• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.130-134
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• 2006

The injection uniformity of the fuel manifold in a liquid rocket engine has been analyzed with dividing plates to improve the cooling performance at the face plate. Three dimensional computational fluid dynamics analysis has been performed to compare the injection uniformity for 5 candidate designs and has been verified to compare with the measured data for the optimal manifold design. For the case I and II, the coolant mass flux increases as the whole working fluid is enforced to flow under the dividing plate. The injection uniformity decreases due to the variation of mass flux at the end of dividing plate and the concentration of mass flow rate at the center of manifold. However case III and IV have uniform injection performance due to reduced mass flux concentration as the coolant can flow along both upper passage and lower passage of the dividing plate. Among the candidate designs, case IV is thought to be the optimal dividing plate with regard to cooling performance and injection uniformity.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.113-122
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• 2002

A numerical analysis on the uniformity of propellant injection velocity of KSR-III has been carried out to give design improvements. Injector holes were approximated as porous media with the same pressure drop . The injection velocity is higher at the opposite side of the inlet for both LOX and fuel due to the static pressure rise in the stagnation region. Flow passages at the vertical circular plate in the LOX dome increase the uniformity of LOX injection. Little change was observed in the injection uniformity and pressure drop for the slanted LOX passage. Also provided were the O/ F ratio distributions from the oxidizer/ fuel injection velocity analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1140-1147
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• 2009

Flow analyses have been performed to investigate the uniformity of propellant flow through the fuel and oxidizer manifolds of a full-scaled gas generator for a pump-fed liquid rocket engines. Injectors were simulated as porous medium layers having equivalent pressure drops. The uniformity of propellants has been analyzed for 3 fuel rings and 3 injector head configurations. The mixture ratio distribution at the exit of injectors has been estimated from the mass flow rates of fuel and oxidizer. The best configuration of fuel ring and injection head was selected through these flow analyses.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.92-100
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• 2005

An optimal fuel manifold is suggested to improve the cooling performance of an injector face plate. The cooling performance at the center area of the injector face plate is to be augmented while the spatial injection uniformity is maintained. The comparison of the cooling performance of f candidates gives the conclusion that the dividing plate from 2-3 injector .ow to 9-10 injector. row is an optimal. The maximum face plate temperature decreases by 27$\%$ while the injection uniformity is close to that of the original design. The pressure drop in the fuel manifold of the optimal design is also same as the original design.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.215-218
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• 2005

An optimal fuel manifold is suggested to improve the cooling performance of injector face plate. The cooling performance at the center area of the injector face plate is to be augmented while the spatial injection uniformity is maintained. The comparison of the cooling performance of 7 candidates gives the conclusion that the dividing plate from 2-3 injector row to 9-10 injector row is an optimal. The maximum face plate temperature decreases by $27\%$ while the injection uniformity is close to that of the original design. The pressure drop in the fuel manifold of the optimal design is also same as the original design.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.16-23
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• 2008

Flow analyses have been performed to investigate the uniformity of propellant flow through the oxidizer manifold of a 30 tonf full-scaled combustor. Injectors were simulated as porous medium layers of equivalent pressure drops. The uniformity of oxidizer propellant has been analyzed for various diameters of holes in vertical/horizontal distributors and configurations of oxidizer inlet to propose an improved design solution. It has been proven that the mass flow uniformity were improved by adjusting the holes in vertical/horizontal distributors.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.1
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• pp.95-102
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• 2006

The PPT being currently developed for the flight model represents a significant leap in techniques and technology compared to the previous flight ones. The electrical energy to be charged in the pulsed plasma thruster (PPT) is a very important aspect to provide an uniform impulse bit ,, and a specific impulse ,, for satellite attitude control. In this paper, we propose a nonlinear control technique and a stability analysis based on the Lyapunov function for the pulsed plasma thruster. Specifically, the proposed control law guarantees to charge and discharge the electrical energy generated from the power processing unit (PPU) within the specified time.

• Journal of the Korean Institute of Gas
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• v.8 no.1 s.22
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• pp.7-12
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• 2004

In the quality control of the aerosol skincare products containing powders, it is essential to guarantee that the contents in the bottle can be completely used without leakage or clogging of the nozzle. In this paper, the clogging caused by powder was investigated and the clogging can be effectively removed by emulsifying the contents containing powder with the LPG using a proper surfactant. And the spraying test shows that the contents in the bottle are completely propelled to outside by LPG when properly emulsified by POE(40) HCO.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.12
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• pp.2376-2384
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• 1992

A theoretical analysis is carried out to predict the characteristics of transient ignition phenomena for the spherical fuel droplets cloud with non-uniform droplet size and number density distribution. Numerical calculations are performed for various cases depending on the combinations of the major parameters such as ambient temperature and initial distributions of droplet size and number density. The results of present study show that the ignition delay decreases for higher ambient temperature and smaller droplet size. Droplets cloud of hollow type with outer concentrated distribution ignites most rapidly.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.02a
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• pp.79-79
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• 2010

최근, 차세대 디스플레이, 터치스크린, 전자파 차폐 및 흡수 등의 분야에 응용하기 위해서 현재 주로 사용되고 있는 ITO박막을 대체하기 위한 연구가 활발하게 진행 되고 있다. ITO 박막은 희소원소인 인듐에서 기인하는 높은 비용뿐만 아니라 매장량도 한계가 있어 대체 재료의 개발이 시급하게 요구되고 있다. 더구나, 다양한 차세대 응용에 있어서는 투명전도성 뿐만 아니라 휠 수 있는 유연성까지 요구되어 ITO박막을 대체할 새로운 투명전도성 유연 박막의 개발에 관한 연구들이 활발히 이루어지고 있다. 탄소나노튜브(CNT)는 금속을 능가하는 이론적인 전기전도도를 갖고 있으며, 높은 탄성등의 우수한 기계적 성질을 갖고 있어, 전도성 확보 및 유연성 구현이라는 투명전도성 플렉서블 박막소재에 요구되는 사항들을 충족시킬 뿐만 아니라, 최근의 대량 합성법등의 개발로 저가에 공급할 수 있다는 장점들이 있어 ITO대체 재료로서 주목을 받고 있다. 그러나, CNT는 튜브 사이에 강한 반데르발스 인력을 가지고 있어 용매 중에 분산하는데 많은 어려움이 있으며, 액상 분산과정을 통한 CNT기반의 플렉서블 박막 제작에 있어서 큰 과제로 남아있다. 본 연구에서는 플라즈마 기능화 처리를 통하여 CNT에 친수성을 부여하였고, 초음파 처리를 통하여 에탄올 중에 CNT를 균일하게 분산한 후, 스프레이 분사법을 이용해 투명 유연기판인 PET고분자 필름위에 균일 박막을 제작하였다. CNT는 아세틸렌 가스를 이용한 열화학증기증착법으로 1mm 이상의 길이를 갖는 수직배향 CNT를 합성하였으며, 이를 아르곤 및 암모니아 플라즈마로 기능화 처리를 실시하였다. 플라즈마 처리를 통해 기능화 된 탄소나노튜브는 플라즈마 처리되지 않은 탄소나노튜브와 분산 속도에서 현저한 차이를 보였다. 제작한 CNT 기반의 투명전도성 유연박막들은 막두께에 따른 전도도 및 투광도의 관계를 조사하였고, 기판에 분사된 CNT 박막의 표면 특성은 AFM, Raman, 접촉각 실험 등을 통하여 분석하였다.