• 한국의상디자인학회지
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• 제15권2호
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• pp.15-26
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• 2013

The purpose of this study is to offer basic data for designing and making of brassiere with the consideration of the physiological nature of man. Each of 3/4-cup wired upward-support-type Mold Bra of 75 size with basic pad made at three representative domestic companies (A, B and C Company) was selected for analysis of pattern and components. The following is the result of this study. 1. That Company A's bra had the highest cup, relatively narrow width, the widest front-center and the highest front center at front pad. That of Company B had relatively short wing over the base and much difference at the height of cup depending on the presence of wire. That of Company C had low and wide cup, the widest bust span and the front center width, the front center height of front pad, the base length of front pad and the length of wings were observed to be of the figures between those of Company A and B. 2. The Bra of Company A had the biggest front center angle of $6^{\circ}$, while that of Company C had the biggest wing angle of $18^{\circ}$. The Bra of Company B showed the biggest difference of patterns depending on the presence of wire. Those of Company A and C showed very similar shape when wire was inserted. 3. The order of making brassiere is following: making of exterior mold cup${\rightarrow}$ sewing exterior cup and circumference of mold${\rightarrow}$ sewing base and wings${\rightarrow}$ sewing binding tape to base${\rightarrow}$ sewing cup and main pad${\rightarrow}$ sewing binding tape to upper sides and upper part of wings${\rightarrow}$ sewing wire-tape to interior base of cup${\rightarrow}$ inserting of wire inside wire-tape${\rightarrow}$ sewing hook & eye on the back of wings${\rightarrow}$ sewing shoulder string.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.217-220
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• 2006

The lift and drag forces produced by a wing of a given cross-sectional profile are dependent on the wing planform and the angle of attack. Aspect ratio is the ratio of the wing span to the average chord. For conventional fixed wing aircrafts, high aspect ratio wings produce a higher lift to drag ratio than low ones for flight at subsonic speeds. Therefore, high aspect ratio wings are used on aircraft intended for long endurance. However, birds and insects flap their wings to fly in the air and they can change their wing motions. Their wing motions are made up of translation and rotation. Therefore, we tested flapping motions with parameters which affect rotational motion such as the angle of attack and the wing beat frequency. The half elliptic shaped wings were designed with the variation of aspect ratio from 4 to 11. The flapping device was operated in the water to reduce the wing beat frequency according to Reynolds similarity. In this study, the aerodynamic forces, the time-averaged force coefficients and the lift to drag ratio were measured at Reynolds number 15,000 to explore the aerodynamic characteristics with the variation of aspect ratio. The maximum lift coefficient was turned up at AR=8. The mean drag coefficients were almost same values at angle of attack from $10^{\circ}$ to $40^{\circ}$ regardless of aspect ratio, and the mean drag coefficients above angle of attack $50^{\circ}$ were decreased according to the increase of aspect ratio. For flapping motion the maximum mean lift to drag ratio appeared at AR=8.

• 한국항공우주학회지
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• 제35권5호
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• pp.381-389
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• 2007

외부장착물의 효율적인 분리해석을 위해 6-DOF 시뮬레이션 프로그램을 개발하였다. 이 S/W는 장착물에 작용하는 공기력을 미리 작성된 공력 데이터베이스를 이용하여 간단한 보간으로 얻기에 전산유체역학에 기초한 방법에 비해 매우 빠른 계산시간을 가지며, 고정된 형상의 무장 뿐 아니라 분리 중 날개를 전개하는 무장에 대해서도 해석이 가능하다. 본 논문에서는 날개전개 무장의 공력 데이터베이스를 MSAP(Multi-body Separation Analysis Program)을 이용하여 작성하고, 비정상 감쇠계수를 Missile Datcom을 이용하여 예측하였다. 이 데이터베이스와 6-DOF 시뮬레이션 프로그램으로 무장의 고정된 날개 뿐 아니라, 날개전개에 따른 무장의 분리 안전성을 판단하였다

• 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.

• 한국소음진동공학회논문집
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• 제22권5호
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• pp.480-488
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• 2012

The aircrafts with high aspect ratio wings made by a composite material have been developed, which enable high energy efficiency and long-term flight by reducing air resistance and structural weight. However, they have difficulties in securing the aeroelastic stability such as the flutter because of their long and flexible wings. The flutter is unstable self-excited-vibration caused by interaction between the structural dynamics and the aerodynamics. It should be verified analytically prior to first flight test that the flutter does not happen in the range of flight mission. Normally, the finite element model is used for the flutter analysis. So it is important to construct the finite element model representing dynamic characteristics similar to those of a real aircraft. Accordingly, in this research, to acquire dynamic characteristics experimentally the modal test of the aircraft with high aspect ratio composite wings was conducted. And then the modal parameters from the finite element analysis(FEA) were compared with those from the modal test. To make analysis results closer to test results, the finite element model was updated by means of the sensitivity analysis on variables and the optimization. Finally, it was proved that the updated finite element model is reliable as compared with the results of the modal test.

• 한국항공우주학회지
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• 제34권7호
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• pp.12-17
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• 2006

채널 및 레일과 같은 비평면 지면 위를 비행하는 날개들의 정상상태 공력특성 및 종방향 정안정성을 경계요소법을 사용하여 연구하였다. 펜스의 높이가 날개의 위치보다 높을 경우, 펜스와 날개와의 거리가 작아질수록 양력이 증가하고 피칭다운 모멘트가 커졌다. 레일의 폭이 날개 스팬보다 넓을 때, 레일의 높이가 낮을수록 양력이 증가하고 유도항력이 감소하였다. 종방향 정안정성 측면에서 단일 날개의 경우 비평면 지면보다 평지에서 안정한 결과를 나타내었다. 종렬배치형 날개의 경우 채널내를 비행하는 날개가 평지보다 비평면 지면에서 안정적이었다. 본 연구결과는 초고속운송체의 설계에 적용될 수 있을 것으로 기대한다.

• 한국동물학회지
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• 제14권2호
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• pp.75-84
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• 1971

Genetic analysis of a new wing mutant, Surf wings (Srf), was performed. Mutant flies were extracted from a wild population of Drosophila melanogaster at the vicinity of Atomic Energy Research Institute, Seoul in August-September 1969. 1. The distal half of wings of heterozygotes (Srf/+) turned upwards about 40 degree from body axis, but flying ability was not disturbed. They overlap Cy in low frequency when they are grown below $22^{\circ}C$. This resembles with Si or j series, but wing margins are not rolled and diversed. Postscutellars are erected slightly, but they, in general, are not crossed. Any other external pleiotropic effects were not observed. 2. Penetrance and expressivity of both sexes are not complete. Their extents are variable with sex and temperature. These characters show maximum tendencies when the development is made at $22^{\circ}C$ (female: P = 0.996, E = 0.932, male:P = 0.961, E = 0.698). 3. The preliminary locus of Srf was determined to be 66.8 on the right arm of second chromosome by using recessive maker gene cn bw. 4. The homozygous flies(Srf/Srf) have shown perfect lethality. The heterozygotes (Srf/+), on the other hand, have shown to be viable and fertile. Srf chromosomes are kept in a balanced lethal system with Pm chromosomes which are associated with inversions. Hence, it is partially reasonable to suppose that Srf may persist in a natural population by the same mechanism. 5. Allelism test with Cy was also conducted. The fact that combination with Cy in the trans-phase (+ Srf/Cy +) is viable in contrast to the lethality of Srf/Srf and Pm/Pm indicates that Srf and Cy are not functionally allelic.

• 패션비즈니스
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• 제20권4호
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• pp.15-35
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• 2016

The purpose of this study was to develop brassiere pattern designed to fit the breast shapes based on ESMOD pattern. It has three quarters cup round shape and also consists of three parts; upper cup, lower cup, and wings. Breast types are classified into five shapes; ideal breast, flat breast, upper developed breast, lower developed breast, and projecting breast. Two subjects for each breast type wore the brassiere, and they evaluated the appearance and wearing twice. Type I for research pattern designed to fit into the breast shape reflecting details of breast size were assessed as superior to the divided commercial type. However, wings' tightness of Type I for research pattern brassiere was high. Thus, to improve wearing satisfaction, extra was added to wing. Based on the results of wearing experiments of Type I for research, we adjusted and modified Type II for research pattern. Subsequently, its appearance and wearing were evaluated, in order to be improved. For upper developed breast pattern, we extended the length of lower part to balance upper and lower part, as the upper part was somewhat long. The lower developed breast has the closest feature to the ideal breast, suggestive that implies it does not require much improvement Projecting breast pattern has minimal space in the lower part, so we added the support to lift them to be similar to the ideal breasts. For all the breast shapes, we reduced the wings' tightness from 8% to 7% so that we could extend the length of the wings.

• 한국항공우주학회지
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• 제47권2호
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• pp.81-89
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• 2019

본 연구는 쿼드 틸트 프로펠러(Quad Tilt Propeller)형상의 탠덤날개 항공기의 전진비행 조건을 풍동실험하여 전방 날개 및 프로펠러가 후방날개에 작용하는 공력 간섭효과를 분석하였다. 6축 밸런스시스템을 이용해 전기체의 힘을 측정하였고 날개뿌리에 부착된 스트레인게이지를 이용하여 각 날개의 굽힘모멘트를 측정하였다. 12홀 프로브를 이용해 날개 및 프로펠러 후류의 유동장을 측정하였으며, 털실과 스모크를 이용한 유동가시화 실험을 통해 유동 특징을 정성적으로 확인하였다. 요소별 공력간섭 현상을 측정하기 위해 프로펠러 부착 조합을 바꿔가며 전방날개와 프로펠러가 후방날개에 작용하는 영향을 분석하였다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회A
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• pp.384-388
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• 2007

Aerodynamic characteristics of Coleoptera species of Epilachna quadricollis and Allomyrina dichotoma are experimentally and numerically investigated. Using digital high speed camera and smoke wire technique, we visualized the continuous wing kinematics and the flight motion of free-flying coleoptera. The experimental visualization shows that the elytra flapped concurrently with the main wing both in the downstroke and upstroke motions. The wing motion of Epilachna quadricollis was captured and analyzed frame by frame to identify the kinematics of the wings and to implement it in the movement of a model wing (thin plate) in the simulation. The two-dimensional simulation of Epilachna quadricollis hovering flight was performed by assuming the wing cross section shape as a thin plate, even though most of insect's wings are made of curved corrugated membrane. The effect of Reynolds number are investigated by the simulation. Meanwhile, in order to investigate the role and effect of elytra, the flow visualization of Allomyrina dichotoma was carried on using smoke wire visualization technique. Here, we confirmed that the vortex generated by elytra due to its movement is strongly influence the vortex dynamic generated by hind wings.