• The Transactions of the Korean Institute of Power Electronics
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• v.9 no.6
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• pp.553-559
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• 2004

The servo motor is used for the driving power source of the conventional linear conveyor system. The mechanical power transfer system is needed for converting the circular to the linear operation. But this system causes some problems of position error, the necessity of the periodical maintenance. In this paper the study on application of transverse flux linear motor(TFLM) is carried out for the indexer system of LCD processing because TFLM has much thrust per a volume than the conventional motor. TFLM is suitable system for the indexer system because of capacity of acceleration, maximum speed and precision of the position, etc.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.12
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• pp.1097-1106
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• 2011

Unsteady numerical analysis was performed to simulate air-launched missiles from a complete helicopter in hover by using an unstructured overset mesh flow solver coupled with a module of six degree-of-freedom motion of equations. The unsteady computations have been performed to obtain flow fields around the complete helicopter including main rotor, tail rotor, and fuselage equipped with multiple missiles, and six-DOF simulation has been performed to predict the behavior of the air-launched missile. The effects of the launching position and the missile thrust on the trajectory of the missile were investigated as well as the aerodynamic interference of the air-launched missile under the unsteady downwash produced by main rotor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.146-149
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• 2006

Spray characteristics of an injector employed in mono-propellant hydrazine thrusters were investigated by PIV(particle image velocimetry) and LDA/PDA(laser/phase Doppler anemometry) techniques. The instanteneous plane image data captured by PIV measurement were examined in order to judge a pass-fail criteria of spray injection performance according to the specific pressure supplied. LDA/PDA technique were also applied to measure the velocity and droplet size of spray were not obtained from PIV measurement. The objective of this experimental study was the clear understanding of spray characteristics as well as the derivation of injector performance to understand clearly the spray characteristics by comparing the both results.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.1
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• pp.50-60
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• 2015

A propulsion system of a satellite provides a necessary thrust to reach to the final orbit after a separation from a launch vehicle. Also, it supplies pulse moments to maintain the satellite in a mission orbit and for its attitude controls during a mission life time. The present study investigates the development trend of bipropellant rocket engines for an orbit transfer and an attitude control of a satellite using monomethylhydrazine and hydrazine for fuel and dinitrogen tetroxide for oxidizer to derive fundamental specifications which are necessary for domestic development researches. Also, their major performance characteristics are summarized.

• The Journal of Korean Institute for Practical Engineering Education
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• v.4 no.1
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• pp.57-64
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• 2012

For design of a electrical Machine it is used conventional design methode to determine size with considering of magnetical circuit and windings. After this process, Flux density and Torque are calculated with FEM program. But most electrical machines are complicated in their configuration, therefore it is not easy to understand the design process and analyzing methode. We need to develop a educational material. In this paper using Linear force motor, which is relatively not complicated in their configuration and easy to understand the relationship between electro magnetics and force, will be explained the design process and calculating process with Finite element methode. And with FEM program will be calculated and illustrated flux density in each part and Force of the Linear force motor easy to understand.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.275-281
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• 2007

For a cooling performance research of the combustor operated in a extreme environment of a high temperature and high pressure, we accomplished a cooling performance analysis. Generally a heat transfer characteristic in cooling passage is known well experimentally and theoretically, however heat flux in the combustion chamber isn't. In this study, fluid flow combined with heat transfer analysis is accomplished about a combustor nozzle. We tried to analyze the cooling performance with a heat transfer characteristic of a gas and coolant side in the view point of quantity on the mass flow rate to be supplied to the cooling channel. And finally, evaluation on the thermal safety of nozzle wall material was accomplished.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1057-1058
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• 2008

철도차량용 선형추진시스템에 있어서, 지상레일에 설치되는 선형유도전동기의 2차측의 리액션플레이트의 시공 공차에 의해서 발생되는 1차측과의 공극의 변화는 추진 시스템의 운행 시 승차감과 기기효율을 떨어뜨리는 결과를 초래하기 때문에 선형유도전동기의 균일 공극 운전은 추진 시스템의 효율을 증가시킬 수 있는 중요한 사항이다. 또한 경사구간에서의 선형유도전동기의 공극길이 조절을 통해서 선형유도 전동기의 용량 변경 없이 추력을 증가시키는 것이 가능하다. 따라서 본 논문에서는 선형유도전동기의 공극 길이를 제어할 수 있으며, 공극 길이제어를 통하여 추진 시스템의 성능 변화를 살펴볼 수 있는 축소 모델선형유도전동기 성능시험기의 공극조절 시스템의 동적 모델링 및 특성 해석을 통하여 시스템을 구성하는 파라미터들의 특성 변화 분석 및 시스템 구현 가능성에 대한 연구를 수행하였다.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.87-95
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• 2007

The ocean and meteorological payloads of COMS are concerned to experience degration of image quality due to the disturbance induced by the motion of moving parts of the payloads. And thruster firings for stationkeeping and wheel offloading are expected to degrade the image quality of the optical payloads. In case of COMS, in order to keep the optical payload free from the mechanical interference from the other payload, the operation design approach has been taken. This paper introduces the operation design of COMS taken to avoid these problems. In order to meet users requirement by avoiding the degradation of image quality, the timeline of optical payloads and housekeeping are optimized, and operational constraints are applied to the mirror motion of the meteorological payload. This paper also introduces the results of time budget analysis performed to validate the operation design.

• Current Industrial and Technological Trends in Aerospace
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• v.5 no.2
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• pp.23-32
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• 2007

헬리콥터 주 로터 시스템은 헬리콥터 전체 성능을 좌우하고, 비행특성을 결정하는 핵심 구성품이다. 주 로터 시스템은 회전하면서 추력 및 조종력을 발생시키기 때문에 동적 밸런싱을 맞추는 것도 중요한 개발단계업무 중에 하나이다. 주 로터 시스템의 개발 과정에서 헬리콥터 비행시제 장착 전에 동적 밸런스 시험, 성능시험, 안정성 시험 등을 포함하는 훨시험(whirl test)을 수행하게 된다. 이 시험 수행을 위해 제작되는 시험장치가 훨타워(whirl tower)이다. 세계 유수 헬리콥터 회사들은 주 로터 훨시험을 위한 설비인 훨타워를 보유하고 있으며, 지속적으로 성능 개량 등을 통해 최신의 기술 및 장비를 적용하여 운영하고 있다. 본 논문에서는 대표적으로 사용되고 있는 해외 헬리콥터 회사들의 훨타워의 사례를 설명하고 설비의 기능을 기술함으로써 기술적 동향에 대하여 살펴보았다. 현재 한국형헬기개발사업(KHP)에서 구축중인 다목적 의 WTTF(whirl tower test facility) 요구조건 및 설계 현황에 대해서도 기술하였다. 당 연구원의 WTTF는 한국형기동헬기(KUH)의 주 로터 훨시험 및 내구성 시험을 위해 구축되고 있다. 본 시험설비는 연구개발용 시험과 양산용 시험을 모두 수행할 수 있도록 다목적으로 개발될 예정이다. 본 설비는 기존 해외 설비와는 차별화되어 다목적 시험을 할 수 있도록 설계가 진행중이며, 2008년12월에 구축 완료 예정이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.1-5
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• 2006

Birds and insect in nature morph their mean camberline shapes to obtain both lift and thrust simultaneously. Previous unsteady thin airfoil theories were derived mainly for a rigid flapping airfoil. An extended unsteady thin airfoil theory for a deformable airfoil is required to analyze the unsteady two-dimensional aerodynamic characteristics of a biomorphing wing. Theodorsen's approach is extended to calculate the unsteady aerodynamic characteristics of a biomorphing airfoil. The mean camberline of the airfoil is represented as a polynomial. The unsteady aerodynamic characteristics of the morphing airfoil are represented as noncirculatory and circulatory terms. Present theory can be applied to the unsteady aerodynamic analysis of a flapping biomorphing airfoil and the aeroelastic analysis of a morphing wing.