• International Journal of Air-Conditioning and Refrigeration
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• 제16권3호
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• pp.100-107
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• 2008

The heat transfer and friction characteristics of heat exchangers having convex louver fins are experimentally investigated, and the results are compared with those of wave fin counterparts. Eighteen samples (nine convex louver fin samples and nine wave fin samples) which had different fm pitches (1.81 mm to 2.54 mm) and tube rows (one to four) were tested. The convex angle was $11.7^{\circ}$. The j factors are insensitive to fin pitch, while f factors increase as fin pitch increases. The effect of fin pitch on f factor is more significant for the wave fin compared with the convex louver fin. It appears that the complex fin pattern of the convex louver fin induces intense mixing of the flow, and thus reduces the effect of fin pitch. Both the j and f factors decrease as the number of tube row increases. However, as the Reynolds number increases, the effect of tube row diminishes. Comparison of the convex louver fin j factors with those of wave fin reveals that convex louver fin j factors are 18% to 29% higher than those of wave fin. The f factors are 16% to 34% higher for the convex louver fin. The difference increases as fin pitch decreases. Existing correlation fails to adequately predict the present data. More data is needed for a general correlation of the convex louver fin geometry.

• 대한족부족관절학회지
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• 제22권1호
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• pp.16-20
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• 2018

Purpose: To evaluate the clinical and radiographic results of surgical treatment for patients with sinus tarsi pain due to accessory talar facet impingement. Materials and Methods: Between July 2013 and July 2015, nine patients who underwent surgery for the accessory talar facet impingement were reviewed. The mean follow-up period was 18.6 months (12~36 months), and the mean age was 33.1 years (19~60 years). Previous trauma history, duration of symptom, and types of surgery were analyzed. The clinical results were evaluated using the American Orthopaedic Foot and Ankle Society (AOFAS) ankle-hindfoot score and visual analogue scale (VAS). Radiographic results were assessed using Meary's angle, calcaneal pitch angle, heel alignment angle, and heel alignment ratio. Results: All patients had evident trauma history prior to the initial symptom. The mean duration of symptoms was 25.6 months (6~120 months). Four patients received only accessory anterolateral talar facet (AALTF) excision, and four patients received medial sliding calcaneal osteotomy (MSCO). One patient underwent both AALTF excision and MSCO. The AOFAS ankle-hindfoot score was significantly improved from 73 (62~77) preoperatively to 93 (67~100) postoperatively. The VAS score was decreased from 6 (5~7) preoperatively to 1 (0~5) postoperatively. The Meary's angle and calcaneal pitch angle showed no significant difference after surgery. The heel alignment angle and ratio increased from $-3.6^{\circ}$ ($-10^{\circ}{\sim}5^{\circ}$) and 0.22 (-0.15~0.6) preoperatively to $2.8^{\circ}$ ($1^{\circ}{\sim}5^{\circ}$) and 0.42 (0.3~0.6) postoperatively, respectively. Conclusion: If there is persistent sinus tarsi pain in patients with hindfoot valgus, accessory talar facet impingement caused by AALTF could be considered as a cause of chronic sinus tarsi pain.

• 한국항공우주학회지
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• 제39권6호
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• pp.505-516
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• 2011

통합유도조종(IGC, Integrated Guidance and Control)은 기존의 분리형 유도조종루프의 성능한계를 극복하기 위해 제안된 개념이다. 본 논문에서는 입사각제어가 가능한 새로운 형태의 IGC 기법을 제안하였다. 제안된 IGC는 자동조종성능과 유도성능을 동시에 얻기 위해 받음각, 피치각속도, 피치각, 시선각을 상태변수로 고려한다. 제안된 IGC의 제어특성을 고찰하기 위하여 비선형 상태방정식에 대한 가제어성 해석 및 평형점 해석을 수행 하였다. IGC 모델에 대한 제어기법으로는 LQR(Linear Quadratic Regulator)을 사용하였으며 LQR을 IGC에 적용하기 위한 방법을 상세하게 설명하였다. 수치 시뮬레이션을 통해 분리형 유도조종루프와 IGC의 성능을 비교하였다. 성능 비교 결과 IGC는 급격한 기동이 필요한 유도기하에 대하여 분리형 유도조종루프에 비해 우수한 유도성능을 보임을 확인하였다.

• 대한기계학회논문집B
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• 제41권1호
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• pp.1-8
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• 2017

대기압 하에서 포화 상태를 유지하는 물의 내부에 잠긴 탠덤 튜브에 적용하기 위한 실험적 상관식을 새롭게 개발하였다. 상관식은 다발효과를 계산하기 위한 것으로 실험에서 측정한 값과 최소자승법을 사용하여 결정하였다. 상관식의 적절함을 평가하기 위해 통계분석을 수행하였다. 상관식은 실험값을 ${\pm}8%$ 범위 내에서 잘 예측함을 확인하였다. 상관식의 적용 범위는 피치=28.5~114mm, 방위각=$0^{\circ}{\sim}90^{\circ}$, 경사각=$0^{\circ}{\sim}90^{\circ}$, 상부 및 하부 튜브 열유속=$0{\sim}120kW/m^2$이다.

• International Journal of Aeronautical and Space Sciences
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• 제6권2호
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• pp.23-32
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• 2005

An experimental control system is proposed for the attitude control of a simplified 2-DOF helicopter model. The main rotor is a rigid one, and the fuselage is simply supported by a fixed hinge point where the longitudinal motion is decoupled from the lateral one since the translations and the rolling rotation are completely removed. The yaw trim of the helicopter is performed with a tail rotor, by which the azimuthal attitude can be adjusted on the rotatable post in the yaw direction. The robust sliding mode control tracking a given attitude angle is proposed based on the flight dynamics. A pitch damper is inserted for the control of pitching angle while the compensator to reaction torque is used for the control of azimuth angle. Several parameters of the system are selected through experiments. The results shows that the proposed control method effectively counteracts nonlinear perturbations such as main rotor disturbance, undesirable chattering, and high frequency dynamics.

• Journal of Astronomy and Space Sciences
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• 제36권2호
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• pp.45-60
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• 2019

The Earth's outer radiation belt has long received considerable attention mainly because the MeV electron flux in the belt varies often dramatically and at various time scales. It is now widely accepted that the wave-particle interaction is one of the major mechanisms responsible for such flux variations. The wave-particle interaction can accelerate electrons to MeV energies, explaining the observed flux increase events, and can also scatter the electrons' motion into the loss cone, resulting in atmospheric precipitation and thus contributing to flux dropouts. In this paper, we provide a review of the current state of research on relativistic electron scattering and precipitation due to the interaction with electromagnetic ion cyclotron (EMIC) waves in the inner magnetosphere. The review is intended to cover progress made over the last ~15 years in the theory and simulations of various issues, including quasilinear resonance diffusion, nonlinear interactions, nonresonant interactions, effects of finite normal angle on pitch angle scattering, effects due to rising tone emission, and ways to scatter near-equatorial pitch angle electrons. The review concludes with suggestions of a few promising topics for future research.

• Journal of Astronomy and Space Sciences
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• 제35권3호
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• pp.195-200
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• 2018

The present paper describes the design of a Solid State Telescope (SST) on board the Korea Astronomy and Space Science Institute satellite-1 (KASISat-1) consisting of four [TBD] nanosatellites. The SST will measure these radiation belt electrons from a low-Earth polar orbit satellite to study mechanisms related to the spatial resolution of electron precipitation, such as electron microbursts, and those related to the measurement of energy dispersion with a high temporal resolution in the sub-auroral regions. We performed a simulation to determine the sensor design of the SST using GEometry ANd Tracking 4 (GEANT4) simulations and the Bethe formula. The simulation was performed in the range of 100 ~ 400 keV considering that the electron, which is to be detected in the space environment. The SST is based on a silicon barrier detector and consists of two telescopes mounted on a satellite to observe the electrons moving along the geomagnetic field (pitch angle $0^{\circ}$) and the quasi-trapped electrons (pitch angle $90^{\circ}$) during observations. We determined the telescope design of the SST in view of previous measurements and the geometrical factor in the cylindrical geometry of Sullivan (1971). With a high spectral resolution of 16 channels over the 100 keV ~ 400 keV energy range, together with the pitch angle information, the designed SST will answer questions regarding the occurrence of microbursts and the interaction with energetic particles. The KASISat-1 is expected to be launched in the latter half of 2020.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2011년도 제41회 하계 정기 학술대회 초록집
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• pp.277-277
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• 2011

디스플레이의 기술발전에 의해 대면적 고해상도의 LCD가 제작되어 왔다. 이에 따라 LCD 점등검사를 위한 Probe Unit의 기술 또한 급속도로 발전하고 있다. 고해상도에 따라 TFT LCD pad가 미세피치화 되어가고 있으며, panel의 검사를 위한 Probe 또한 30 um 이하의 초미세피치를 요구하고 있다. 따라서, 초미세 pitch의 LCD panel의 점등검사를 위한 Probe Unit의 개발이 시급하가. 본 연구에서는 30 um 이하의 미세피치의 Probe block을 위한 Slit wafer의 식각 공정 조건을 연구하였다. Si 공정에서 식각율과 식각깊이에 따른 profile angle의 목표를 설정하고, 식각조건에 따라 이 두 값의 변화를 관측하였다. 식각실험으로 Si DRIE 장비를 이용하여, chamber 압력, cycle time, gas flow, Oxygen의 조건에 따라 각각의 단면 및 표면을 SEM 관측을 통해 최적의 식각 조건을 찾고자 하였다. 식각율은 5um/min 이상, profile angle은 $90{\pm}1^{\circ}$의 값을 목표로 하였다. 이 때 최적의 식각조건은 Etching : SF6 400 sccm, 10.4 sec, passivation : C4F8 400 sccm, 4 sec의 조건이었으며, 식각공정의 Coil power는 2,600 W이었다. 이러한 조건의 공정으로 6 inch Si wafer에 공정한 결과 균일한 식각율 및 profile angle 값을 보였으며, oxygen gas를 미량 유입함으로써 식각율이 균일해짐을 알 수 있었다. 결론적으로 최적의 Slit wafer 식각 조건을 확립함으로써 Probe Unit을 위한 Pin 삽입공정 또한 수율 향상이 기대된다.

• 제어로봇시스템학회논문지
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• 제13권1호
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• pp.6-14
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• 2007

Modem version of supersonic jet fighter aircraft must have been guaranteed appropriate controllability and stability in HAoA(High Angle of Attack). Limit value of aircraft entering into the departure in HAoA is related to aircraft configuration design. But, the control law such as AoA and yaw-rate limiter is implemented in digital Fly-By-Wire flight control system of supersonic jet fighter to guarantee the aircraft's safety in HAoA. The HAoA flight control law have two parts, one is control law of departure prevention and the other is control law of departure recovery support. The control laws of departure prevention for advanced jet trainer consist AoA limiter, roll command limiter and rudder fader. The control laws of departure recovery support are consist yaw-rate limiter and MPO(Manual Pitch Override) mode. The guideline of pitch rocking using MPO mode is simple, but operating skill of pitch rocking is very difficult by the pilot with inexperience of departure situation. This paper addresses the design and validation of APR(Automatic Pitch Rocker) control law instead of MPO in order to automatic recovery without manual pitch rocking by the pilot. And, recovery characteristic with APR verifies by the nonlinear analysis and pilot evaluation.

• 조명전기설비학회논문지
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• 제18권2호
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• pp.142-149
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• 2004

본 논문은 바람으로부터 최대출력을 추출하기 위해 계통연계 풍력발전시스템의 신경회로망 제어기와 추출된 최대출력을 계통에 전달하기 위한 전력제어기를 제안한다. 유도발전기, 변압기, 정류기 및 인버터 등으로 구성된 제어기를 갖춘 풍력발전시스템의 모델링과 시뮬레이션에 대해 검토하고자 한다. 본 논문에서는 동특성해석을 위해 드라이브 트레인 모델, 유도발전기 모델과 계통접속 모델을 제시한다. 신경회로망 제어기는 풍차날개의 피치각을 제어하여 바람으로부터 최대출력을 추출한다. 피치제어방법은 기계적으로 복잡하지만 제어성능은 스톨제어보다 우수하게 된다. MATLAB으로 수행한 시뮬레이션 결과는 발전기 토오크, 발전기 회전속도, 피치각, 계통으로 주입되는 유효/무효전력 등을 예시하고 있으며 그 결과를 보면 제안된 제어기의 효용성을 입증할 수 있다.