• Proceedings of the Korean Vacuum Society Conference
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• 1999.07a
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• pp.230-230
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• 1999

PDP 미세면방전에서 방전의 전기, 광학적 특성을 이해하기 위해서는 근본적으로 면방전에 대한 기초적인 이해와 연구가 뒤따라야 한다. 따라서 본 연구에서는 일차적으로 방전 전극구조에서 방전 전압변화에 가장 중요한 변수인 방전 유지 전극 간격에 대해서 구동 진동수, 유전체 두께, 전극폭, MgO 보호막 두께 등과 같은 다른 변수들은 고정시켜 놓고 방전기체종류(Ne,Xe, He)와 Xe 기체혼합 비율 (1%, 4%, 7%등)에 따라서 방전유지 전극간격(50, 100, 150, 200$mu extrm{m}$)을 변화시켜가며 실험을 수행했다. 방전 유지 전극의 간격(d)이 좁을수록 방전개시(Vf), 유지 전압(Vs)은 낮아지고 전극간격을 점차로 넓게 하면 방전개시, 유진 전압이 높아지게 되는 즉 전극 간격에 따라서 가스 압력(P)에 따른 파센 최저방전 개시전압과 최저방전 유지전압 특성곡선이 존재함을 알 수 있었다. 또한 단일종의 기체를 사용했을 때 보다는 혼합기체를 사용했을 때 Penning effect에 의해서 방전 전압이 상대적으로 낮아지는 경향을 관측 할 수 있었으며, Xe 기체 혼합 비율에 따른 방전전압 특성 또한 관측하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.1
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• pp.17-25
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• 2017

An experimental study was performed for the combustion-field visualization of the burner which burns the liquid hydrocarbon fuel atomized by an ultrasonic oscillator. Configurations of the flame and temperature gradient were caught by both high-speed camera and thermo-graphic camera, and those images were analyzed in detail through a post-processing. In addition, the fuel consumption was measured using the balance during the combustion reaction. As a result, the consumption of atomized fuel increased with the increasing flow-rate of carrier-gas, but any correlation between the air/fuel ratio and carrier-gas flow-rate was not found at the low flow-rate condition. Also, the combustion-field grew and reaction-temperature rose due to the strengthening of combustion reaction with the increasing flow-rate of carrier-gas and power consumption of ultrasonic oscillator.

• Journal of Aerospace System Engineering
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• v.16 no.5
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• pp.78-85
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• 2022

Multicopter-type unmanned aerial vehicles (UAV) are increasingly for cargo transportation to mountainous and island regions, image information acquisition in disaster areas, and emergency rescue transport. In order to successfully perform these tasks, the aircraft structure must be able to safely support the loads induced by flight conditions while ensuring the vibration and aeroelastic stability of the prop-rotor. This study introduced a structural analysis model of a 40kg payload multicopter with an engine-generator hybrid power system. The deformation and stress distribution are investigated depending on the load conditions. In addition, the vibration characteristics and aeroelastic stability of the prop-rotor were also presented to flight speed and aircraft pitch angle. The maximum thrust generated by the prop-rotor and the landing load applied to the multicopter under normal and emergency landing conditions were reviewed., It confirmed that the structure could support without failure. In addition, it confirmed that the damping characteristics of each primary locate in the constant region according to the aircraft's flight speed and the prop-rotors rotating speed.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.185-185
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• 2004

최근 고속 회전기계에 사용되고 있는 공기호일 베어링은 동압형 기체 베어링으로 매우 안정적이고, 보통의 저널 베어링에서 발생할 수 있는 불안정한 진동을 최소화 할 수 있는 장점을 가지고 있다. 또한 높은 안정성 및 축 자체에 자동 조절 기능을 가지고 있어서 극저온 기계 및 고속 회전기계에 널리 사용되고 있다. 이러한 고속 회전기계는 축의 기동 및 정지 시, 위험속도를 안전하게 통과하기 위해 위험속도에서의 진동을 억제하여야 하고, 운전 가능한 회전수를 증가시키기 위해서 로터 시스템의 동적 해석이 필요하다.(중략)

• Journal of IKEEE
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• v.24 no.1
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• pp.33-39
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• 2020

In this paper, we propose the design technique of the vehicle's load weight measuring system using tire pressure, which is one of the physical elements of tires. The proposed technique consists of four processes: noise correction by load and vibration, gas flow correction, data mixer and weight conversion. Noise correction by load and vibration eliminates noise that increases the tire's internal pressure due to external shocks and vibrations produced by the vehicle while it is in motion. In the gas flow correction process, the noise of the internal pressure of the tire is increased due to the temperature rise of the ground with respect to the data obtained through the noise correction process due to the load and vibration. In the data mixer process, the load and pressure on the tolerances the empty, median and the full load are classified according to the change in pressure of the tire that is delivered perpendicular to the tire in the event of cargo. In the weight conversion process, weight is expressed by weight through weight conversion algorithms using noise correction results by load and vibration and gas flow correction. The weight conversion algorithm calculates the weight conversion factor, which is the slope of the linear function with respect to the load and pressure change, and converts the weight. In order to evaluate the accuracy of the loading weight measurement system of the vehicle using the tire pneumatic system technique proposed in this paper, we propose the design technique of the vehicle's load weight measuring system using tire pressure, which is one of the physical elements of tires.. Noise correction results by load and vibration and gas flow data correction results showed reliable results. In addition, repeated weight precision test showed better weight accuracy than the standard value of 90% of domestic companies.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.3
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• pp.9-16
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• 2016

An experimental study was performed to investigate the combustion characteristics of the liquid hydrocarbon fuel atomized by an ultrasonic oscillator. Configuration of the flame was caught by the high-speed camera, and images were analyzed in detail through a post-processing. In addition, the fuel consumption was measured using the balance during the combustion reaction. As a result, the consumption of atomized fuel increased with the increasing flow-rate of carrier-gas, but any correlation between the air/fuel ratio and carrier-gas flow-rate was not found. The variation of flame area was dependent on the fuel consumption and input power of the ultrasonic oscillator. FFT (Fast Fourier Transform) analyses using the flame area were conducted in order to discuss flame flickering.

• Journal of the Korea Institute of Military Science and Technology
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• v.24 no.3
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• pp.255-263
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• 2021

This paper investigates numerically the effect of rotor hub vibratory load components on the airframe vibration responses of high-speed compound unmanned rotorcraft (HCUR) using a lift-offset coaxial rotor, wings, and two propellers. The rotor hub vibratory loads are predicted using a rotorcraft comprehensive analysis code, CAMRAD II, and the airframe vibration responses are calculated by a finite element analysis software, MSC.NASTRAN. It is shown that the vibratory hub pitch moment of a lift-offset coaxial rotor is the most dominant component for both the longitudinal and vertical vibration responses at four specified locations of the airframe.

• Journal of the Korean Chemical Society
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• v.54 no.6
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• pp.799-808
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• 2010

In this study, we conducted a textbook analysis and a conceptual test in order to investigate misconceptions of preservice chemistry teachers in understanding motions of molecular gases. As a result, we found out that many of the general chemistry textbooks not only introduce motions of molecular gases by explaining basic conceptions and using simple models, but also omit the explanation on center of mass when dealing with rotational motion. The physical chemistry textbooks, however, mainly approach motions of molecular gases in terms of spectroscopy and use various models to explain more intensified concepts, referring the center of mass in rotational motions. Meanwhile, pre-service chemistry teachers' confidence and understanding in the motions of molecular gases were very low and pre-service teachers also had many misconceptions about them. We believe this is because they had a tendency to depend largely on their intuition based on the pre-conceptions and the visual materials in the textbooks.

• Proceeding of EDISON Challenge
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• 2013.04a
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• pp.387-392
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• 2013

본 연구에서는 천음속 전투기 무장창 내부의 압력 진동을 제어하기 위해 F-111의 무장창을 2차원 공동(Cavity)으로 모델링하고, EDISON_전산열유체 시스템을 활용하여 공동의 형상 변화에 따라 발생하는 유동 특성을 분석하였다. 최근의 전투기들은 항력 감소와 스텔스 기능을 위해 무기를 기체 안에 내장하는데, 덮개를 열 때 발생하는 공동 형상에 의해 강한 압력 진동이 유발된다. 이러한 진동은 무장창과 주변 기계 장치에 구조적 진동을 일으키고 고장 또는 파괴를 유발하므로, 근본적인 해결책이 필요한 중요한 문제이다. 본 연구에서는 진동의 원인이 되는 전단층(Shear layer) 불안정성을 해결하기 위해 기존에 연구된 형상(Leading edge extension 및 Ramp)과 본 연구에서 새로 제안한 Ramp extension을 적용해 보았다. 그 결과 압력 진동의 원인이 되는 유동 특성이 줄어들고 압력 진동 역시 감소했음을 관찰할 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.89-94
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• 2010

Fuselage propellant feeding system should supply propellants to engine with required flow rate, temperature and pressure. Propellant vibration in engine and feeding line changes feeding characteristics, and frequently inhibits to satisfy the required feeding requirements. Sloshing and POGO vibration are known to be the major vibration phenomena. Concerning sloshing and POGO, vehicle control and structural dynamics aspects are extensively studied, whereas, its effect on propellant feeding performance is not clearly understood. This paper focuses on the deviation of required feeding performance due to propellant vibration. Overall characteristics of propellant vibration and its effect on propellant supply to engine are reviewed and control mechanism for suppressing vibration is introduced.