• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.4
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• pp.1-8
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• 2014

Overexpanded flow of an axisymmetric thruster nozzle is numerically simulated to investigate effects of nozzle pressure ratio (NPR) on the shock structure and thrust performance. The Reynolds-averaged Navier-Stokes equations with k-${\omega}$ SST turbulence model are solved utilizing FLUENT solver. As the NPR is raised, thrust performance monotonically increases with the shock structure and flow-separation point being pushed toward the nozzle exit. It is also discussed that the flow structure at nozzle-exit plane which is immediately affected by a position of nozzle-interior shocks and expansion waves, has strong influence upon the thrust performance of thruster nozzle.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1995.04a
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• pp.313-317
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• 1995

최근 환경오염이 심각한 사회문제로 대두됨에 따라 환경오염원을 제거하기 위한 여러 가지의 집진장치가 개발되고 있는데 화력발전소에서는 건식정전집진장치(dry electrostatic precipitator)를 이용하고 있다. 건식정전집진장치는 햄머(hammer) 방식의 충격장치를 설치하여 집진극과 방전극에 충격을 가함으로써 충격력을 극대화시키고 높은 분진박리 효과를 꾀하고 있는데 환경오염원이 되고 있는 집진판의 분진의 분리율을 높이기 위해서는 집진판의 전체 영역에서 분진을 동일하게 떨어뜨릴 수 있는 충격장치가 설계되어야 하는데, 이를 위해서는 충격하중에 따른 집진판의 진동 형태를 정확하게 분석하여야 한다. 본 연구에서는 집진판의 충격하중에 따른 진동의 형태를 분석하기 위해 펄스 레이저를 이용한 2중 노출 홀로그래피 시스템을 구성하였다. 홀로그래픽 간섭계는 이미 오래 전에 개발된 레이저 응용 계측기법으로서 주로 정현적인 진동을 하는 진동체의 진동 현상을 연구하는 데에 많이 사용되어 왔는데 그 기술 개발은 상당한 수준에 있다. 그러나 종래의 기술들은 주로 헬륨-네온(He-Ne)레이저와 같은 연속 레이저(continuous wave laser)를 이용한 기술들인데 최근에는 루비(ruby) 레이저와 같은 펄스 레이저 (pulse laser)를 이용한 기술이 많이 응용되고 있다. 이 펄스 레이저 홀로그래픽 간섭계를 Gottenberg는 응력파에 의해서 발생된 변형을 측정하기 위해 사용하였고 Aprahamian등은 보(beam)와 평판의 굽힘파(bending wave)의 전파 특성 연구에 이용하였다. 그 실험적 결과는 수치적 해석 결과와 비교되어 매우 좋은 일치성을 보였는데 이러한 펄스 레이져 홀로그래픽 간섭계 기법의 주요 장점은 어떠한 특정한 순간에 관찰하고자 하는 시험편의 전체 영역의 파동 전파 형상을 관찰할 수 있다는 것이다. 따라서 본 연구에서는 펄스 레이저를 응용한 2중 노출 홀로그래피법(double exposure holography method)을 이용해서 집진판에 충격하중이 가해졌을 때 발생하는 진동이 발생과 전파 특성을 충격하중의 방향에 따라서 분석하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.9
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• pp.862-868
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• 2010

Development of a small scale aircraft has been carried out for the BASA(Bilateral Aviation Safety Agreement) program in Korea. This aircraft adopted all the composite structures for environmental friendly by low fuel consumption due to its lightness behavior. However the composite structure has s disadvantage which is very weak against impact due to foreign object damages. Therefore the aim of this study is focusing on the damage evaluation and repair techniques of the aircraft composite structure. The damages of composite laminates including the carbon/epoxy UD laminate and the carbon/epoxy fabric face sheets-honeycomb core sandwich laminate were simulated by a drop weight type impact test equipment and the damaged specimen were repaired using the external patch repair method after removing damaged area. The compressive strength test and analysis results after repairing the impact damaged specimens were compared with the compressive strength test and analysis results of undamaged specimens and impact damaged specimens. Finally, the strength recovery capability by repairing were investigated.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.15 no.7
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• pp.4081-4086
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• 2014

Cellulose acetate butyrate (CAB) is a biodegradable resin with excellent optical properties, but it is difficult to apply film process. In this study, an attempt was made to improve the processability of CAB using polyactic acid and the mechanical properties using an impact modifier. Polylacitc acid (PLA)/Cellulose acetate butyrate (CAB) blends with an impact modifier were prepared using a twin screw extruder. The temperature range was $140^{\circ}C$ to $200^{\circ}C$, and the screw speed was fixed to 200 rpm. To evaluate the miscibility of impact modified CAB/PLA, the glass transition behavior and morphology were observed by DSC and FE-SEM. The mechanical properties were investigated by dynamic mechanical analysis (DMA) and a Universal Testing Machine (UTM). In addition, the effect of an impact modifier in the polymer matrix was determined using a notched Izod impact strength tester. Finally, the PLA/CAB/impact modifier 75/25/10 ratio was found to be a compatible system. In the 10wt.% impact modifier, the sample had a 4 times higher izod impact strength than the non-toughening composition.

• Proceedings of the KWS Conference
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• 2009.11a
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• pp.16-16
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• 2009

Alloy 82/182로 용접된 원자력 발전소 주기기의 이종 금속 용접부는 장기간 운전 후 응력부식균열(SCC : Stress Corrosion Cracking)에 의한 결함이 나타나게 된다. 2000년대 이후로 원자력 주기기 Alloy 82/182 용접부에서 PWSCC(Primary Water Stress Corrosion Cracking)에 의한 Degradation이 급격히 증가하는 추세를 보이고 있으며, 국내에서도 이와 관련하여 원자력 발전소의 안전성에 대한 Issue 및 대비책에 대한 관심이 고조되고 있다. 이러한 Alloy 600 용접부에 대한 결함을 예방하기 위한 대표적인 기술로써 수명연장 오버레이 기술이 있다. 원자력 주기기 노즐부는 저탄소강으로 제작되어 있으며, 저탄소강에는 제작 시 용접후열처리가 적용된다. 후열처리를 하는 주된 이유는 Tempering을 통해 열영향부의 인성 및 연성의 회복과 강도를 감소시켜 모재와 동등 또는 이 이상의 물성을 갖도록 하는 데 그 목적이 있다. 그러나 수명연장 오버레이의 경우 현장 작업 시에 후열처리가 어렵기 때문에, 이를 대체하기 위한 기술로 템퍼비드 용접을 적용할 경우 후열처리를 면제해 주고 있다. 본 연구에서는 수명연장 오버레이 기술 개발의 일환으로써 저 탄소강에 대한 템퍼비드 용접 기술을 확립하였다. 실험에 사용된 모재는 원자력 주기기의 노즐에 사용되는 SA508 Gr.3 Cl.1을 사용하였으며, 용가재는 Alloy 52 및 52M을 사용하였다. 최적 조건 도출을 위해서 실험 매트릭스를 이용하여 기본 실험을 수행하였으며, 실험에는 자동 GTAW 용접을 적용하였다. 기본 실험을 통해 얻은 최적 조건을 사용하여 PQ 시험을 수행하여 WPS를 확보하였다. 분석은 용접 후 조직 및 경도 시험, 물리시험(인장시험, 굽힘시험 및 충격시험)을 수행하였다.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.124-132
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• 2004

This paper deals with the static and dynamic analysis of the housing and PCB of TCU(Thruster Control Unit) for KSLV-I(Korea Space Launch Vehicle-I). TCU should pass the environment test simulating the flight environment of KSLV-I. The most important tests are the vibration and the shock tests. In this research, we proposed a design standard about the vibration and the shock environment and then verified TCU housing and PCB design met the standard. Based on the analytical results, the TCU housing was redesigned to meet the design standard. The new design is supposed to pass the environment test.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.7 no.4
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• pp.743-748
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• 2006

We investigated the flame retardancy and the mechanical properties of Nylon6 by using melamine-based halogen-free flame retardants(melamine cyanurate:MC-100 and melamine phosphate:MP-100). We chose the UL-94 method for flame retardancy and measured the tensile strength, flexural strength, flexural modulus by using UTM and impact strength by using Izod impact tester. We also tested the effect of nano-clay on flammability and mechanical properties. We obtained the V0 grade when the concentration of flame retardant was over 5 wt%. The tensile strength and flexural strength decreased and flexural modulus increased with the concentration of both flame retardant systems. The results showed that MC-100 system was better than MPP-100 system. Because of poor dispersion, we did not obtain the synergistic effect of nano-clay.

• Applied Chemistry for Engineering
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• v.29 no.2
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• pp.168-175
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• 2018

In order to investigate the effect of the chemical treatment of bamboo fiber on physical properties of polypropylene (PP)/bamboo fiber (BF) composites, silane coupling agents such as ${\gamma}$-aminopropyltriethoxysilane (APS), ${\gamma}$-glycidoxypropyl-trimethoxysilane (GPS) and ${\gamma}$-mercaptopropyltrimethoxysilane (MRPS) were applied to BF and alkaline treated BF. Morphological properties of the chemically treated BF were confirmed by optical microscope and SEM measurements, and chemical structure changes were confirmed by FT-IR and EDS. TGA results showed that the thermal stability of silane treated BF increased. Based on the analysis of a universal testing machine and an Izod impact test, the flexural and impact properties of PP/silane treated BF composites showed higher values than those of PP/BF composites. The enhancement of interfacial adhesion properties of the PP/BF composite was checked from SEM images of the fracture of specimens after the tensile test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.328-331
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• 2008

In order to see the detailed characteristics of model scramjet engine, numerical analysis was performed and compared to the ground test results done by KARI and UQ. Pressure distribution predicted by numerical analysis showed good agreements with test results. Static temperature and pressure distribution explained the mechanisms of cavity flame holder and W-shape cowl which have showed enhancing effects on the supersonic combustion.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.13-19
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• 2003

A supersonic ground test facility to develop Ramjet and SCRamjet(Supersonic Combustion Ramjet) engine should be able to simulate high altitude and high Mach number conditions including air total pressure, oxygen level and specific heat ratio at the combustion chamber entrance. The test facility also should simulate the effect of oblique shock wave caused by the flight vehicle. The test facility developed in this study is supersonic free-jet blowdown type, which consists of high pressure air supply source(maximum pressure=32MPa), air heater(vitiation type), supersonic diffuser, ejector, and test chamber(nozzle exit dimension=200mm$\times$200mm).