• 한국방재학회 논문집
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• 제8권5호
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• pp.147-153
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• 2008

저수호안에 작용하는 외력들 중에서 유수에 의한 소류력과 항행하는 선박에 의한 항주파는 호안의 안정성에 가장 큰 영향을 미칠 수 있는 항목들이다. 본 연구에서는 이러한 외력들에 대해 호안의 안정성을 분석하였다. 분석대상지역은 서울시의 한강인공호안을 생태녹지공간으로 조성하는 시험시공구간이다. RMA-2모형을 이용하여 계산된 유속을 사용하여 소류력을 산정하고, 안정성은 대상구간에 대해 계산한 계산소류력과 호안재료의 허용소류력을 비교하여 분석하였다. 분석결과 측점 93의 200년빈도 계산소류력이 허용소류력을 초과하여 이 지점은 수리적안정성이 확보되지 않는 지점으로 판단할 수 있었다. 2007년 8월 10일의 강우에 대해서는 전구간에서 계산소류력이 허용소류력보다 작게 모의되었다. 따라서 소류력에 대해서는 안정하다고 판단할 수 있으나 부분적으로 호안이 침수된 부분에 세굴이 발생한 이유는 시공후 식생이 활착할 시간이 부족한 상태에서 작은 소류력에 대해서도 세굴이 발생하였으며, 항주파 등의 다른 외력과 중첩되어 발생하였다고 생각된다. 한강을 운행하는 한강유람선과 수상택시에 의해 발생하는 항주파를 계산하였으며 이를 이용하여 호안에 미치는 파력을 산정하여 호안재료에 따른 지지력과 비교하였다. 그 결과 한강을 운항하는 선박들이 호안에 미치는 외력은 허용지지력보다 매우 작은 값으로 판단되므로 호안은 항주파에 대해서는 안정하다고 판단할 수 있으나 소류력 등의 다른 외력과 동시에 작용할 경우소류력 등의 다른 외력과 동시에 작용할 경우에는 복합적인 외력을 고려해야 할 것이다.

• 대한조선학회논문집
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• 제48권5호
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• pp.445-450
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• 2011

In order to estimate a yacht sail performance, measuring system of aerodynamic forces acting on the yacht sail is constructed and experiments of flexible model sail are carried out at the medium-size subsonic wind tunnel of Chungnam National University. Experimental results for a flexible sail are compared with experimental and numerical results of fixed shape sail. In case of a fixed shape sail, lift and drag coefficients are rarely changed at all velocity conditions. However, those of the flexible sail are decreased as the incoming velocity is increased. These are understandably resulted from shape variations due to the flexible material. Therefore aero-elastic similarity should be more carefully considered in the model test rather than other similarities.

• 대한조선학회논문집
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• 제50권5호
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• pp.282-290
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• 2013

The effects of the combination of blade number for forward and after propeller on the propeller shaft forces of a contra-rotating propeller (CRP) system are presented in the paper. The research is performed through the numerical simulations based on the Reynolds-Averaged Navier-Stokes equations (RANS). The simulation results of the present method in open water condition are validated comparing with the experimental data as well as the other numerical simulation results based on the potential method for 4-0-4 CRP (3686+3687A) and 4-0-5 CRP (3686+3849) of DTNSRDC. Two sets of CRP are designed and simulated to study the effect of the combination of blade number in behind-hull condition. One set consists of 3-blade and 4-blade, while the other is 4-blade and 4-blade. A full hull body submerged under the free surface is modeled in the computational domain to simulate directly the wake field of the ship at the propeller plane. From the simulation results, the fluctuations of axial force and moment are dominant in the case of same blade numbers for forward and after propellers, whereas the fluctuations of horizontal and vertical forces and moments are very large in the case of different blade numbers.

• 한국항공운항학회지
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• 제17권4호
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• pp.8-16
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• 2009

An experimental study was carried out to investigate aerodynamic characteristics on reduced frequency of flapping wings. The half span of the wing is 28cm, and the mean chord length of wing is 10cm. In flight, the Reynolds Number range of birds is about $10^4$, and the reduced frequency during a level flight is 0.25. The experimental variables of present study were set to have similar conditions with the bird flight's one. The freestream velocities in a wind tunnel were 2.50, 3.75 and $5.00^m/s$, and the corresponding Reynolds numbers were $1.7{\times}10^4$, $2.5{\times}10^4$ and $3.3{\times}10^4$, respectively. The wing beat frequencies of an experimental model were 2, 3 and 4Hz, and the corresponding reduced frequency was decided between 0.1 and 0.5. Aerodynamic forces of an experimental flapping model were measured by using 2 axis load-cell. Inertial forces measured in a vacuum chamber were removed from measuring forces in the wind tunnel in order to acquire pure aerodynamic forces. Hall sensors and laser trigger were used to make sure the exact position of wings during the flapping motion. Results show that the ratio of downstroke in a wing beat cycle is increased as a wing beat frequency increases. The instantaneous lift coefficient is the maximum value at the end of downstroke of flapping wing model. It is found that a critical reduced frequency with large lift coefficient is existed near k=0.25.

• 문화기술의 융합
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• 제9권3호
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• pp.371-376
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• 2023

라오즈하오(老字号)란 오랜 역사를 지닌 제품, 기술 또는 서비스를 가리키며, 중국 전통문화 배경과 깊은 역사유산을 갖고 있으며, 사회적으로 인정받아 우수한 평판을 형성한 브랜드를 의미한다. 일부 라오즈하오는 발전하고 있지만, 일부 라오즈하오는 생존의 위기에 직면하고 있으며, 중국 정부와 사회는 다양한 지원정책을 발표하여 지속적인 발전을 위해 노력하고 있다. 현재 한국에서 라오즈하오에 대한 연구가 매우 부족하기에, 본 연구는 중국 화장품브랜드 시에푸춘(謝馥春)의 역사, 현황, 경쟁력을 분석하였다. 연구결과, 시에푸춘은 중국 최초의 화장품 기업으로서, 전통문화를 계승한 제조기법을 가졌으며, 현재 상당한 시장 점유율을 유지하고 있다. 5-Forces 모델을 활용하여 시에푸춘의 경쟁력을 분석하고, 라오즈하오 기업에 대한 시사점과 발전모델을 제시하였다.

• 한국해안해양공학회지
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• 제12권4호
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• pp.157-167
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• 2000

한국해양연구소는 1998년에 이어도 종합해양과학기지의 기본설계를 수행한 바 있으며 심해 설계파에 Morison 식과 Stream function 이론을 적용하여 설계파력을 결정한 바 있다. 본 연구에서는 삼차원 수리모형실험 통하여 이어도 해역에서의 파랑전파를 모의하였으며, 구조물의 파력 및 Air gap를 계측하고 이들을 SACS 프로그램의 계산치와 비교함으로써 기본설계 값들의 타당성을 검토하였다. 그 결과, 시도된 4개의 심해파향 중에서 SSW, S, SE계열의 파향에 대해서는 계측치가 SACS 계산치 보다 작게 나타났다. 그러나, 유일하게 구조물에 미치기 전에 쇄파되는 NNW계열의 파향에서는 전반적으로 SACS 계산치를 상회하였으며, 그방향성 흐름과 파가 복합되어 있는 경우와 매우 유사한 파력변화를 보여주었다. 구조물의 Air gap은 모든 심해파향에 대하여 계측치가 기본설계치보다 작은 것으로 나타났다.

• 소성∙가공
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• 제18권5호
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• pp.371-376
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• 2009

An equivalent drawbead model(EDM) for sheet metal forming analysis, which replaces complex drawbead geometries with drawbead forces in modeling the stamping dies with finite elements, is experimentally verified and applied to the numerical simulation of auto-panel stamping process. The drawbead restraining and opening forces of elliptical drawbead, circular drawbead, square drawbead, and step drawbead are obtained by performing the drawbead pulling test and compared with those of EDM and commercial code models(CCM). Better agreement with experimental measurements is found in EDM than CCM. Furthermore, the excellence of EDM is demonstrated in its application to the auto-body stamping analysis.

• Wind and Structures
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• 제20권6호
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• pp.811-827
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• 2015

This study presents experimental and numerical aerodynamic investigation of a prototype vehicle. Aerodynamics forces examined which exerted on a prototype. This experimental study was implemented in a wind tunnel for the Reynolds number between $10^5-3.1{\times}10^5$. Numerical aerodynamic analysis of the vehicle is conducted for different Reynolds number by using FLUENT CFD software, with the k-$\varepsilon$ realizable turbulence model. The studied model aims at verifying the aerodynamic forces between experimental and numerical results. After the Reynolds number of $2.8{\times}10^5$, the drag coefficient obtained experimentally becomes independent of Reynolds number and has a value of 0.25.

• 한국정밀공학회지
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• 제15권5호
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• pp.145-152
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• 1998

In this research, in order to predict the cutting force using a mechanistic model, specific cutting force was firstly obtained through the cutting experiments. Band sawing process is similar to a milling, that is multi-point cutting. Therefore it is not easy matter to evaluate specific cutting force. Thus, the thickness of workpiec was made smaller than one pitch of the saw in terms of fly cutting in the face milling process. Then the cutting force was predicted by analyzing the geometric shape of a saw tooth The tooth shape used in the research was raker set style that was generally used in band sawing. And a set of teeth is comprised of three teeth, those are ranked as left, straight and right. The mechanistic model was developed in this study considered those shapes of each tooth. From the validation experiments, the predicted cutting forces coincided well with the measured ones. Therefore the predicted cutting forces can be used for the adaptive control of saw engaging feed rate in the band sawing.

• International Journal of Aeronautical and Space Sciences
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• 제13권4호
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• pp.446-457
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• 2012

Aeroelastic analysis of an aircraft with a high aspect ratio wing for medium altitude and long endurance capability was attempted in this paper. In order to achieve such an objective, various structural models were adopted. The traditional approach has been based on a one-dimensional Euler-Bernoulli beam model. The structural analysis results of the present beam model were compared with those by the three-dimensional NASTRAN finite element model. In it, a taper ratio of 0.5 was applied; it was comprised of 21 ribs and 3 spars, and included two control surfaces. The relevant unsteady aerodynamic forces were obtained by using ZAERO, which is based on the doublet lattice method that considers flow compressibility. To obtain the unsteady aerodynamic force, the structural mode shapes and natural frequencies were transferred to ZAERO. Two types of unsteady aerodynamic forces were considered. The first was the unsteady aerodynamic forces which were based on the one-dimensional beam shape; the other was based on the three-dimensional FEM model shape. These two types of aerodynamic forces were compared, and applied to the foregoing flutter analysis. The ultimate goal of the present research is to analyze the possible interaction between the rigid-body degrees of freedom and the aeroelastic modes. This will be achieved after the development of a reliable nonlinear beam formulation that would validate the current results as well as enable a thorough investigation of the nonlinearity. Moreover, such analysis will allow for an examination of the above-mentioned interaction between the flight dynamics and aeroelastic modes with the inclusion of the rigid body degrees of freedom.