• 한국안전학회지
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• 제12권1호
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• pp.77-93
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• 1997

The natural convection and combined heat transfer induced by fire in a rectangular enclosure is numerically studied. The model for this numerical analysis is partially opened, it is divided by a vertical baffle projecting from ceiling. The solution procedure Includes the standard k- $\varepsilon$ model for turbulent flow and the discrete ordinates method (DOM ) is used for the calculation of radiative heat transfer equation. In this study, numerical simulation on the combined naturnal convection and radiation is carried out in a partial enclosure filled with absorbed-emitted gray media, but is not considered scattering problem. The velocity vectors, streamlines, and isothermal lines are compared the results of pure convection with those of the combined convection-radiation, the combined heat transfer. Comparing the results of pure convection with those of the combined convection-radiation, the combined heat transfer analysis shows the stronger circulation than those of the pure convection. Three different locations of heat source are considered to observe the effect of heat source location on the heat transfer phenomena. As the results, the circulation and the heat transfer In the left region from heating block are much more influenced than those in the right region. It is also founded that the radiation effect cannot be neglected in analyzing the building in fire.

• Journal of Astronomy and Space Sciences
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• 제19권4호
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• pp.305-318
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• 2002

한반도 상공의 중간 자외선 대기광을 측정하기 위해 3단형 과학로켓(KSR-III)에 탑재될 대기광도계(Airglow Photometer, AGP)가 제작되었다. 대기광도계 비행 모형(FM)은 4-channel로 이루어져 100km~300km 구간의 중간 자외선 영역의 OI 2972${\AA}$, $N_2$ VK(0,6) 2780${\AA}$, $N_2$ 2PG 3150${\AA}$ 대기광과 배경으로 3070${\AA}$을 지평선 방향으로 측정하게 된다. 대기광도계는 광도계 본체, 차폐경(Baffle), 전자제어부, 전원공급기로 구성되어 있다. 광도계 본체는 협대역 간섭 필터를 통해 선택된 파장의 대기광을 직경 2.5cm 렌즈로 초점면에 설치된 실틈(slit)을 통해 자외선 감지용 광전증배관으로 진입시키는 구조로 되어있다. 비행중 영점 측정을 위해 초점면 실틈 뒤편의 회전판에 영점광원을 설치하였다. 차폐경은 저충대기로부터 산란되는 태양광이 광도계로 진입하지 못하도록 성능을 최적화하여 설계 제작되었다. 대기광도계 비행모형의 지상 테스트로서 각광도계의 성능 테스트 및 감응도, 영점 측정 등을 실시하였다. 대기광도개가 미약한 빛을 감응하도록 제작되었기 때문에 국내에서 신뢰도를 갖고 절대 감응도를 결정할 수 없었다. 그러나 대기광도계 각 channel 간 상대 감응도 측정값은 안정되게 측정되었기 때문에, 추후 로켓 비행시 측정한 자료를 신뢰성있게 분석할 수 있을 것으로 기대된다.

• 한국수자원학회:학술대회논문집
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• 한국수자원학회 2012년도 학술발표회
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• pp.593-593
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• 2012

본 연구는 화력 및 원자력 발전소로 취입된 냉각수(circulating and essential service water)가 복수기로부터 온배수 형태의 개수로 흐름으로 표층배수 될 경우 수온을 저감시키기 위해 주입하는 희석수(by-pass cooling water)와의 혼합효과의 효율성을 증대시키고, 불리한 수리현상을 야기하지 않으며, 경제적인 배수로 구조물을 고찰하기 위한 목적으로 시도되었다. 배수로 구조물 내 온배수와 희석수가 혼합되는 구간을 혼합지(mixing basin)라 하는데, 본 과업에서는 ${\bigcirc}{\bigcirc}$발전소의 배수로 구간 중 혼합지를 대상으로 FLOW-3D$^{(R)}$를 이용한 3차원 수치모형을 구축하고, 총 9개에 해당하는 각 대안별 현상을 분석하고 비교하였다. 각 대안들의 차이점은 배수로에 설치되는 보조구조물들의 형상과 배열 등이며, 복수기로부터 나오는 배출수의 수온은 $42^{\circ}C$, 희석수는 $35^{\circ}C$이고, 본 과업의 주요 관심대상 물리량은 유속과 온도이다. 배수로에 아무런 보조 구조물이 없는 형태인 기본 계획안을 검토한 결과, 평균 $3.31^{\circ}C$의 수온강하가 이루어졌으나, 우안 쪽으로 강한 흐름이 발생하여 수온의 좌우편차가 $4.61^{\circ}C$ 가량 발생하는 것으로 나타났다. 기본 계획안의 검토결과를 보완하기 위한 대안으로 연직 흐름의 소산을 위해 고안된 잠형 소파블록(baffle block) 설치안은 평균 $3.06^{\circ}C$의 수온강하가 이루어지고 $4.44^{\circ}C$의 수온 좌우편차가 발생했다. 지그재그(zigzag) 형태의 흐름을 만들어 혼합효과를 올리기 위한 미로형 수제(labyrinth groin) 설치안은 평균 $5.33^{\circ}C$의 수온강하가 이루어지고, $1.43^{\circ}C$의 수온 좌우편차를 보여줘 검토했던 대안들 중 가장 좋은 결과를 보여주었다. V자 배열 소파블럭(deformed block) 설치안은 연직 및 수평방향의 소산을 기대했으나 평균 $3.00^{\circ}C$의 수온 강하와 $4.41^{\circ}C$의 수온 좌우편차를 나타냈다. 벤츄리(Venturi) 형태의 흐름을 발생시키기 위한 병목형(bottleneck) 수로안은 평균 $3.18^{\circ}C$의 수온강하와 $3.94^{\circ}C$의 수온 좌우편차, 흐름의 소산과 흐름방향을 변화시키기 위한 와형 수제(swirl groin) 설치안은 평균 $2.24^{\circ}C$의 수온강하와 $1.48^{\circ}C$의 수온좌우편차, 우안 흐름을 지연시키기 위한 물방석(water cushion) 수로안은 평균 $3.03^{\circ}C$의 수온강하와 $4.50^{\circ}C$의 수온 좌우편차, 우안의 흐름을 좌안으로 보내기 위한 분사형(injector) 수로안은 평균 $3.13^{\circ}C$의 수온강하와 $4.45^{\circ}C$의 수온 좌우편차, 우안의 흐름을 막기 위한 외팔형 수제(cantilever groin) 설치안은 평균 $3.11^{\circ}C$의 수온강하와 $3.02^{\circ}C$의 수온 좌우편차가 발생하는 것으로 나타났다.

• 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.