• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.1
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• pp.8-15
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• 2004

Supersonic jets impinging on $60^{\cire}$ wedge were investigated to obtain fundamental design data for jet deflector It was of interest to study flow phenomena such as shock interaction and separation induced by shear layer. Experiments using supersonic cold flow system were conducted for Schlieren flow visualization and measurement of surface pressure. Numerical results were compared with the experimental results. The major parameters are underexpansion ratio, distance from nozzle to apex and design Mach number. Flow conditions were obtained for the wedge shock to attach on or detach from the wedge. The dominant feature of flow-field is shock pattern induced by the Interaction between the wedge shock and the barrel shock.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.6
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• pp.596-604
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• 2010

In order to investigate the operating conditions and major design parameters of a dual ramjet propulsion system, an theoretical analysis of ramjet and scramjet propulsion systems was performed. The performance characteristics of each engine are delivered by thermo-dynamical cycle analysis, considering loss effects in a real engine. The performance sensitivity analysis is conducted by investigating various performance parameters, such as an intake efficiency, combustor inlet Mach number, configuration of the combustor, fuel flow rate, and exhaust nozzle efficiency. Based on these analysis results, the processes of application to dual ramjet cycle engines are specified.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.125-129
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• 2006

In the present study, preliminary design and analysis of flow distribution for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.464-468
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• 2005

In the present study, preliminary design and performance analysis for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.

• Proceedings of the Korean Vacuum Society Conference
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• 2014.02a
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• pp.239.2-239.2
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• 2014

태양전지의 전면전극과 웨이퍼의 접촉저항은 태양전지의 효율을 저하시키는 원인이 된다. 전면전극과 웨이퍼의 접촉저항을 감소시키는 공정으로써 선택적 에미터 도핑이 널리 적용되고 있다. 선택적 에미터 도핑은 태양전지의 전면전극 하부에 고농도 도핑을 함으로써 전극과 웨이퍼의 접촉저항을 감소시켜 태양전지의 효율상승을 유도한다. 이러한 선택적 에미터 도핑은 주로 고가의 레이저 장비가 요구 되어 생산단가가 높으며 웨이퍼의 구조적 손상을 야기한다. 본 연구에서는 고가의 레이저 장비를 플라즈마 제트 장치로 대체함으로써 생산단가를 낮추고자 한다. 도펀트가 도포된 웨이퍼에 플라즈마 제트를 조사하면 플라즈마 전류 흐름에 의한 저항 열이 발생한다. 발생된 열에 의해 도펀트가 웨이퍼에 확산되어 도핑된다. 플라즈마 제트로 구성된 선택적 에미터 도핑 장비 개발을 위한 기초 특성을 조사한다. 플라즈마 제트의 전류량의 변화에 따른 웨이퍼의 온도 특성과 도포된 도펀트 용재의 인산 함유량에 따른 도핑 깊이를 조사한다. 또한 선택적 에미터 도핑의 생산성을 향상시키기 위해 다중 채널 플라즈마 제트 장치를 구성하여 특성을 조사한다. 각 채널의 플라즈마 제트의 선폭과 전류량이 적절한 균일도를 갖도록 한다. 도핑 프로파일은 이차 이온 질량분석법을 통해 분석한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.1
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• pp.38-43
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• 2006

In the present study, preliminary design and analysis for a jet pump, which is able to transfer fuel from the tank to the engine, were performed as an aerospace component technology development project. The jet pump is a core part, which is normally installed in the fuel tank, to supply the fuel from the tank to the engine feed pump, or to transfer the feed between tanks. In order to design preliminarily installed in the jet pump, equations for design were modelled using SIMULINK, and the design was carried out based on the simulation model.

• Proceedings of the Korean Vacuum Society Conference
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• 2013.02a
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• pp.554-554
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• 2013

대기압 제트 플라즈마를 저주파(수-수십 kHz) 전압에서 구동 시, 일반적으로 '스트리머(streamer)'혹은 '플라즈마 총알(plasma bullet)'로 불리는 현상이 특정 운전조건에서 관찰된다. 본 연구에서는 동일 구조의 Ta, Ti, stainless steel, brass, Cu, Ni 전극을 이용하여 전극물질에 따른 대기압 제트 플라즈마의 특성 변화를 분석하였다. 각각의 물질은 서로 다른 이차전자방출계수, 일함수, 전기전도도 등 고유한 성질이 다르기 때문에 이들 전극을 이용하여 발생시킨 제트 플라즈마 역시 다른 특성을 갖는다. Acton SpectroPro750 분광기를 이용하여 얻은 플라즈마 방출광스펙트럼으로부터 구한 전자 여기온도(Texc=680~720 K)와 OH의 분자 회전온도(Trot=350~380K)는 물질에 따라 큰 변화를 보이지 않았으나, 발생된 스트리머 거동에서 큰 차이를 확인하였다. ICCD 카메라를 이용한 시간 분해된 이미지에서 전극물질에 따른 첫 번째 스트리머의 발생시간 및 스트리머 속력, 두 번째 스트리머의 분리시간이 모두 다른 것을 확인하였다. 제일 차이가 심하게 나타나는 Ti과 Cu의 경우 첫 스트리머의 발생시간 차이는 약 $1{\mu}s$이며, 평균속력 및 순간속력이 약 2 km/s 차이가 났다. 이 결과를 통해 물질의 이차전자방출계수 및 일함수가 대기압 제트 플라즈마에서 스트리머 발생에 영향을 주는 것을 알았고, 다른 전극물질을 사용한 제트 플라즈마의 특성이 다름에 따라 여러 응용에서의 결과에도 영향을 미칠 것이라생각한다.

• Journal of Astronomy and Space Sciences
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• v.6 no.1
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• pp.17-28
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• 1989

The classical solar wind theory proposed by Parker(1963) explains well the dynamics of the wind pheonomena such as stellar wind and accretion disk. While the stellar wind system like the solar wind has the spherically symmetric wind structure, there are various jet phenomena which collimate the system into the narrow space. We can find these dynamical structures in SS433, in the optical jet of M87, and around the active galactic nulei. We present the dynamical structure of the jet system in disks, which conserves the angular monetum, with the Keplerian rotation and the strong relation between the geometrical cross section and the physical change of the jet stream on the basis of the hydrodynamic equations.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.115-128
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• 2006

A technical analysis of current scramjet and combined-cycle engine is presented. Substantial research has been pursued to characterize the operation mechanism of scramjet propulsion, especially in the areas of flame stabilization and system integration, dramatically over the years in support of both military and space access application. Major technology that had significant impact on the maturation of scramjet propulsion technology are dual combustion ramjet, dual mode ramjet, and combined cycle engine to cover a typical wide rage of flight, up to flight Mach number 10. Notable are the fundamental and practical techniques, for instance, scram propulsion itself, thermal relaxation and protection using endothermic fuel and/or CSiC composit materials, and design/manufacture of movable intake and nozzle, to realize high speed propulsion system in near future.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.3
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• pp.10-18
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• 2001

In this paper, Supersonic jets impinging on a wedge were investigated in order to acquire fundamental design data for jet deflectors. Surface pressure distributions and pressure contours were obtained using a cold flow tester producing Mach 2 supersonic jets. Schlieren system was used to visualize the flow structure on the wedge surface. Numerical computations were performed and compared with the experimental results. Both results were in good agreement. The results showed that underexpansion ratio did not affect on the surface pressure distribution when the wedge is located at the nozzle exit. With increasing underexpansion ratio, pressure recovery decreased as the wedge is located farther from the nozzle exit. In the pressure contour, it was possible to locate the region where the peak pressure on the wedge surface was occurred.