• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.9
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• pp.899-905
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• 2009

Most supersonic-flow test facility has axisymmetric nozzles or two-dimensional symmetric nozzles. Compared to these nozzles, a two-dimensional asymmetric nozzle has advantages of reducing low cost for various Mach number testing and undesirable flow structure such as shock wave reflection because the nozzle part can be directly connected to the test section part in this type of nozzle. The two-dimensional asymmetric nozzle, which was Mach number 2, was designed for supersonic combustion experiment. And it was verified with the numerical analysis and visualization of Mach wave. This study suggested the practical method for design and verification of supersonic two dimensional asymmetric nozzles.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.1
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• pp.54-63
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• 2006

Ejector system are used to transport a low momentum flow to the higher pressure flow by the momentum change between high and low momentum flows. This system is used to simulate the high altitude and Mach number condition over altitude 20 km and Mach 4 of the supersonic test facility. We applied the design and the performance analysis technique(EISIMP code) of the Ramjet Test Facility(RJTF) air system in JAXA to the ejector system of the ramjet test facility in KARI. After preliminary design of the ejector system, we performed a computational study using FLUENT and investigated shock structures and flow characteristics of the ejector system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.573-577
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• 2009

Dynamic behavior simulation of supersonic engine was performed and PI control algorithm was studied for the buzz control in the inlet and the thrust control. Firstly, required thrust was tracked according to the fuel flow control and then inlet pressure was regulated through the nozzle throat area control so that the buzz margin has the positive all the time. The control was performed according to the change of flight Mach number, altitude and angle of attack. The proportional gain and the integral gain for regulating the buzz margin was induced and simulated. In the results, it was confirmed and satisfied that control target in the operating area was changed the angle of attack from $0^{\circ}$ to $10^{\circ}$ at the flight Mach number of 2.1~3.0.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.4
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• pp.18-25
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• 2000

A two-color particle image velocimetry (PIV) has been developed for measuring two dimensional velocity flowfields and applied to a Mach 2.0 supersonic nozzle. This technique is similar to a single-color PIV technique except that two different color laser beams are used to solve the directional ambiguity problem. A green-color laser sheet (532 nm: 2nd harmonic beam of YAG laser) and a red-color laser sheet (619 nm: output beam from YAG pumped Dye laser using Rhodamine 640) are employed to illuminate the seeded particles. A high resolution (3060${\times}$2036) digital color CCD camera is used to record the particle positions. This system eliminates the photographic-film processing time and subsequent digitization time as well as the complexities associated with conventional image shifting techniques for solving directional ambiguity problem. The two-color PIV also has the advantage that velocity distributions in high speed flowfields can be measured simply and accurately by varying the time interval between two different laser beams due to its high signal-to-noise ratio and thereby less requirement of panicle pair numbers for a velocity vector in one interrogation spot. The velocity distribution in the Mach 2.0 supersonic nozzle has been measured and the over-expanded shock cell structure can be predicted by the strain rate field. These results are compared and analyzed with the schlieren photograph for the velocity distributions and shock location.

• Korean Journal of Optics and Photonics
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• v.17 no.3
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• pp.285-289
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• 2006

A novel alignment-free micro-optic MZI filter has been demonstrated. The filter is composed of two fiber-pigtailed collimators and a beam-splittingplate with a periodically etched stripe pattern. We fabricated the plate through a standard lithographic formulation process by using a pyrex substrate glass with SU-8 resist coating on its one of the surfaces. The maximum insertion loss of the implemented filter was less than 2 dB over 1000 nm to 1600 nm and the extinction ratio was larger than 33 dB. The measured PDL within the 3-dB pass band of the filter was less than 0.15dB and the maximum extinction ratio variation was less than 2 dB even when the worst alignment error occured.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.1
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• pp.97-103
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• 2003

Numerical research has been done for the transverse jet behind a rearward-facings step in turbulent supersonic flow without chemical reaction. Purpose of transverse jet is to enhance mixing of the fuel in the combustor. Two-dimensional unsteady flowfields generated by slot injection into supersonic flow are numerically simulated with the Navier-Stokes equations with two-equation k-$\varepsilon$ turbulence model. Numerical method is used high-order upwind TVD scheme. Eight cases are computed for different slot momentum flux ratios and slot position at downstream of the step. The flow is very similar to the cavity flow, because the jet acts as an obstacle. The numerical results thus show the periodic phenomenon.

• Proceedings of the Materials Research Society of Korea Conference
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• 2003.03a
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• pp.244-244
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• 2003

나노인덴테이션은 시편에 압자를 침투시켜 재료의 기계적 특성을 파악할 수 있는 경도시험법이다. 압입범위를 나노미터범위로 조절할 수 있어 기존에 접근할 수 없었던 극 미소부분에로 응용이 넓어지고 있다. 경도시험시 재료의 탄성 및 소성 작용에 의해 재료는 변형되고, 표면변화 관찰을 통해 표면아래 부분에서 이루어지고 있는 거동을 예측할 수 있다. 이러한 관점에서 나노인덴테이션 시험시에도 발생하는 파일업과 싱크인 현상에서 재료가 나노미터 범위에서 어떠한 양상으로 변형을 하는지를 고찰하는 것은 의미가 있을 것이다. 본 연구에서 파일업과 싱크인의 양상을 파악하고 그 양을 정량화하기 위하여 가공경화양에 따른 표면변화와 압입하중 변화에 따른 표면변화를 관찰하였다. 어닐링한 봉상 알루미늄을 압축변형을 0%, 5%, 20%, 40%, 50% 로 변형시켜 가공경화를 일으켰고, 표면은 전해연마하여 나노압입시험이 가능하도록 하였다. 각각의 시편을 나노인덴테이션 압입하중을 변화시켜 재료에서 하중 변화에 따라 나타나는 표면변화를 관찰하였고, 위의 각 조건에서 파일업양을 정량화 하였다. 연구결과에 대해 ANSYS 유한요소분석 프로그램을 사용하여 재료의 변형양상을 시뮬레이션 하였고, 실제 실험데이터와 비교 분석하였다.

• Journal of Welding and Joining
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• v.13 no.3
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• pp.1-7
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• 1995

1992년 9월 현재 전 세계적으로 운전 중(건설포함)인 액화 및 인수기지의 LNG 저장탱크는 지상식-이중벽 금속 탱크, 지상식-맴브레인 PC 탱크, 지상식-자립식 내부탱크/PC 외부탱크, 피드식-RC(Reinforced Concrete) 보강둑 탱크, 피트식-이중벽 금속탱크, 피트식-자립식 내부탱크/PC 외부탱크 및 지하식 탱크의 7가지 유형으로 나 타낼 수 있다. 또한 액화천연가스를 저장하는 내부탱크 소재에 따라 9%Ni강 및 MEMBRANE(SUS304) 형식으로 대별할 수 있다. MEMBRANE 저장탱크 형식의 핵심기술인 MEMBRANE은 -162.deg.C의 LNG에 의한 열수축팽창에 견딜 수 있도록 스테인레스강판 (SUS304)을 사용하여 기하학적으로 특이한 주름진 형상을 갖도록 설계되었으며 주름 형상에 따라 프랑스의 테크니가즈(Technigaz), 일본의 가와사끼(Kawasaki). 미쓰비시 (Mitsubishi), 이시가와지마하리마(Ishikawajima-Harima)사의 멤브레인과 세계에서 3번째로 한국가스공사 연구개발원이 개발한 링디식 멤브레인으로 구별할 수 있다. 본 해설에서는 국내의 전국 천연가스 공급사업계획 및 건설현황을 검토하고 최근 전 세계적으로 널리 사용되고 있는 액화천연가스 저장탱크의 종류를 용량별, 년도별로 분석하여 전세계의 액화천연가스 저장탱크에 관해 소개 하겠다.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.2
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• pp.51-58
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• 2001

Supersonic, axisymmetric, jets issuing from several kinds of dual, coaxial, nozzles were experimentally investigated. Four different kinds of coaxial, dual nozzles were employed to characterize the major. features of the supersonic, coaxial, dual jets. Two convergent-divergent supersonic nozzles with different impinging angle on the jet axis of were designed to have the Mach number 2.0 and used to compare the coaxial jet flows with those discharging from two sonic nozzles. The primary pressure ratio was changed in the range from 4.0 to 10.0 and the assistant jet ratio from 1.0 to 4.0. The results obtained show that the assistant jets from the annular. nozzle affect the coaxial jet flows and an increase of both the primary jet pressure ratio and assistant jet pressure ratio lead to a longer supersonic length of the dual, coaxial jet.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.46 no.1
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• pp.43-48
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• 2009

We constructed a simple wavelength readout system for a tunable fiber laser which was used for a fiber Bragg grating sensor array system. A quadrature sampling method was used to demodulate wavelength variations of the tunable laser which consisted of a SOA(semi-conductor optical amplifier) and a fiber-optic Fabry-Perot filter. Internal triggers, which have a 90 degree phase period, have been generated by using a double-pass Mach-Zehnder interferometer. From Lissajous plots with quadrature sampled data, a mean phase error of ${\sim}2.51$ mrad was obtained. From the wavelength readout experiments, an accurate and fast linear wavelength demodulation has been confirmed.