 천장 부근에 분사각도 $180^{\circ}$, 오리피스 직경 8.2 mm의 노즐(Nozzle)을 설치한 후 목재와 가솔린 각각에 대해서 화재실험을 실시하여 워터커튼 전후의 온도분포와 가시도를 측정하였다. 그결과 워터커튼 시스템의열및연기유동 제어는 가연성 물질의 연소특성에 따른 고온의 연기발생량과 분사 노즐에 의한 유동현상이 중요한 상관관계를 갖고 있음을 확인하였다.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 1992년도 추계학술대회 논문집
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• pp.136-140
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• 1992

The purpose of this research is to develop the lithium secondary battery. This paper describes the preparation, electrochemical properties of nontstoichiometric(NS)-$V_6O_{13}$ and characteristics of Li/$V_6O_{13}$ secondary battery. NS-$V_6O_{13}$ was prepared by thermal decomposition of $NH_4VO_3$ under Ar stream of 140ml/min~180ml/min flow rate. And then, this NS-$V_6O_{13}$ was used for cathode active material. Cathode sheet was prepared by compressing the composite of NS-$V_6O_{13}$, acetylene black(A.B) and teflon emulsion (T.E). Characteristics of the test cell are summarised as follows. Oxidation capacity of NS-$V_6O_{13}$ was about 20% less than its reduction capacity. A part of NS-$V_6O_{13}$ cathode active material showed irreversible reaction in early charge-discharge cycle. This phenomena seems to be caused by irreversible incoporation/discoporation of lithium cation to/from NS-$V_6O_{13}$ host. Discharge characteristics curve of Li/$V_6O_{13}$ cell showed 4 potential plateaus. Charge-discharge capacity was declined in the beginning of cycling and slowly increased in company with increasing of coulombic efficiency. Energy density per weight of $V_6O_{13}$ cathode material was as high as 522Wh/kg~765Wh/kg.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1996년도 하계학술대회 논문집 C
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• pp.2004-2006
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• 1996

A thermally driven polysilicon micro actuator has been fabricated using surface micromachining techniques. It consists of P-doped polysilicon as a structural layer and TEOS (tetracthylorthosilicate) as a sacrificial layer. The polysilicon was annealed for the relaxation of residual stress which is the main cause to its deformation such as bending and buckling. And the newly developed HF VPE (vapor phase etching) process was also used as an effective release method for the elimination of sacrificial TEOS layer. The thickneas of polysilicon is $2{\mu}m$ and the lengths of active and passive polysilicon cantilevers are $500{\mu}m$ and $260{\mu}m$, respectively. The actuation is incurred by die thermal expansion due to the current flow in the active polysilicon cantilever, which motion is amplified by lever mechanism. The moving distance of polysilicon micro actuator was experimentally conformed as large as $21{\mu}m$ at the input voltage level of 10V and 50Hz square wave. The actuating characteristics are investigated by simulating the phenomena of heat transfer and thermal expansion in the polysilicon layer. The displacement of actuator is analyzed to be proportional to the square of input voltage. These micro actuator technology can be utilized for the fabrication of MEMS (microelectromechanical system) such as micro relay, which requires large displacement or contact force but relatively slow response.

• 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.