• The Transactions of The Korean Institute of Electrical Engineers
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• v.59 no.1
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• pp.70-75
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• 2010

The objective of this paper is to propose a new velocity measurement method for an electro-mechanical fin actuator. The model of the electro-mechanical fin actuator includes uncertainties such as unknown disturbances and parameter variations in flight condition. So, an electro-mechanical fin actuator system needs robust control algorithm which requires not only position information but also velocity information. Usually, analog tachometers have been used for velocity feedback in an electro-mechanical fin actuator. However, using these types of sensors have problems such as the cost, space, and malfunction. These problems lead to propose a new velocity measurement method using linear type Hall-effect sensor. In order to verify the proposed method, several experiments are performed using Model Following Sliding Mode Controller(MFSMC). It is shown that the MFSMC with a new velocity measurement method using linear type Hall-effect sensor can satisfy the requirements without using of velocity sensor.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2003.05e
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• pp.96-99
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• 2003

In this dissertation the results of the combined experimental and theoretical studies designed to understand and predict the spatial growth and transport coefficients for electrons in $SF_6$ and $SF_6$-Ar mixtures have described. The transport coefficients for electrons in (0.1[%])$SF_6$-Ar, (0.5[%])$SF_6$-Ar, (1.0[%])$SF_6$-Ar, (3.0[%])$SF_6$-Ar and (5.0[%])$SF_6$-Ar mixtures were measured by time-of-flight method, and the electron energy distribution function and the parameters of the velocity and the diffusion were determined by the variation of the collision cross-sections with energy.

• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
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• 2005.05a
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• pp.342-345
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• 2005

This paper describes the electron energy distribution function characteristics in $SF_6-He$ gas calculated for range of E/N values from $50{\sim}700[Td]$ by the Monte Carlo simulation(MCS) and Boltzmann equation(BE) method using a set of electron collision cross sections determined by the authors and the values of electron swarm parameters are obtained by time of flight(TOF) method. The results gained that the values of the electron swarm parameters such as the electron drift velocity, the electron ionization or attachment coefficients, longitudinal and transverse diffusion coefficients agree with the experimental and theoretical for a range of E/N. The results of Boltzmann equation and Monte carlo simulation have been compared with experimental data by Pollock, Ohmori, cottrell and Walker.

• The Transactions of the Korean Institute of Electrical Engineers P
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• v.64 no.3
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• pp.125-129
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• 2015

Energy distribution function for electrons in SF6-Ar mixtures gas used by MCS-BEq algorithm has been analysed over the E/N range 30~300[Td] by a two term Boltzmann equation and a Monte Carlo Simulation using a set of electron cross sections determined by other authors experimentally the electron swarm parameters for 0.2[%] and 0.5[%] $SF_6-Ar$ mixtures were measured by time-of-flight(TOF) method, The results show that the deduced longitudinal diffusion coefficients and transverse diffusion coefficients agree reasonably well with theoretical for a rang of E/N values. The results obtained from Boltzmann equation method and Monte Carlo simulation have been compared with present and previously obtained data and respective set of electron collision cross sections of the molecules.

• The Transactions of the Korean Institute of Electrical Engineers P
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• v.59 no.2
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• pp.146-150
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• 2010

Distribution Function and Drift velocities for electrons in $SF_6$-Ar mixtures gases used by MCS-BEq algorithm has been analysed over the E/N range 30~300[Td] by a two term Boltzmann equation and by a Monte Carlo simulation using a set of electron cross sections determined by other authors, experimentally the electron swarm parameters for 0.2[%] and 0.5[%] $SF_6$-Ar mixtures were measured by time-of-flight method. The results obtained in this work will provide valuable information on the fundamental behaviors of electrons in weakly ionized gases and the role of electron attachment in the choice of better gases and unitary gas dielectrics or electro negative components in dielectric gas mixtures. The results show that the deduced electron drift velocities agree reasonably well with theoretical for a rang of E/N values.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.9 no.2
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• pp.20-25
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• 2010

A camera module is supported by a gimbal structure in collection equipment of image information. During flight, the gimbal system undergoes serious accelerations with wide frequencies. To get the correct images, the camera module must be stably vibrated under these conditions. If natural frequency unfortunately exists in a exciting frequency range, resonance occurs there. Hence, harmonic responses analysis is needed to know correct vibration characteristic of the gimbal system. Finite element analysis was performed to get an acceleration of the gimbal system by mode superposition after extracting mode shapes and natural frequencies. Considering damping ratio of 2%, the reponses of gimbal structure were calculated from excitations with a design frequency band. As results, a maximum acceleration transmissibility, which is the ratio of response to excitation, was obtained and it can be used to design the gimbal structure effectively.

• Proceedings of the Korean Society of Machine Tool Engineers Conference
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• 2001.10a
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• pp.292-297
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• 2001

Twin screw extruders are the heart of the polymer processing industry. They are used at some stage in nearly all polymer processing operations. This paper is concerned with the basic elements of the extruder design. The proper design of the geometry of the extruder screw is of crucial importance to the proper functioning of the extruder. If the material transport instabilities occur as a result of improper screw geometry, even the most sophisticated computerized control system cannot solve the problem. For this purpose, a characteristic design on flights shape of the extruder screw. This paper presents cross section designs of a closely intermeshing twin screw extruder with double-flighted screw elements, and channel depth characteristics for a double flighted corotating self-wiping twin screw extruder.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.60 no.5
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• pp.1036-1042
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• 2011

This paper presents an algorithm that conducts automatic memory scrubbing operated by dedicated hardwares. The proposed algorithm is designed so that it can scrub entire memory in a given scrub period, while minimally affecting the execution of flight softwares. The scrub controller is constructed in a form of state machines, which have two execution modes - normal mode and burst mode. The deadline event generator and period tick generator are designed in a separate way to support the behavior of the scrub controller. The proposed controller is implemented in VHDL code to validate its applicability. A simple version of the controller is also applied to mass memory modules used in STSAT-3.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2011.07a
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• pp.373-375
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• 2011

최근 들어, Time-of-Flight (TOF) 방식의 깊이 센서가 컴퓨터 비전이나 영상처리분야 등의 연구에서 다양하게 활용되고 있다. TOF 방식의 깊이 센서는 실시간으로 정확한 깊이 정보를 획득할 수 있는 장점이 있는 반면, 해상도가 낮고 센서의 광학적 특성으로 인해 노이즈가 발생한다는 단점이 있다. 본 논문에서는 이러한 깊이 센서의 단점을 극복하고 고품질의 다시점 영상 합성을 위해 기존 깊이 센서에 여러 대의 Charge-coupled Device (CCD) 카메라를 결합하여 시점 간 일관성 있는 고해상도의 깊이 영상을 획득하는 기술을 제안한다. 한정되어 있는 시점의 영상을 이용하여 다시점 영상을 합성할 때, 각 시점에 해당하는 깊이 영상의 정확도에 따라 합성되는 영상의 품질이 결정된다. 따라서 보유 시점에 해당하는 깊이 영상 간의 일관성이 유지되고 객체의 경계가 정확히 보존되어야만 생성되는 임의 시점 영상의 품질이 보장될 수 있다. 이에, 본 논문에서는 Joint Bilateral Upsampling (JBU)을 기반으로 시점 간 일관성을 고려한 깊이 영상의 해상도 개선 기술을 제안하고 이를 통해 다시점 영상 합성 결과의 품질을 향상시킨다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.351-354
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• 2006

In the present work, performance analysis of fuel feed and transfer system for Smart UAV was conducted. For the fuel feed system, it was verified that minimum and maximum pressure requirements at the fuel inlet of engine were satisfied. For the fuel transfer system, design variables of jet pump were derived and performance was verified for the maximum acceleration flight condition by using ESDU design guide and flowmaster code.