• 한국전산유체공학회:학술대회논문집
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• 2006.05a
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• pp.263-267
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• 2006

The path of a flapping airfoil during upstroke and down-stroke is optimized for maximum thrust and propulsive efficiency. The periodic flapping motion in combined pitch and plunge is described using Non-Uniform B-Splines(NURBS). A gradient based algorithm is employed for optimization of the NURBS parameters. Unsteady, low speed laminar flows are computed using a Navier-Stokes solver in a parallel computing environment based on domain decomposition. It is shown that the thrust generation is significantly improved in comparison to the sinusoidal flapping motion. For a high thrust generation, the airfoil stays at a high effective angle of attack for short durations.

• Proceedings of the KIPE Conference
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• 2006.06a
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• pp.260-262
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• 2006

본 논문에서는 블레이드 피치각 변동을 포함한 풍력발전기 출력특성 시뮬레이션 모델을 개발하였으며, 피치각 변동이 필요한 경우를 각각 비상정지, 기동원활, 출력제한의 3가지 사례 연구를 통해 개발된 모델의 검증 수행하였다. 비상정지의 상황에서 풍력발전기의 출력특성을 모의하였고, 초기 정지 상태에서 블레이드 기동을 위한 초기 피치각 설정 및 변동하는 회전 속도에 맞는 블레이드 변동 지령 값을 구현하였으며, 정격 풍속이상에서 피치각을 감소시키는 제어기를 구현하여 정격이상의 출력 발생이 제한되는 것을 시뮬레이션을 통하여 확인하였다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.11 no.1
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• pp.57-66
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• 2003

This study is performed to secure the safety of civil aviation by establishing systematic analysis ability of Flight Data Recorder. Through this study, we analysed the flight data of A321 & A330 aircraft with lift angles and take-off actions of flight crew members.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.32.2-32.2
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• 2009

We examine cyclotron resonant interactions of radiation belt electrons with VLF chorus, plasmaspheric ELF hiss and electromagnetic ion cyclotron (EMIC) waves. Bounce-averaged diffusion rates depend on wave mode, equatorial pitch-angle, electron energy and L-shell. As well, diffusion rates can be sensitive to the latitudinal distributions of particle density and wave power. For different configurations of the plasmasphere, we calculate electron precipitation loss timescales due to combined scattering by VLF chorus, ELF hiss and EMIC waves.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.10
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• pp.60-67
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• 2005

Modern version of supersonic jet fighter aircraft must have guaranteed appropriate controllability and stability in HAoA(high angle of attack). Limit value of aircraft entering into the deep stall in HAoA is related to aircraft configuration design. But, In order to guarantee the aircraft's safety in HAoA, control law for HAoA region implemented in digital Fly-By-Wire flight control system of supersonic jet fighter. The AoA limiter is designed for positive HAoA in longitudinal control law. But, aircraft departure during aggressive negative pitch maneuver such as push over in departure resistance flight test. Therefore negative AoA limiter is needed in longitudinal control law. Result of T-50 flight test show that the AoA is exceed the limit value during aggressive positive pitch maneuver in pull up of power approach mode. In this paper, the AoA limit control law in positive and negative AoA was proposed in order to improve aircraft controllability and stability.

• Journal of Korean Foot and Ankle Society
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• v.15 no.4
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• pp.201-206
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• 2011

Purpose: Subtalar distraction arthrodesis is useful treatment option for restore hindfoot alignment. but, using structural autograft have high risk of donor site morbidity. Recently, by replacing the structural allograft has been reported satisfactory clinical results. Therefore, the authors reviewed the results of subtalar distraction arthrodesis using a structural allograft, retrospectively. Materials and Methods: From January 2008 to May 2010, 12 patients (12 feets; 9 male, 3 female) underwent subtalar distraction arthrodesis using frozen structural allograft. 9 cases were calcaneal malunion, 2 were nonunion or malunion after subtalar arthrodesis, 1 was other cause. Mean age was 38.9 (12~66) years old and follow up period was 16.5 (12~36) months. Surgical was performed with posterolateral approach and tricortical allobone block of frozen femoral neck was used. Analysis was done with retorspective manner to evaluate preoperative, postoperative, and final follow up radiologic measurement and AOFAS ankle-hindfoot scale. Results: There was statistically significant increase (p<0.05) of ankle-hindfoot scale from preoperative 27.5 points to postoperative 72.5 points, talocalcaneal height by 6.62 mm, calcaneal pitch angle by 5.73 degrees, lateral talocalcaneal angle by 6.38 degrees and significant decrease (p<0.05) of tali-1st metatarsal angle by 5.23 degrees. 11 feet (91.7%) acquired bony union and it takes average 5.1 months. Final post-operative result revealed talocalcaneal height changed by 2.57 mm, calcaneal pitch anble, lateral talocalcaneal angle, talar-1st metatarsal angle were changed by 2.63 degrees, 1.62 degrees, 1.18 degrees, respectively (p<0.05). 3 cases of partial osteonecrosis of posterior facet of calcaneus were observed in operation field, 4 cases of complication were developed (1 case of nonunion, 1 collapse of allobone graft, 1 screw loosening, 1 superficial skin necrosis). Conclusion: Subtalar distraction arthrodesis using frozen structural allobone graft is useful alternative treatment method of arthrodesis with structural autobone graft.

• Tribology and Lubricants
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• v.14 no.2
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• pp.26-34
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• 1998

This paper presents a high-speed performance analysis of ball bearings with ceramic balls under thrust loads. The sliding velocity profiles between a ball and raceways were obtained by the 3-D quasi-dynamic equations of motion including both centrifugal force and gyroscopic moment derived by vector matrix algebra. The friction at the contact areas was obtained by the Bair-Winer's non-Newtonian rheological model and the Hamrock-Dowson's central film thickness in EHL analysis. The nonlinear equations were solved by the Newton-Raphson method and the underrelaxation iterative method. The friction torques and ball behaviors with various loads, ball materials, and contact angles were predicted by this model. It was shown that the friction torque was sensitive to thrust load and contact angle, and that the friction torque and the pitch angle of the bearing with ceramic balls are smaller than those of the bearing with steel balls.

• Tribology and Lubricants
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• v.25 no.5
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• pp.298-304
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• 2009

An angled labyrinth seal is used for the diaphragm-packing-ring seal design of steam turbine due to its leakage reduction characteristic. CFD analysis using FLUENT has been performed to predict leakage and determine an optimum slanted angle which yields the best leakage reduction. Results show that the optimum value of slanted angle is $-30^{\circ}$ independent of number of labyrinth teeth, inlet pressure, and tooth height to pitch ratio. 3D CFD analysis has been performed for predicting leakage of the angled labyrinth seal. Comparing with the result of 2D CFD analysis, 3D CFD analysis shows 1.4% smaller.

• ETRI Journal
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• v.36 no.2
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• pp.232-241
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• 2014

A holographic display system with a 22-inch LCD panel is developed to provide a wide viewing angle and large holographic 3D image. It is realized by steering a narrow viewing window resulting from a very large pixel pitch compared to the wave length of the laser light. Point light sources and a lens array make it possible to arbitrarily control the position of the viewing window for a moving observer. The holographic display provides both eyes of the observer with a holographic 3D image using two vertically placed LCD panels and a beam splitter to support the holographic stereogram.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 2002.05a
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• pp.285-290
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• 2002

Screw in injection molding machine is affected by heat flux, pressure on inside barrel, geometry of screw including flight number, pitch and flight angle. Volumetric efficiency increases as the flight number increases, but it didn't show steady tendency according to helix angle of flight. Heat flux from heating pad and injection pressure play a very important role on the thermal behavior characteristics. The increased number of multi-flight is merits and demerits for a screw efficiency. So, we have to optimize flight number of the screw considering temperature, displacement, distortion and stress of the screw.