• 한국추진공학회지
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• 제8권2호
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• pp.46-53
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• 2004

로켓 노즐부의 토출관에 대한 신뢰성을 위하여 접합계면의 결함유무를 평가하기 위한 초음파 시험법을 개발하였다. 본 연구의 주된 목적은 철피와 FRP 사이의 에폭시 접합계면에서 미접착 부위와 미충전 부위를 찾아내는 것이다. 미접착부나 미충전부를 찾아내기 위해서 고주파수 초음파 펄스-에코를 이용하여 철피와 에폭시 접착제 사이의 경계면에서 반사되는 초음파 신호를 측정하였다. 결함이 있는 부위의 gap의 크기를 평가하기 위해서 저주파 초음파를 이용하여 공진이 일어나도록 철피를 가진하였다. 이러한 기법을 이용하여 양산품을 검사하기 위한 자동화 장치를 개발하였다. 검사기법을 검증하기 위해서 초음파 시험을 수행한 토출관을 절단하여 현미경으로 gap을 측정하였다.

• 한국분무공학회지
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• 제25권1호
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• pp.8-14
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• 2020

Recently, 1-D model-based engine development using virtual engine system is getting more attention than experimental-based engine development due to the advantages in time and cost. Injection rate profile is the one of the main parameters that determine the start and end of combustion. Therefore, it is essential to set up a sophisticated model to accurately predict the injection rate as starting point of virtual engine system. In this research, procedure of 1-D model setup based on AMESim is introduced to predict the dynamic behavior and injection rate of diesel injector. As a first step, detailed 3D cross-sectional drawing of the injector was achieved, which can be done with help of precision measurement system. Then an approximate AMESim model was provided based on the 3D drawing, which is composed of three part such as solenoid part, control chamber part and needle and nozzle orifice part. However, validation results in terms of total injection quantity showed some errors over the acceptable level. Therefore, experimental work including needle movement visualization, solenoid part analysis and flow characteristics of injector part was performed together to provide more accuracy of 1-D model. Finally, 1-D model with the accuracy of less than 10% of error compared with experimental result in terms of injection quantity and injection rate shape under normal temperature and single injection condition was established. Further work considering fuel temperature and multiple injection will be performed.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.290-293
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• 2017

스크램젯 엔진용 초음속 연소기 연구를 위한 직결형, 연속식 연소 시험 설비를 개발하였다. 비행체 속도 마하 5, 연소기 입구 유속 마하 2를 가정하고, 시험 대상 연소기의 유로 단면은 높이 32 mm, 폭 70 mm로 가정하여 설비 요구 조건을 결정하였다. 이에 따라 설비는 유동 전압력 548 kPaA, 전온도 1,320 K, 유량 0.776 kg/s로 설계하였다. 설비는 터보형 압축기, 전기 가열기 및 연소식 가열기와 그 하류에 유동 가속을 위해 장착한 마하 2의 2차원 노즐로 구성하였다. 노즐 상류에서 산소를 추가 공급하여 연소식 공기 가열에 의한 산소 감소를 보상하도록 하였다. 배기는 별도의 감압은 하지 않았다. 저압, 저유량에서의 시운전을 수행하였으며, 설계점 운전은 향후 계획 중에 있다.

• 한국방재학회 논문집
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• 제9권5호
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• pp.63-68
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• 2009

본 연구에서 물 흐름에 일정한 농도로 포 소화약제를 정확하게 혼합하는 포 소화설비용 소화약제 혼합장치의 성능향상을 위하여 포소화약제의 정량 혼합특성을 분석하였다. 펌프, 탱크, 압력계, 유량계, 노즐로 구성되는 성능평가 시스템을 사용하여 개발된 프로포셔너의 성능이 실험적으로 평가하였다. 결과적으로 라인프로포셔너의 포소화약제 혼합성능은 벤츄리 효과에 의한 물유량 증가와 오리피스 단면적 증가에 따라 증가하고 오차율 $\pm4%$이내의 범위에서 물 유량과 포소화약제 양의 혼합농도 3%의 성능을 보였다. 프레셔프로포셔너의 경우 물 유량 증가와 입구압력 증가에 따라 혼합성능이 증가하고 오차율 $\pm2%$이내의 범위에서 물 유량과 포소화약제 양의 혼합농도 3%의 성능으로 분석되었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.109-114
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• 2008

This paper presents the development status of a subscale precooled turbojet engine "S-engine" for the hypersonic cruiser and space place. S-engine employs the precooled-cycle using liquid hydrogen as fuel and coolant. It has $23cm{\times}23cm$ of rectangular cross section, 2.6 m of the overall length and about 100 kg of the target weight employing composite materials for a variable-geometry rectangular air-intake and nozzle. The design thrust and specific impulse at sea-level-static(SLS) are 1.2 kN and 2,000 sec respectively. After the system design and component tests, a prototype engine made of metal was manufactured and provided for the system firing test using gaseous hydrogen in March 2007. The core engine performance could be verified in this test. The second firing test using liquid hydrogen was conducted in October 2007. The engine, fuel supplying system and control system for the next flight test were used in this test. We verified the engine start-up sequence, compressor-turbine matching and performance of system and components. A flight test of S-engine is to be conducted by the Balloon-based Operation Vehicle(BOV) at Taiki town in Hokkaido in October 2008. The vehicle is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high-altitude observation balloon. After 40 second free-fall, the vehicle pulls up and S-engine operates for 60 seconds up to Mach 2. High altitude tests of the engine components corresponding to the BOV flight condition are also conducted.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.115-121
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• 2008

A core engine for pre-cooled turbojet engines is designed and its component performances are examined both by CFD analyses and experiments. The engine is designed for a flight demonstration of precooled turbojet engine cycle. The engine uses gas hydrogen as fuel. The external boundary including measurement devices is set within $23cm{\times}23cm$ of rectangular cross section, in order to install the engine downstream of the air intake. The rotation speed is 80000 rpm at design point. Mixed flow compressor is selected to attain high pressure ratio and small diameter by single stage. Reverse type main combustor is selected to reduce the engine diameter and the rotating shaft length. The temperature at main combustor is determined by the temperature limit of non-cooled turbine. High loading turbine is designed to attain high pressure ratio by single stage. The firing test of the core engine is conducted using components of small pre-cooled turbojet engine. Gas hydrogen is injected into the main burner and hot gas is generated to drive the turbine. Air flow rate of the compressor can be modulated by a variable geometry exhaust nozzle, which is connected downstream of the core engine. As a result, 75% rotation speed is attained without hazardous vibration and heat damage. Aerodynamic performances of both compressor and turbine are obtained and evaluated independently.

• 전기화학회지
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• 제4권3호
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• pp.104-108
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• 2001

용융분사법으로 나프탈렌계 메조페이스 피치(mP)를 방사하여 산화안정화 속도를 변화시켜 흑연화 섬유의 모폴러지를 제어하였으며, 흑연화 섬유를 이용하여 Li-ion 이차전지 부극을 제조하여 충$\cdot$방전 거동 및 용량을 측정하였다. 용융분사조건에 따라 제조된 피치섬유의 직경은 $4{\mu}m$로부터 $16{\mu}m$까지 다양하였다 이중에서 직경 $10{\mu}m$인 피치섬유를 선택하여 세가지 승온속도 조건 $2^{\circ}C/min,\;5^{\circ}C/min,\;10^{\circ}/min$에서 산화안정화 후 $1000^{\circ}C$에서 탄소화하여 $2650^{\circ}C$에서 흑연화 한 결과, 섬유 단면이 산화안정화 조건 $2^{\circ}C/min$의 경우는 라디알 구조, $5^{\circ}C/min$의 것은 라디알-랜덤 구조, $10^{\circ}C/min$의 경우는 skin-core 구조를 형성하였고, 승온속도가 큰 경우일수록 이흑연화성이 컷다. 이것은 큰 승온속도에서는 탄소화$\cdot$흑연화 과정에서 섬유표면에서만 산화안정화가 일어나고, 내부에서는 피치분자가 유동성이 커 승온과정에서 고결정성의 흑연구조가 발달한 것으로 추측된다. 따라서 이흑연화성이 큰 $10^{\circ}C/min$에서 산화안정화 한 것이 충전방전 용량이 $2^{\circ}C/min$의 경우에 비해서 1.3배로 약 400mAh/g, 충방전 효율도 $96.8\%$로 가장 우수한 특성을 나타냈다.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2011년도 제40회 동계학술대회 초록집
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• pp.407-408
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• 2011

Natural boron consists of two stable isotopes 10B and 11B with natural abundance of 18.8 atom percent of 10B and 81.2 atom percent of 11B. The thermal neutron absorption cross-section for 10B and 11B are 3837 barn and 0.005 barn respectively. 10B enriched specific compounds are used for control rods and as a reactor coolant additives. In this work 2 methods for boron enrichment were analysed: 1) Gas irradiation in static conditions. Dissociation occurs due to multiphoton absorption by specific isotopes in appropriately tuned laser field. IR shifted laser pulses are usually used in combination with increasing the laser intensity also improves selectivity up to some degree. In order to prevent recombination of dissociated molecules BCl3 is mixed with H2S 2) SILARC method. Advantages of this method: a) Gas cooling is helpful to split and shrink boron isotopes absorption bands. In order to achieve better selectivity BCl3 gas has to be substantially rarefied (~0.01%-5%) in mixture with carrier gas. b) Laser intensity is lower than in the first method. Some preliminary calculations of dissociation and recombination with carrier gas molecules energetics for both methods will be demonstrated Boron separation in SILARC method can be represented as multistage process: 1) Mixture of BCl3 with carrier gas is putted in reservoir 2) Gas overcooling due to expansion through Laval nozzle 3) IR multiphoton absorption by gas irradiated by specifically tuned laser field with subsequent gradual gas condensation in outlet chamber It is planned to develop software which includes these stages. This software will rely on the following available software based on quantum molecular dynamics in external quantized field: 1) WavePacket: Each particle is treated semiclassicaly based on Wigner transform method 2) Turbomole: It is based on local density methods like density of functional methods (DFT) and its improvement- coupled clusters approach (CC) to take into account quantum correlation. These models will be used to extract information concerning kinetic coefficients, and their dependence on applied external field. Information on radiative corrections to equation of state induced by laser field which take into account possible phase transition (or crossover?) can be also revealed. This mixed phase equation of state with quantum corrections will be further used in hydrodynamical simulations. Moreover results of these hydrodynamical simulations can be compared with results of CFD calculations. The first reasonable question to ask before starting the CFD simulations is whether turbulent effects are significant or not, and how to model turbulence? The questions of laser beam parameters and outlet chamber geometry which are most optimal to make all gas volume irradiated is also discussed. Relationship between enrichment factor and stagnation pressure and temperature based on experimental data is also reported.