• 한국추진공학회지
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• 제16권6호
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• pp.9-15
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• 2012

추력변화를 초공동 수중운동체의 추진체로 사용되는 수반응성 금속입자와 해수는 연소챔버 내에서 균질하게 혼합될 때 비추력이 극대화 된다. 본 연구의 목적은 상사성의 관점에서 분사기 형상이 입자 분포에 미치는 영향을 알아보는 것이다. 이를 위해 PIV기법을 이용하여 반경방향의 입자 분포와 입자 평균속도의 상사성에 대하여 알아보았다.

• KIEE International Transactions on Electrophysics and Applications
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• 제3C권6호
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• pp.224-229
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• 2003

An ultra high frequency (UHF) coupler possessing ultra wide band (UWB) characteristics ranging from hundreds of MHz to several GHz is desirable for the detection of the partial discharge (PD) pulses because the pulses propagate with rise time shorter than one nanosecond in a gas-insulated substation (GIS). Thus, the authors have proposed a log-periodic antenna for GIS PD detection. Various parameters of the coupler such as frequency bandwidth, coupler gain, radiation pattern, and coupler geometry were considered throughout the simulations. The experiments for the detection characteristics of the coupler were carried out in the mock-up GIS chamber. The results indicated that the detection characteristics of the coupler are dependent on the installation angle of the coupler, the position of the coupler in the hand hole and the existence of the spacer.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.205-209
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• 2010

The technology of production of the thermoplastic composite rocket propellants is based on a two-phase production procedure. The first phase represents the production of a semi-product in the sheet (foil) form (thickness: 0.5 mm ~ 5 mm), whereas the second phase is realized independently from the first one and it is based on the semi-produced product and thus the final form of the propellant grain is realized in relation to the defined geometry. Well done mechanical characteristics of the propellant grain enable that the same thing could be used as a mandrel in the filament winding procedure in creating the motor chamber of the composite material.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2010년도 제35회 추계학술대회논문집
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• pp.597-600
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• 2010

극저온 액체 질소 제트 유동의 아임계 및 초임계 특성을 파악하기 위한 실험을 수행하였다. 단일 제트 분사기를 고압 챔버 내에 장착하여 제트의 주위기체압력, 분사기 형상 및 유동 조건의 영향을 조사하였다. 실험 결과로부터 아임계 조건과 초임계 조건에서의 제트의 특성 변화를 관찰하였으며, 주위기체압력이 대기압일 경우 유동 내에 섭동이 발생함을 파악하였다. 분사기 형상에 따른 유동 변화 또한 파악하였다.

• 한국추진공학회지
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• 제4권1호
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• pp.74-92
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• 2000

A numerical analysis has been conducted to study the transient flowfield during the transition from the booster to sustainer phase in an integrated rocket ramjet (IRR) propulsion system. Emphasis is placed on the unsteady inlet aerodynamics, fuel/air mixing in an entire ramjet engine during the flow transient phase. The computational geometry consists of the entire IRR engine, including the inlet, the combustion chamber, and the exhaust nozzle. Turbulence closure is achieved using a low-Reynolds-number two-equation model. The governing equations are solved numerically by means of a finite-volume, preconditioned flux-differencing scheme over a wide range of Mach umber. Various important physical processes are investigated systemically, including terminal shock train.

• Journal of Mechanical Science and Technology
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• 제20권10호
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• pp.1626-1637
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• 2006

The pressure pulsation due to the gear geometry of the gerotor (generalized rotor) pump mainly occurs in an instant that the chamber of the gerotor enters the delivery port and leaves the suction one. Such a pressure pulsation may result in undesirable vibration and noise of pump components as well as cavitation in hydraulic system. Therefore, it is very important to examine the pressure characteristic of the gerotor pump at its design and analysis stages. In this paper, in order to reduce the pressure pulsation in the gerotor pump, the port plate with the relief grooves is designed by referring to as notch of vane pump and relief groove of piston pump. A series of the theoretical analyses on the pressure pulsation is performed in consideration of various design parameters of the port plate, including the installation positions of the port inlet/outlet and the groove width, and the operating conditions such as rotational velocity and delivery pressure.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 2001년도 제33회 춘계학술대회 개최
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• pp.392-400
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• 2001

The sealing performance of an elastomeric O-ring seal using bi-materials has been analyzed for the contact stress behaviors that develop between the O-ring seal and the surfaces with which it comes into contact. The leakage of an O-ring seal will occur when the pressure differential across the seal just exceeds the initial (or static) peak contact stress. The contact stress behaviors that develop in compressed O-rings, in common case of restrained geometry(grooved), are investigated using the finite element method. The analysis includes material hyperelasticity and axisymmetry. The computed FEM results show that the contact stress behaviors are related to a ratio of length between NBR and FFKM and temperature of vaccum chamber.

• Advances in aircraft and spacecraft science
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• 제7권3호
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• pp.187-202
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• 2020

The exhaust nozzle serves back pressure of Pulse detonation combustor, so combustion chamber gets sufficient pressure for propulsion. In this context recent researches are focused on influence of nozzle effect on single cycle detonation wave propagation and propulsion performance of PDE. The effects of various nozzles like convergent-divergent nozzle, convergent nozzle, divergent nozzle and without nozzle at exit section of detonation tubes were computationally investigated to seek the desired propulsion performance. Further the effect of divergent nozzle length and half angle on detonation wave structure was analyzed. The simulations have been done using Ansys 14 Fluent platform. The LES turbulence model was used to simulate the combustion wave reacting flows in combustor with standard wall function. From these numerical simulations among four acquaint nozzles the highest thrust augmentation could be attained in divergent nozzle geometry and detonation wave propagation velocity eventually reaches to 1830 m/s, which is near about C-J velocity. Smaller the divergent nozzle half angle has a significant effect on faster detonation wave propagation.

• 한국분무공학회지
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• 제27권1호
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• pp.18-25
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• 2022

Hot-firing tests were performed to experimentally confirm the effect of the eigenmode in the fuel-air mixing section on combustion instability by changing mixing section length, inlet mean velocity, equivalence ratio, and swirler geometry. A premixed gas composed of air and ethylene was supplied to the combustion chamber through an mixing section and an axial swirler. As the mixing section length increased, the inlet velocity perturbation decreased, but the combustion instability increased more. It was found that the resonance frequency of the first longitudinal mode in the mixing section shifted to the third longitudinal mode as the length of the mixing section increased. The results implied that the transition of the resonace frquency by changing the length of the mixing section might cause combustion instability.

• 조명전기설비학회논문지
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• 제19권4호
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• pp.1-8
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• 2005

본 연구에서는 2차원적 유체 모델을 통하여 보다 실질적인 플라즈마를 이해하고자 하였으며, 기하학적인 방전전극 구조를 반영하도록 전극단에서 챔버 외벽의 거리를 변화시키면서 플라즈마의 특성을 정량적으로 비교 분석하고자 하였다. 방전 챔버의 구조로서, 전극의 반경과 방전 챔버의 높이는 일정하게 유지하면서 방전 챔버의 넓이를 변화시킴에 따라 형성되는 플라즈마의 특성을 분석하였다. 그 결과, 전극단과 챔버 외벽의 거리가 짧을수록 그 영역에서 전계가 강하게 형성되어, 외벽을 향하는 각 입자들의 움직임도 매우 활발하다는 것을 알 수 있었다. 또한, 전각단과 외벽과의 거리가 짧을수록 전극 면상에서 형성되는 입자들의 수밀도와 유속의 변화가 일정하게 형성되는 것을 알 수 있었다. 이러한 결과는 웨이퍼의 대구경화에 따른 플라즈마의 균일성을 고려할 경우에 매우 효과적일 것으로 고려되어 진다.