• 한국추진공학회지
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• 제23권1호
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• pp.52-60
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• 2019

본 연구에서는 수치해석을 활용하여 여러 개의 이젝터로 구성된 병렬형 이젝터의 성능과 구조에 대한 특성을 확인하였다. 병렬 이젝터의 설계는 단일 이젝터와 동일한 설계 변수(질량 흡입비, 압축비, 팽창비)를 사용하였다. 해석 결과에 의하면, 병렬형과 단일 이젝터의 작동 질량 흡입비의 비가 같을 경우에는 성능에 있어 큰 차이를 보이지 않았으나, 시스템의 크기가 작아지는 이점이 있음을 확인하였다. 또한, 동일 성능의 이젝터를 병렬로 배치하였을 때는 질량 흡입비가 단일 보다 감소하여 더 낮은 압력을 구현하는 것을 확인하였다. 해석 결과를 종합하면 병렬형 이젝터 성능은 단일 이젝터와 크게 다르지 않으나, 병렬형 이젝터 구성에 따라서는 크기와 작동에 이점이 있음을 확인하였다.

• 한국추진공학회지
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• 제3권4호
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• pp.67-74
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• 1999

고체 물체 표면이나 지표면에 초음속 제트가 충돌할 때 발생되는 문제들은 다단 로켓의 분리, 우주공간에서의 도킹, 수직 이/착륙기, 제트 엔진의 배기가스, 가스터빈 블레이드, 지상 로켓 발사 등의 다양한 상황에서 일어나며 이러한 충돌제트의 유동은 아음속과 초음속 혼합영역, 충격파가 교차하는 영역, 팽창파, 난류 전단층 등의 매우 복잡한 구조를 이루고 있는 것으로 알려져 있다. 본 연구에서는 출구마하수 2, 축소-확대형 초음속 노즐을 통해 과소 팽창된 제트가 수직, 경사평판에 부딪힐 때 형성되는 표면압력분포 및 유동가시화 등을 초음속 유동시험장치를 이용하여 연구하였다. 평판에서의 최대압력은 수직일 경우보다 경사졌을 때 훨씬 더 컸으며, 이는 여러 충격파를 통한 압력 회복 때문이다. 또한, 평판이 자유제트의 첫 번째 충격파 셀 내에 위치할 때 과소 팽창비에 따른 표면압력분포는 서로 유사한 경향을 보여주었다.

• 한국응용과학기술학회지
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• 제35권4호
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• pp.1260-1268
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• 2018

항공터빈유는 등유 기반의 석유제품에 산화 방지제(Antioxidant), 빙결 방지제(Fuel system icing inhibitor, FSII), 전기전도도 향상제(Electrical conductivity improver) 등의 첨가제를 첨가하여 항공기 연료로서 필요한 성능 향상 및 보관이나 이송 등에 관한 특정한 능력을 부여시키고 있다. 이들 첨가제는 항공터빈유의 품질에 이상이 발생하거나 다른 석유제품과 구별하기 위하여 그 첨가량을 정성 및 정량적으로 분석할 수 있어야 한다. 항공터빈유는 수많은 탄화수소 화합물로 구성된 복잡한 화합물이기 때문에 미량으로 첨가된 산화 방지제와 빙결 방지제를 분석하기 위하여 Multi-dimensional GC-MS (MDGC-MS)의 Deans switching 기술을 적용하였다. 2.5 - 20 mg/L 농도 범위의 산화 방지제와 빙결 방지제를 MDGC-MS로 정량 및 정성적으로 분석할 수 있었으며, 검출 한계는 1-dimensional GC-MS의 분석 결과와 비교하여 약 2배 정도 낮았다. 본 연구에서 개발된 시험 방법은 기존의 GC-MS보다 첨가제 피크의 분리능이 더 우수하였으며, 시료의 전처리가 필요없이 두 가지 첨가제를 동시에 분석할 수 있었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제36회 춘계학술대회논문집
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• pp.1-2
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• 2011

Hybrid rockets have lately attracted attention as a strong candidate of small, low cost, safe and reliable launch vehicles. A significant topic is that the first commercially sponsored space ship, SpaceShipOne vehicle chose a hybrid rocket. The main factors for the choice were safety of operation, system cost, quick turnaround, and thrust termination. In Japan, five universities including Hokkaido University and three private companies organized "Hybrid Rocket Research Group" from 1998 to 2002. Their main purpose was to downsize the cost and scale of rocket experiments. In 2002, UNISEC (University Space Engineering Consortium) and HASTIC (Hokkaido Aerospace Science and Technology Incubation Center) took over the educational and R&D rocket activities respectively and the research group dissolved. In 2008, JAXA/ISAS and eleven universities formed "Hybrid Rocket Research Working Group" as a subcommittee of the Steering Committee for Space Engineering in ISAS. Their goal is to demonstrate technical feasibility of lowcost and high frequency launches of nano/micro satellites into sun-synchronous orbits. Hybrid rockets use a combination of solid and liquid propellants. Usually the fuel is in a solid phase. A serious problem of hybrid rockets is the low regression rate of the solid fuel. In single port hybrids the low regression rate below 1 mm/s causes large L/D exceeding a hundred and small fuel loading ratio falling below 0.3. Multi-port hybrids are a typical solution to solve this problem. However, this solution is not the mainstream in Japan. Another approach is to use high regression rate fuels. For example, a fuel regression rate of 4 mm/s decreases L/D to around 10 and increases the loading ratio to around 0.75. Liquefying fuels such as paraffins are strong candidates for high regression fuels and subject of active research in Japan too. Nakagawa et al. in Tokai University employed EVA (Ethylene Vinyl Acetate) to modify viscosity of paraffin based fuels and investigated the effect of viscosity on regression rates. Wada et al. in Akita University employed LTP (Low melting ThermoPlastic) as another candidate of liquefying fuels and demonstrated high regression rates comparable to paraffin fuels. Hori et al. in JAXA/ISAS employed glycidylazide-poly(ethylene glycol) (GAP-PEG) copolymers as high regression rate fuels and modified the combustion characteristics by changing the PEG mixing ratio. Regression rate improvement by changing internal ballistics is another stream of research. The author proposed a new fuel configuration named "CAMUI" in 1998. CAMUI comes from an abbreviation of "cascaded multistage impinging-jet" meaning the distinctive flow field. A CAMUI type fuel grain consists of several cylindrical fuel blocks with two ports in axial direction. The port alignment shifts 90 degrees with each other to make jets out of ports impinge on the upstream end face of the downstream fuel block, resulting in intense heat transfer to the fuel. Yuasa et al. in Tokyo Metropolitan University employed swirling injection method and improved regression rates more than three times higher. However, regression rate distribution along the axis is not uniform due to the decay of the swirl strength. Aso et al. in Kyushu University employed multi-swirl injection to solve this problem. Combinations of swirling injection and paraffin based fuel have been tried and some results show very high regression rates exceeding ten times of conventional one. High fuel regression rates by new fuel, new internal ballistics, or combination of them require faster fuel-oxidizer mixing to maintain combustion efficiency. Nakagawa et al. succeeded to improve combustion efficiency of a paraffin-based fuel from 77% to 96% by a baffle plate. Another effective approach some researchers are trying is to use an aft-chamber to increase residence time. Better understanding of the new flow fields is necessary to reveal basic mechanisms of regression enhancement. Yuasa et al. visualized the combustion field in a swirling injection type motor. Nakagawa et al. observed boundary layer combustion of wax-based fuels. To understand detailed flow structures in swirling flow type hybrids, Sawada et al. (Tohoku Univ.), Teramoto et al. (Univ. of Tokyo), Shimada et al. (ISAS), and Tsuboi et al. (Kyushu Inst. Tech.) are trying to simulate the flow field numerically. Main challenges are turbulent reaction, stiffness due to low Mach number flow, fuel regression model, and other non-steady phenomena. Oshima et al. in Hokkaido University simulated CAMUI type flow fields and discussed correspondence relation between regression distribution of a burning surface and the vortex structure over the surface.

• 대한원격탐사학회지
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• 제38권4호
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• pp.343-353
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• 2022

An attempt to derive the surface temperature from the Korea Multi-purpose Satellite (KOMPSAT)-3A mid-wave infrared (MWIR) data acquired over the southern California on Nov. 14, 2015 has been made using the MODerate resolution atmospheric TRANsmission (MODTRAN) radiative transfer model. Since after the successful launch on March 25, 2015, the KOMPSAT-3A spacecraft and its two payload instruments - the high-resolution multispectral optical sensor and the scanner infrared imaging system (SIIS) - continue to operate properly. SIIS uses the MWIR spectral band of 3.3-5.2 ㎛ for data acquisition. As input data for the realistic simulation of the KOMPSAT-3A SIIS imaging conditions in the MODTRAN model, we used the National Centers for Environmental Prediction (NCEP) atmospheric profiles, the KOMPSAT-3Asensor response function, the solar and line-of-sight geometry, and the University of Wisconsin emissivity database. The land cover type of the study area includes water,sand, and agricultural (vegetated) land located in the southern California. Results of surface temperature showed the reasonable geographical pattern over water, sand, and agricultural land. It is however worthwhile to note that the surface temperature pattern does not resemble the top-of-atmosphere (TOA) radiance counterpart. This is because MWIR TOA radiances consist of both shortwave (0.2-5 ㎛) and longwave (5-50 ㎛) components and the surface temperature depends solely upon the surface emitted radiance of longwave components. We found in our case that the shortwave surface reflection primarily causes the difference of geographical pattern between surface temperature and TOA radiance. Validation of the surface temperature for this study is practically difficult to perform due to the lack of ground truth data. We therefore made simple comparisons with two datasets over Salton Sea: National Aeronautics and Space Administration (NASA) Jet Propulsion Laboratory (JPL) field data and Salton Sea data. The current estimate differs with these datasets by 2.2 K and 1.4 K, respectively, though it seems not possible to quantify factors causing such differences.