• Parasites, Hosts and Diseases
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• 제52권5호
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• pp.537-540
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• 2014

We present a case of ocular toxocariasis treated successfully with oral albendazole in combination with steroids. A 26-year-old male visited the authors' clinic with the chief complaint of flying flies in his right eye. The fundus photograph showed a whitish epiretinal scar, and the fluorescein angiography revealed a hypofluorescein lesion of the scar and late leakage at the margin. An elevated retinal surface and posterior acoustic shadowing of the scar were observed in the optical coherence tomography, and Toxocara IgG was positive. The patient was diagnosed with toxocariasis, and the condition was treated with albendazole (400 mg twice a day) for a month and oral triamcinolone (16 mg for 2 weeks, once a day, and then 8 mg for 1 week, once a day) from day 13 of the albendazole treatment. The lesions decreased after the treatment. Based on this study, oral albendazole combined with steroids can be a simple and effective regimen for treating ocular toxocariasis.

• 한국소음진동공학회논문집
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• 제14권12호
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• pp.1347-1353
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• 2004

With respect to the researches of the optical flying head(OFH) , the head-gimbal assembly should be analyzed to guarantee the stable fabrication and the characteristics of shock resistance. The suitable design is proved through the Probabilistic analysis of the design parameters and material properties of the model. Probabilistic analysis is a technique that be used to assess the effect of uncertain input parameters and assumptions on your analysis model. Using a probabilistic analysis you can find out how much the results of a finite elements analysis are affected by uncertainties in the model. Another factor is analysis of the dynamic shock analysis. For the mobile application, one of the important requirements is durability under severe environmental condition, especially, resistance to mechanical shock. An important challenge in the disk recording is to improve disk drive robustness in shock environments. If the system comes in contact with outer shock disturbance. the system gets critical damage in head-gimbal assembly or disk. This paper describes probabilistic and dynamic shock analysis of head-gimbal assembly in micro MO drives using OFH slider.

• 한국추진공학회지
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• 제20권5호
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• pp.90-98
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• 2016

극초음속 공기 흡입 추진기관의 지상 시험 시 추진기관의 고속 비행 조건을 모의하기 위해 고온 공기를 공급할 수 있는 고온 공기 가열기가 필요하다. 본 논문에서는 다양한 고온 가열기들을 조사하여 유형별로 정리하고, 장단점을 비교하였다. 가열기는 크게 유동장 내 연소 가열기, 아크 가열기, 축열식 가열기, 열교환식 가열기 4종류로 분류할 수 있었으며, 각각의 장단점이 다양하므로 목적에 맞게 가열기를 선정하여야 한다.

• 한국철도학회논문집
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• 제13권4호
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• pp.376-381
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• 2010

본 연구에서는 주요 간선 철도 노선의 고속화 시 열차풍 예측을 위하여 KTX 열차, 누리로 열차 및 TTX 열차를 대상으로 호남선과 경부선에서 Kiel-probe를 이용한 열차풍 측정 프루브 어레이와 다채널 압력측정 시스템을 이용하여 열차풍 현장 측정 시험을 수행하였다. 시험 결과, 열차가 통과하는 동안의 열차하부 평균유속을 열차의 속도로 나눈 값은 열차 속도에 무관하고 차량의 종류에만 관계하기 때문에, 주어진 열차의 종류와 열차 속도에 대하여 열차 하부의 유속을 예측할 수 있는 것으로 나타났다. 또한 열차 하부 형상과 하부 열차풍특성의 관계에 대해서도 논하였다.

• International Journal of Aeronautical and Space Sciences
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• 제9권1호
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• pp.121-128
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• 2008

This paper describes the modeling and autopilot design procedure of a Blended Wing-Body(BWB) UAV. The BWB UAV is a tailless design that integrates the wing and the fuselage. This configuration shows some aerodynamic advantages of lower wetted area to volume ratio and lower interference drag as compared to conventional type UAV. Also, BWB UAV may be increase payload capacity and flight range. However, despite of these benefits, this type of UAV presents several problems related to flying qualities, stability, and control. In this paper, the detailed modeling procedure of BWB UAV and stability analysis results using the linearized model at trim condition are represented. Finally, we designed the autopilot of BWB UAV based on a simple control allocation scheme and evaluated its performance through nonlinear simulation.

• International Journal of Naval Architecture and Ocean Engineering
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• 제9권1호
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• pp.35-44
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• 2017

Supercavitation is one of the most attractive technologies to achieve high speed for underwater vehicles. However, the multiphase flow with high-speed around the supercavitating vehicle (SCV) is difficult to simulate accurately. In this paper, we use modified the turbulent viscosity formula in the Standard K-Epsilon (SKE) turbulent model to simulate the supercavitating flow. The numerical results of flow over several typical cavitators are in agreement with the experimental data and theoretical prediction. In the last part, a flying SCV was studied by unsteady numerical simulation. The selected computation setup corresponds to an outdoor supercavitating experiment. Only very limited experimental data was recorded due to the difficulties under the circumstance of high-speed underwater condition. However, the numerical simulation recovers the whole scenario, the results are qualitatively reasonable by comparing to the experimental observations. The drag reduction capacity of supercavitation is evaluated by comparing with a moving vehicle launching at the same speed but without supercavitation. The results show that the supercavitation reduces the drag of the vehicle dramatically.

• 화약ㆍ발파
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• 제24권2호
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• pp.75-82
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• 2006

우리나라 석회석 광산 대부분은 광상의 부존조건, 채광실수율, 안전조업, 경제성 등을 고려하여 노천채굴 방식을 채택하고 있으나, 광산개발 과정에 따른 진입로 확보, 발파 및 장비굴착, 암석의 파쇄 및 분쇄, 운반, 선광 등으로 인한 먼지의 날림, 소음, 진동, 폐석사면 붕괴에 의한 농경지 훼손 등의 광해를 발생시켜 환경적인 문제를 유발시키고 있다. 본 연구에서는 석회석 노천채굴 작업에 따른 주변의 환경피해 최소화와 광해에 따른 경제적 손실을 감소시키기 위해 현장 시공과정에서 체험하였던 광해저감 방법들을 제시하였다.

• 한국군사과학기술학회지
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• 제25권6호
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• pp.596-605
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• 2022

In this study, analysis of dynamic characteristics and flight vibration was performed to unmanned aerial vehicles. The analysis model was supplemented by performing a dynamic characteristic test and a random vibration test using manufactured dummy aerial vehicle. For the dynamic characteristic test, a bungee cable was used to implement the free end boundary condition. Prior to the flight vibration test using a multiple electric shaker, a random vibration test was performed to predict the excitation force during the actual flight vibration test. It was judged that the actual test could be predicted more accurately by supplementing the analysis model from the test results. In addition, it was possible to determine the feasibility of the test by predicting the excitation force of the flight vibration test.

• 한국농공학회지
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• 제6권2호
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• pp.816-825
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• 1964

1. Outline: The flow of the siphon spillway is very intricate and affected by vacuous condition. It is an intresting problem to make vacuum rapidly in_siphon, i.e, to provoke the perfect siphonaoge with the lowest water-level of overflow. The hydraulic experiments of siphon spillway have practiced at the Masan Lake, Haenam, the province of Junnam and gained rational and economical results which cannot be odtained by calculation. 2. Experiment: The model scale was a half of that of the prototype. 3. Results and discussion: In the experiments of 14 runs, washing, overflow water level, outlet, water level of cushion, phenomenon of water flying and water pressure of every part, etc. were studied. a) The relation of overflow water-level at siphon inlet and deflector When the elevation of the deflector is 10. 65m and the form of deflector O.4m long is the hypotenuse of an $45^{\circ}$ isosceles triangle, the over flow water-level is the minimum, i. e. the siphonage was excellent. There is no effect by the rising of overflow water-Ievel between 11.95m to 1O.65m of deflector elevation (in the first plan, it is 11.05m). But the overflow water-level rises remarkably in the outside region of the above limits. b) The relation of overflow water-level, the length of cushion and standard height of the base. The reduction of the length of cushion brings the rising of overflow waterlevel, and the rising of the standard height of the base brings the rising of overflow water level. For the long cushion length and low standard height of the base, it cannot be expeted to have the falling of overflow water-level. The most satisfactory data were obtained at 5.20m of the base standard height and 6.1m of the length of cushion. The first vah,le planned was 5.70 m and 4.30m.

• 한국항공우주학회지
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• 제37권6호
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• pp.519-526
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• 2009

본 논문에서는 커나드와 테일핀을 가진 지대지 유도미사일이 대기권을 비행할 때 최대 사거리를 갖기 위한 효율적인 외형 형상 최적화 기법 연구에 대하여 기술하였다. 이를 위하여 비행궤적 해석 기법과 최적화 기법을 연계하여 미사일의 사거리 증대를 위한 외형 형상 최적화 전산 프로그램 시스템을 구축하였다. 비행궤적 해석부분에서는 반실험적 기법을 이용한 공력해석프로그램인 Missile DATCOM을 직접 연결하여 운동방정식 계산에 필요한 공력계수들을 계산 시간 단계 마다 효율적으로 제공할 수 있게 하였고 최고점 이후의 활공비행 구간에서는 최대 양항비를 갖는 Trim 조건 계산 모듈을 첨가하여 활공비행전 영역에서 최대 양항비 상태에서 지속적으로 비행한다는 가정으로 계산 하였다. 최적화 기법으로는 Response Surface Method(RSM)를 적용하여 계산 시간 효율화를 꾀하였다.