• 전기학회논문지
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• 제57권3호
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• pp.403-408
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• 2008

The gyroscope is the sensor for detecting the rotation in inertial reference frame and constitute the navigation system together an accelerometer. As the inertial reference equipment for attitude determination and control in the satellite, the mechanical gyroscope has been used but it bring the disturbance for mass unbalance so the disturbance give a bad influence to the observation satellite mission because the mechanical gyroscope has the rotation parts. During the launch. The mechanical gyroscope is weak in vibration, shock and has the defect of narrow operating temperature range so it need the special design in integration. Recently the low orbit observation satellite for seeking the high pointing accuracy of image camera payload accept the FOG(Fiber Optic Gyro) or RLG(Ring Laser Gyro) for the attitude determination and control. The Ring Laser Gyro makes use of the Sanac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. It need the 1000V DC to create the He-Ne plasma in discharge tube. In this paper, the design process of the High Voltage Power Supply for RLG(Ring Laser Gyroscope) is described. The specification for High Voltage Power Supply (HVPS) is proposed. Also, The analysis of flyback converter topology is explained. The Design for the HVPS is composed of the inverter circuit, feedback control circuit, high frequency switching transformer design and voltage doubler circuit.

• 대한기계학회논문집B
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• 제29권10호
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• pp.1101-1110
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• 2005

In this paper we present the numerical results of the behavior of the horizontal vortex generated by ejecting a liquid vertically upward from an orifice into the bulk fluid above the orifice. The numerical calculation has been performed for the axi-symmetric Navier-Stokes equation. A simple flow-visualization experiment was also conducted to qualitatively verify the numerical solutions. Three cases of the flow configurations studied in this paper are; firstly, the vortex was generated without any background rotation, secondly, the vortex was made under a full background rotation, and thirdly, the vortex was made during the spin-up process such that only the region adjacent to the side wall was set into motion viewed in the inertial frame of reference. It was shown that the swirl flow at the inlet boundary affects considerably the formation and development of the vortex for the second case. In the third case, it was remarkable to see that the vortex cannot penetrate into the region near to the side wall of the tank, because of the strong swirl flow and corresponding high pressure gradient in the region.

• Journal of Electrical Engineering and Technology
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• 제12권4호
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• pp.1675-1682
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• 2017

This paper deals with three dimensional orientation estimation algorithm for an attitude and heading reference system (AHRS) based on nine-axis inertial/magnetic sensor signals. In terms of the orientation estimation based on the use of a Kalman filter (KF), the quaternion is arguably the most popular orientation representation. However, one critical drawback in the quaternion representation is that undesirable magnetic disturbances affect not only yaw estimation but also roll and pitch estimations. In this paper, a sequential direction cosine matrix-based orientation KF for AHRS has been presented. The proposed algorithm uses two linear KFs, consisting of an attitude KF followed by a heading KF. In the latter, the direction of the local magnetic field vector is projected onto the heading axis of the inertial frame by considering the dip angle, which can be determined after the attitude KF. Owing to the sequential KF structure, the effects of even extreme magnetic disturbances are limited to the roll and pitch estimations, without any additional decoupling process. This overcomes an inherent issue in quaternion-based estimation algorithms. Validation test results show that the proposed method outperforms other comparison methods in terms of the yaw estimation accuracy during perturbations and in terms of the recovery speed.

• 한국항공우주학회지
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• 제45권8호
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• pp.671-677
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• 2017

본 논문은 관성항법시스템(Inertial Navigation System)과 비전 센서(Vision Sensor)를 활용한 통합 항법시스템의 성능 향상을 위한 INS/멀티비전 통합항법 시스템을 제시하였다. 기존의 단일 센서나 스테레오 비전(Stereo vision)을 활용한 경우 측정되는 랜드마크의 수가 적을 경우 필터가 발산하는 문제가 발생할 수 있다. 이러한 문제를 해결하기 위해 본 논문에서는 3개의 비전 센서를 동체를 기준으로 $0^{\circ}$, $120^{\circ}$, $-120^{\circ}$으로 설치하여 단일 센서로 사용되는 경우보다 성능이 향상됨을 수치 시뮬레이션을 통하여 검증하였다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2008년도 제39회 하계학술대회
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• pp.1488-1490
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• 2008

The gyroscope is the sensor for detecting the rotation in inertial reference frame and constitute the navigation system together an accelerometer. As the inertial reference equipment for attitude determination and control in the satellite, the mechanical gyroscope has been used but it bring the disturbance for mass unbalance so the disturbance give a bad influence to the observation satellite mission because the mechanical gyroscope has the rotation parts. During the launch, The mechanical gyroscope is weak in vibration, shock and has the defect of narrow operating temperature range so it need the special design in integration. Recently the low orbit observation satellite for seeking the high pointing accuracy of image camera payload accept the FOG(Fiber Optic Gyro) or RLG(Ring Laser Gyro) for the attitude determination and control. The Ring Laser Gyro makes use of the Sanac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. It need the 1000V DC to create the He-Ne plasma in discharge tube. In this paper, the design process of the High Voltage Power Supply for RLG(Ring Laser Gyroscope) is described. The specification for High Voltage Power Supply(HVPS) is proposed. Also, The analysis of flyback converter topology is explained. The Design for the HVPS is composed of the inverter circuit, feedback control circuit, high frequency switching transformer design and voltage doubler circuit.

• 한국항공우주학회지
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• 제44권4호
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• pp.308-315
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• 2016

본 논문은 관성 항법 시스템(Inertial Navigation System)을 활용한 자세 및 방향 결정시스템(Attitude & Heading Reference System)의 성능을 향상시키기 위한 새로운 기법인, 순차적 측정 오차 공분산(Sequential Measurement Noise Covariance) 기법을 제시하였다. 관성 센서는 시간이 지남에 따라 발생하는 적분오차와 진동이나 가속구간과 같은 외란이 가해 졌을 때 성능이 저하된다는 단점이 있다. 특히, 저가의 관성 센서의 경우 이러한 현상이 더욱 두드러지게 나타난다. 이를 극복하기 위한 알고리즘들은 많이 존재한다. 하지만 가장 일반적으로 사용되는 확장 칼만 필터의 경우 가속도계를 사용할 때 측정값(Measurement)이 일정 범위를 넘어가면 센서값을 배제하는 방법을 사용한다. 본 논문에서 제안하는 기법은 범위를 설정하지 않고 과거의 데이터를 순차적으로 활용하여 측정값의 가중치를 변화하는 기법이다. 최종적으로 제안된 기법을 수치 시뮬레이션을 통해 검증하였다.

• 한국소음진동공학회논문집
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• 제26권6_spc호
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• pp.644-650
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• 2016

Track maintenance works based on track geometry recordings are essential to enhance the safety and comfort of railway transportation. Usually, the track irregularity has been measured by a special inspection trains which all were imported from abroad. Because the inspection train speed is limited under 160 km/h, it takes a long time to inspect railways and there is difficulty in daytime operation. To solve this problem, we started to develop a track geometry measuring system (TGMS) with measurement speed up to 300 km/h which can be installed in commercial vehicles such as HEMU-430X. In this paper, we introduce a newly developed inertial TGMS and propose two inertial navigation system (INS) algorithms (method A, B) for measuring track geometry. In order to investigate advantage and disadvantage of each algorithm, we performed vibration test of the TGMS, which was simulated by 6-axis shaking table. Through the vibration test, we analyzed the influence of vehicle vibration on the TGMS which will be installed on bogie frame. To the vibration test, two methods satisfied the required accuracy of track geometry measurement under the level of the actual vehicle vibration of HEMU-430X train. Theoretically, method A is sensitive to vehicle vibration than method B. However, HEMU-430X's bogie vibration frequency range is out of interest range of measurement system. Therefore, method A can also apply the HEMU-430X train.

• 한국항공우주학회지
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• 제31권8호
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• pp.19-26
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• 2003

비정상 Euler 방정식 틀에서 동안정 미계수의 정상 예측 방법을 제안하였다. 새로운 접근방법은 비정상 지배방정식을 수정하지 않고 정상 예측방법을 적용하도록 해 준다. 제안된 방법을 통해 lunar 코닝운동 및 나선운동을 사용하여 피치감쇠 계수 합과 개별 값을 계산하였다. ANSR 형상과 Basic Finner 형상에 대한 계산결과는 PNS 계산결과, 실험치, 그리고 비정상적 예측방법을 사용한 결과와 잘 일치하고, 직교좌표계에서 정상적 예측 방법이 피치감쇠 계수의 예측에 성공적으로 적용될 수 있음을 보여준다.

• 설비공학논문집
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• 제30권2호
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• pp.92-99
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• 2018

A numerical analysis of a compressor dehumidifier has been conducted focusing on the air side heat transfer, which is a part of a series research on the dehumidifier. The moving reference frame was applied to the fan modeling, and the porous model was used for the evaporator and condenser modeling. Curve fitting obtained the inertial and viscous resistances parameters to the results of the physical model of the unit cell with actual shape of a fin tube. The porous model was validated within a reasonable computation time for the range of practical inlet velocity of a dehumidifier. A parametric study has been conducted for fin number, fan speed (i.e., air flow rate), and evaporator/condenser tube arrangement. ANOVA analysis showed the dependency of each parameter on the velocity and temperature uniformity, which are desirable for high performance of the dehumidifier.

• 한국전산구조공학회논문집
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• 제21권5호
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• pp.475-482
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• 2008

본 논문은 로터 시스템의 디스크 회전운동을 표현하는데 있어 운동방정식을 통합하는 과정에서 기존 연구자들이 채택한 오일러 각 사용법이 일관성이 없음을 지적하였다. 기존 연구자들은 오일러 각 순서가 달라서 속도와 운동에너지도 달리 산정하였음은 물론, 운동방정식은 오직 선형 시스템만 취급해 왔다 이러한 오일러 각 사용법의 단점을 극복하기 위하여 회전운동을 더욱 단순하게 매개화할 수 있는 4원법(quaternion)과 구 좌표계를 적용하여 비선형 시스템을 도출하였다. 이를 바탕으로 수치해석을 통하여 기존 방법과 비교하여 제안한 방법의 신뢰성과 우수성을 보였다.