• Proceedings of the Korean Vacuum Society Conference
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• 2010.08a
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• pp.129-129
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• 2010

플라즈마 처리를 통하여 수직 합성된 다중벽 탄소나노튜브가 원뿔형 다발이 될 수 있으며 원뿔형 탄소나노튜브 다발은 기존의 구조적, 기계적 성질의 향상과 더불어 향상된 전계방출 능력을 가질 것으로 기대되어 이를 X-선원, 전계방출디스플레이(FED), 유기발광다이오드(OLED) 백라이트 등의 전자빔 원으로 적용하기 위한 연구가 진행되고 있다. 원뿔형 탄소나노튜브 다발의 형상 제어를 통하여 전계방출특성을 향상시킬 수 있으며 이를 위해 원뿔형 탄소나노튜브 다발이 생성되는 메커니즘과 조사되는 플라즈마의 역할에 대해서 이해하는 것이 중요하다. 본 연구에서는 플라즈마 생성부와 조사부를 분리한 유도결합형 플라즈마 원을 사용하여 입사되는 이온의 에너지, 조사량, 입자 종을 독립적으로 제어하였고 이를 통하여 원뿔형 탄소나노튜브 다발이 형성되는 메커니즘과 플라즈마의 역할을 밝혀내었다. 알곤 및 수소 플라즈마 처리에서는 원뿔형 탄소나노튜브 다발이 형성되지 않았으나 질소 및 산소 플라즈마 처리에서는 원뿔형 탄소나노튜브 다발이 형성되었다. 특히 산소 플라즈마 처리가 원뿔형 탄소나노튜브 다발 형성에 효과적이었다. 원뿔형 탄소나노튜브 다발의 형성 메커니즘은 탄소나노튜브의 분극과 쉬스 전기장의 상호작용을 이용한 모델을 사용하여 설명하였다. 질소 및 산소 플라즈마 처리에서는 탄소나노튜브 끝단에 생성되는 C-N, C-O 결합에 의해 향상된 유도 쌍극자와 쉬스 전기장에 의해 탄소나노튜브 끝단이 모여 원뿔형 탄소나노튜브 다발이 생성됨을 밝혀내었다. 산소 플라즈마 처리에서 입사되는 이온의 에너지 조절에 의한 쉬스 전기장 조절과 조사량 조절을 독립적으로 수행하여 원뿔형 탄소나노튜브 다발의 직경 및 높이가 쉬스 전기장 및 조사량에 따라 조절 가능함을 보였다. 이로부터 입사되는 이온의 입자 종, 쉬스 전기장 및 조사량 조절 등의 플라즈마 인자 조절을 통하여 원뿔형 탄소나노튜브 다발의 형상 제어가 가능함을 보였다. 탄소나노튜브의 형상 제어와 더불어 세슘 입자 삽입을 통한 탄소나노튜브의 일함수 감소를 통하여 향상된 전계 방출 특성을 갖는 탄소나노튜브 팁의 제조 가능성을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.2
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• pp.22-31
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• 2005

A design study was conducted for a new concept aircraft(Canard Rotor/Wing: CRW) that has the capability of dual mode flight, a rotorcraft and a fixed wing mode. The CRW can show a vertical take off/landing and a high speed/efficiency cruise performance simultaneously. It is not surprising to develop a new sizing code for this class of aircraft because conventional sizing codes developed solely for either the rotary wing or the fixed wing aircraft are not adequate to design a dual mode aircraft operated both by the rotary wing through tip jet effux and the fixed wing lift. Thus, a new design code was developed based on the conventional sizing code by adding some features including rotor performance, duct flow, and engine flow analysis, hence could eventually predict the performance of reaction driven rotor, the flight performance and the flight characteristics. The various design parameters were investigated to find their influences on the flight performance then, a small UAV(Unmanned Aircraft Vehicle) of 1500 lbs class was optimally designed to have minimum weight using the developed sizing code.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.8
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• pp.763-771
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• 2011

An optimization procedure for the design of a ventilation axial-flow fan is presented in this paper. Flow analyses of the preliminary fan are performed by solving three-dimensional Reynolds-averaged Navier-Stokes equations via a finite-volume solver with the shear-stress transport turbulence model as a turbulence closure. Three variables, the hub-to-tip ratio and the stagger angles at the mid and tip spans, are selected for the optimization. The Latin-hypercube sampling method as a design-of-experiments technique is used to generate twenty-five design points within the design space. and the weighted average surrogate models, WTA1, WTA2, and WTA3, are applied for find optimal designs. The results show that the efficiency is considerably enhanced.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.11
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• pp.1721-1725
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• 2010

This paper reports the fabrication of geometry-controlled carbon microneedles by a backside exposure method and pyrolysis. The SU-8 microneedles are a polymer precursor in a carbonization process, which geometries such as base diameter, spacing, and aspect ratio can be controlled in a photolithography step. Using this fabrication method, highly reproducible carbon microneedles, which have high aspect ratios of more than 10 and very sharp nanotips, can be realized. The quartz surface with carbon microneedles becomes very hydrophilic and its wettability is adjusted by carrying out the silane treatment. In the carbon microneedle array ($3\;{\mu}m{\times}3\;{\mu}m$), the contact angle is extremly enhanced (${\sim}180^{\circ}$); this will be advantageous in developing low-drag microfluidics and labs-on-a-chip as well as in other bio-applications.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.8
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• pp.875-880
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• 2014

Recently, three-dimensional scaffolds and nanofibers are being developed for bone tissue regeneration. In this study, we fabricated a hybrid scaffold using a nano-micro precision deposition system. The fabrication process involved the application of the solid freeform fabrication (SFF) technology and electrospinning. The hybrid scaffolds were combined using micro scaffolds and nanofibers. The nanofibers were deposited on each layer of the micro scaffolding using the electrospinning process. The micro scaffolds were fabricated using the SFF technology at a temperature of $100^{\circ}C$, pressure of 650 kPa, and scan velocity of 250 mm/s. Nanofiber fabrication was conducted by means of electrospinning using the flow rate, solution concentration, distance from the tip to the collector (TCD), and voltage. The nanofibers were fabricated using a flow rate of 0.1 ml/min, voltage of 5 kV, TCD of 1 mm, and 10 wt% of solution concentration. MG-63 cells were seeded into the hybrid scaffold for the purpose of its evaluation.

• Journal of Energy Engineering
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• v.12 no.3
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• pp.197-206
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• 2003

A numerical analysis of the pulse-jet cleaning characteristics in a porous ceramic candle filter system was performed. To obtain the detailed velocity and pressure distribution during the cleaning process in a porous filter system, the axi-symmetric compressible Navier-Stokes equations including energy conservation equation were solved by using the FLUENT code which adopts FVM (Finite Volume Method). The effects of pulse cleaning nozzle diameter, nozzle tip position, permeability of a porous ceramic candle filter, diffuser throat diameter, and cleaning pressure on the cleaning flow characteristics were investigated extensively.

• Journal of computational fluids engineering
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• v.17 no.2
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• pp.1-10
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• 2012

This paper presents the numerical simulation results of heat transfer and friction loss for a rotating two-pass duct with the airfoil-guide vanes in the turning region. The Kriging model is used as an optimization technique with Reynolds-averaged Navier-Stokes analysis of flow field and heat transfer with shear stress transport turbulent model. To improve the heat transfer performance, angle and location of the airfoil-guide vanes have been selected as design variables. The optimization problem has been defined as a minimization of the objective function, which is defined as a linear combination of heat transfer related term and friction loss related term with a weight factor. The airfoil-guide vanes in the turning region keep the high level of heat transfer while the friction loss has a low value. By comparing the presence or absence of airfoil-guide vanes, it is shown that the airfoil-guide vanes exhibited the best heat transfer performance to improve the blade cooling except the first passage.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.4
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• pp.19-26
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• 2003

In this paper, the result of the conceptual study of a tipjet driven propulsion system is presented. The concept of a tipjet driven propulsion system is to employ tipjet as power source to drive a rotor Because the vehicle is supposed to takeoff and land vertically, a rotor system, which has tipjet nozzles, is adopted to fly like a helicopter. Exhaust gas, which is generated by an engine, Passes through an internal duct system and divided into four blade ducts. The design code is consists of two parts, engine model and internal duct model. Inside a rotating duct, compressible flow is affected by two additional force terms, centrifugal force and coriolis force and they govern the performance in rotary mode, The intention of this paper is to address the issues associated with sizing and optimizing configurations of a tipjet driven propulsion system especially in rotary wing mode.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.297-301
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• 2007

The blades of supersonic turbines with low aspect ratio are usually designed to have the same cross sectional shape in radial direction. The profile diameter definition of turbines may lead to produce unintended flow passage area variations resulting performance degradation. In this paper, the effects of profile diameter definition on the supersonic impulse turbine performance have been investigated. Computational results of three different profile diameters are compared. It has been found that flow passage area variation can be achieved according to designer's intention when blade profile is defined at rotor tip diameter. Furthermore, the turbine blade profile defined at rotor tip showed better performance than the others.

• Transactions of the Korean Society of Machine Tool Engineers
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• v.11 no.6
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• pp.1-9
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• 2002

This study describes the geometric characteristics and the 5-axis machining method in order to make end mill cutter coming with insert tips. End mill geometry is consisted of flute part and insert tip part. Flute part modeled by using ruled surfaces with constant helix angle, and insert tip part modeled by rectangular planes containing tapped hole of specified direction in its center. In this study, the modeled insert tip part considered both of a radial rake angle and a axial rake angle, because they were important cutting conditions. In order to machining the virtual end mill defined from geometric characteristics, we programmed a special software to machining the end mill considered in this study. This software can generate NC-codes about following processes, end milling or ball end milling of flute part end milling of rectangular plane, centering of hole, drilling of hole, and tapping of hole. Ant sampled end mills were modeled and machined on 5-axis CNC machining center with two index tables. Since machined end mills were very agreeable to designed end mills, we saw that the method proposed in this study can be very useful for manufacturing of end mill body with insert tip.