• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.12-12
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• 2000

우리 나라는 일본상공의 비행을 피하기 위하여 제주도와 남해안 근해로 발사장 선정이 국한되는 지정학적인 위치로 볼 때 발사장 선택에 제한이 없는 공중발사에 대한 가능성 연구가 필요한 시점에 있다. 본 연구는 우리 나라와 같은 분단 된 특수상황 그리고 지정학적 위치에서의 발사장을 고려한 우주 발사체 개발의 필요성에 따라 F-4에 장착 가능한 3단형 공중발사 로켓을 설계하고 1/3의 축소 모형을 제작하였다. 2kg의 payload를 갖는 발사체의 1단은 LRM ( Lox/kerosene )을 사용하였고 2, 3단은 SRM ( HTPB/AP/Al )을 사용하였으며 발사고도는 11-l2km 상공에서 F-4에 의해서 발사되고 31km지점에서 1단 분리가 이루어지며 62km지점에서 2단 분리와 nose fairing을 분리하게 된다. 전장은 6.85m 이며 전체 무게는 560.6kg 이고 전체 발사체 시스템의 CAD 도면은 아래 그림 1과 같이 주어져 있다. 그림 2에서는 F-4E phantom의 장착성을 검토해 본 결과 장착이 가능함을 알 수 있었으며 추진제 양의 감소로 크기를 대폭 줄일 수 있었다.

• Journal of computational fluids engineering
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• v.8 no.3
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• pp.56-65
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• 2003

A numerical procedure for analyzing the heat transfer in a regenerative cooling passage of liquid rocket has been developed. The thermal analysis is based on the numerical model of Naraghi〔1〕. The thermodynamic and transport properties of the combustion gases are evaluated using the chemical equilibrium composition. The pressure and heat flux obtained by the isentropic relation are in good agreement with the result of Navier-Stokes equations. The effect of design parameters on heat transfer is addressed for the pressure loss and temperature variation. Also, their constraints in designing the cooling passage are recommended. Finally, in a heated rectangular duct, the effects of secondary flow on heat transfer are scrutinized by the nonlinear k- e -fu of Park et at.〔2〕.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.12-12
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• 1998

무기체계의 추진체로서 고체 로켓트 추진기관이 제작의 용이성, 구조의 간단성, 이에 따른 저렴한 제작비, 그리고 고 신뢰도 확보가능 등의 여러 장점으로 대부분의 현존 전술 유도무기에 채택되어 사용되어 오고 있으나 대응, 방어 무기체계의 빠른 발전으로 이에 따른 새로운 추진기관의 유도무기체제가 요구되고 있다. 램제트 기관은 공기흡입추진기관으로 상대적으로 높은 비추력(1000-2000s)과 추력 중량비(∼20)을 가지며, 이로 인해 기존의 로켓 엔진에 비해 4-5배의 성능을 낼 수 있으며, 초음속 장거리 비행에 적합하다며, 또한 높은 속도영역까지 운용가능하고 구조가 비교적 간단하다.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.142-150
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• 2003

Turbulent flows and related heat transfer in a square heated duct is investigated by a turbulence model and a large eddy simulation. The cooling channel of calorimeter is modeled to the square duct. The nonlinear k-ε-fμ model of Park et al. [3] is slightly modified and their explicit heat flux model is employed. The Reynolds number is varied in the range 4000≤Reｂ≤20000. The heat transfer is closely linked to the secondary flows which driven by the turbulent motion. Its magnitude is 1~3% of the mean streamwise velocity. The relation of Nu~Re0.8Pr0.34 is validated by comparing with the predicted Nu of k-ε-fμ model. Finally, the coherent structures and thermal fluctuations are scrutinized.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.3
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• pp.35-42
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• 2007

Acoustic damping induced by gap width between baffled injectors is investigated numerically, which are installed to suppress pressure oscillations in a model rocket combustor. The previous work reported that the baffled injectors show larger acoustic damping with the gap width between injectors. It is simulated numerically and its mechanism is examined. Damping factors are calculated as a function of gap width and it is found that the optimum gap is 0.1 mm or so. For understanding of the improved damping induced by the gap, dissipation rate of turbulent kinetic energy and vorticity are calculated as a function of the gap. Both parameters have their maximum values at the specific gap and especially, the dissipation rate has the same profile as that of damping factor. It verifies that the improved damping made by the gap is attributed to the increased acoustic-energy dissipation.

• 유체기계공업학회:학술대회논문집
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• 2000.12a
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• pp.318-324
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• 2000

액체로켓인 KSR-III는 점화시 및 연소실 압력의 이상 저하시 추진제가 지나치게 많이 공급되는 것을 막기 위하여 케비테이션 벤튜리를 사용한다. 본 연구에서는 Fluent가 제공하는 케비테이션 모형을 사용하여 케비테이션 벤튜리 내부의 공동 발생과 이에 따른 유량제어 현상을 해석하였다. 케비테이션 모형은 공동의 붕괴를 효과적으로 예측하지 못하는 단점이 있지만 벤튜리를 통과하는 유량은 공동이 발생하는 위치에서 유효 유로 감소에 의하여 제한되므로 유량제어 현상을 성공적으로 관찰할 수 있었다. 결과로서 벤튜리 상류의 압력이 일정하게 유지될 때 하류의 압력 변동에 대하여 유량이 변화하지 않음을 확인하였다. 상류의 압력이 24.1bar로 일정하게 유지되고 벤튜리에서 압력차이가 3bar 이하일 때 공동은 발생하지 않았다. 압력차가 6bar 이상일 때 공동이 발생하며 (압력차 6bar인 경우와 비교하여) 9bar, 12bar의 압력차에 대한 유량 증가는 각각 $5\%,\;7\%$에 그쳐 주어진 작동조건에서 벤튜리로 유량제어가 가능하였다.

• Journal of Gifted/Talented Education
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• v.24 no.3
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• pp.421-444
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• 2014

In STEAM education, contents that has been extracted from a variety of areas, so it can work closely and systematically. Therefore STEAM education requires systems thinking that can be grasped effectively these different disciplines. The purposes of this study are to develop a STEAM program based on systems thinking, and apply the program to the secondary science gifted student in order to investigate the educational effect. A model of the Program developed from previous research and theoretical contents of systems thinking and STEAM. A draft of the STEAM program was developed on the theme of "rocket". A total of 113 students was participated in this study. 100 seventh and 13 eighth graders were enrolled at seigy. A single group pre-post test paired t-test was conducted on them in systems thinking skills. Result of applying the program to the students as follows. The systems thinking ability was improved after the application of the program. 'Mental Model', 'Personal Skill', 'Team Learning', and 'System Analysis', 'Shared Vision' emerged for both improved significantly. In conclusion, the STEAM program based on system thinking improves students' systems thinking skills. This program of results can be helpful in cultivate human resources with the problem solving ability based on system thinking and STEAM literacy by used in public education curriculum.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.1
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• pp.55-63
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• 2012

The turbulent flow characteristics in a coaxial injector were investigated by the nonlinear $k-{\varepsilon}-f_{\mu}$ model of Park et al.[1] and large eddy simulation (LES). In order to analyze the geometric effects on the scalar mixing for nonreacting variable-density flows, several recessed lengths and momentum flux ratios are selected at a constant Reynolds number. The nonlinear $k-{\varepsilon}-f_{\mu}$�� model proposed the meaningful characteristics for various momentum flux ratios and recess lengths. The LES results showed the changes of small-scale structures by the recess. When the inner jet was recessed, the development of turbulent kinetic energy became faster than that of non-recessed case. Also, the mixing characteristics were mainly influenced by the variation of shear rates, but the local mixing was changed by the adoption of recess.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.3
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• pp.1-8
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• 2010

Acoustic tuning of quarter-wave resonator is investigated numerically to suppress combustion instability in liquid rocket engines. A model combustion chamber is adopted. First, basic acoustic characteristics are examined and acoustic damping is pursued by quarter-wave resonators. Next, for frequency tuning of the resonators, thermodynamic properties inside the acoustic resonators are estimated based on the numerical data. Maximum damping capacity is obtained when the resonators are designed to have the optimum length calculated with the properties. But, damping capacity induced by the resonators with the same length is comparable with it.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.25-32
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• 2020

A numerical study on combustion instabilities in a model combustor was conducted with various momentum flux ratios. Five ratios are calculated based on an actual operating condition of rocket engine. As momentum flux ratio increases, the spreading angle on the injector outlet decreases. And, as increase of axial momentum flux, pressure fluctuation decreases inside the combustor. By using dynamic mode decomposition method, the acoustic modes inside the combustor are identified. Combustion stabilities are analyzed by comparing the damping coefficient of the 2^nd longitudinal mode.