• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2002.11a
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• pp.105-109
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• 2002

최근 빈번하게 발생되고 있는 가스사고는 많은 인명과 재산상의 손실을 초래하고 있다. 특히 도시 가스 보다는 공기보다 비중이 큰 LP가스에 의한 사고가 많이 발생된다. 특히 최근에 발생한 인천 부평구의 LP가스 폭발사고는 사망6명, 부상21명 등 총 27명의 인명피해와 주택 붕괴 등 많은 재산상의 손실을 초래하였다. 또한 LP가스 용기는 용기자체가 자해나 위해의 수단으로 이용되기도 한다. 이에 따라 정부에서는 1998년 1월 10일 고압가스안전관리법 시행규칙을 개정하여 LP가스용기에 부착되어 사용되는 밸브를 과류차단형으로 의무화하여 가스사고예방을 위해 힘쓰고 있다.(중략)

• Journal of the Korean Society for Railway
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• v.6 no.2
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• pp.22-32
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• 2003

차륜없이 전자석에 의해 부상하고, 리니어모터에 의해 추진하는 시스템이다. HSST의 가장 큰 장점은, 접촉지짖에 의한 저소음 및 공기저항외에는 주행저항이 없기 때문에 고속주행이 가능하다. HSST도 당초에는 최고속도 200∼300km/h 정도의 시스템 HSST-200, HSST-300 타입을 목표로 개발을 진행해왔지만, 최근에는 급구배 및 급곡선 통과가 가능한 특성을 활용하여 도시내 교통을 대상으로 하는 최고속도 100km/h 정도의 시스템 HSST-100 타입 개발에도 주력함으로써 실용화에 달하고 있다. 경량전철로서의 취급하고 있는 시스템은 HSST-100 타입이다.(중략)

• Proceedings of the SAREK Conference
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• 2003.07a
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• pp.196-196
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• 2003

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 2001.06a
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• pp.236-242
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• 2001

In this paper the effect of bump compliance, load, and the number of pad on the lift-off speed is studied. When the load is greater and bump compliance lower, the shaft is lifted off at higher rotating speed. And when the load is applied near the center of pad, lift-off speed is lower. When the number of pad increases, the lift-off speed is higher. The lift-off characteristics can be used to lengthen the life time of the coating and design the rotating machinery supported by bump bearings.

• Proceedings of the KSME Conference
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• 2001.06c
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• pp.316-321
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• 2001

The optical storage device has recently experienced significant improvement, especially for the aspects of high capacity and fast transfer rate. However, it is necessary to study a new shape of air bearing surface for the rotary type actuator because the optical storage device has the lower access time than that of HDD (Hard Disk Drives). In this study, we proposed the air bearing shape by using SA (Simulated Annealing) algorithm which is very effective to achieve the global optimum instead of many local optimums. The objective of optimization is to minimize the deviation in flying height from a target value 100nm. In addition, the pitch and roll angle should be maintained within the operation limits.

• 한국전산유체공학회:학술대회논문집
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• 2004.03a
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• pp.196-201
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• 2004

Aerodynamic characteristics of three-dimensional wings in ground effect for Aero-levitation Electric Vehicle(AEV) are numerically investigated for various ground clearances and wing spans at the Reynolds number of $2\times10^6$. Numerical results show that a sizeable three-dimensional flow separation occurs with formation of an arch vortex at the junction of main and vertical wings, and that this is conjectured a primary cause for the high lift-to-drag(L/D) reduction rate of the main wing, when the wing span is decreased. Improvements on L/D ratios of the wings with small spans are pursued by breaking the coherence of superimposed adverse pressure gradients at the wing junction.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2006.10a
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• pp.359-360
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• 2006

• Journal of Institute of Control, Robotics and Systems
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• v.11 no.3
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• pp.246-253
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• 2005

An experimenal study on flight control of high-speed AEV(Aero-levitation Electric Vehicle) scale model in wind-tunnel is conducted. The AEV is to fly at very low altitude in predesigned track so that it is always under the wing-in-ground effect. The experiment is intended to fly the scale model to follow the predesigned altitude schedule while holding its attitude (pitch, roll, and yaw). Especially, the altitude changes for climb, cruise, and descent with constant pitch angle are most important maneuvers. The experiment shows that the required mission flights can be performed with appropriate sensors, processors, and actuators.

• 한국전산유체공학회:학술대회논문집
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• 2005.04a
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• pp.57-64
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• 2005

Aerodynamic characteristics of three-dimensional wings in ground effect for Aero-levitation Electric Vehicle(AEV) are numerically investigated for various fairing shapes at the junctions of 3D Wings. Numerical results show that a sizeable three-dimensional comer flow separation occurs with formation of an arch vortex at the junction of main and vertical wings, and also that this is predicted the main cause of the high lift-to-drag(L/D) reduction rate of the main wing. To avoid the comer flow separation, the main idea of this study is to reduce the cross section gradient of the comer flow tube near the trailing edge for various fairing shapes. Improvements on L/D ratios of the wings are pursued by breaking the coherence of superimposed adverse pressure gradients at the wing junction when the cross section gradient is changed slowly at the trailing edge.

• Proceedings of the KSME Conference
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• 2008.11a
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• pp.1244-1249
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• 2008

This paper shows a perfonnance analysis for pneumatic servo cylinder. The pistons without seal have partly cylindrical and conical shapes. 2 dimensional Reynolds equation and FD(finite differential) numerical techniques are utilized for the perfonnance analysis. The relationship among self-centering forces and leakage flows are investigated. Also, optimal design values for a servo cylinder are presented. A prototype of servo cylinder which had rod bearing with four pockets, five pockets, and six pockets was manufactured respectively.