• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.228-231
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• 2011

Burning rate of a propellent is an essential factor when designing a propulsion system. In order to come up with burning rate, first we need to design and build propellent grain to get neutral pressure curve. Then check the pressure with ground test and calculate the burning rate using burning rate equation. This burning rate is then compared to the burning rate of a propellent which was resulted from making a standardized specimen and combusting it using a strand burner. An accurate burning rate is calculated after comparing those two burning rates. For this study, compact propulsion system was designed, produced, tested and analyzed in order to get burning rates, an essential factor in propulsion system design, in an effective way.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.26-31
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• 2009

Three Lox pumps and one fuel pump are manufactured for turbopump real-propellent tests and water tests of the pumps are performed in order to estimate the performance characteristics of the pumps. According to the test results, the test region(flow ratio, cavitation number) of the pumps at the water tests cover the operating region at the real-propellent tests and also all the pumps satisfy the design requirement. The head of the Lox pumps shows a 2% difference among them due to the internal geometry, but the efficiency and overall cavitation performance are almost same. It is found that the fuel pump has a similar head and efficiency compared with the previous model of the same internal geometry, while it has a little inferior cavitation performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.05a
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• pp.149-154
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• 1996

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2011.07a
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• pp.451-453
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• 2011

본 논문에서는 챔퍼 디스턴스 매칭(chamfer distance matching)를 이용하여 위성 영상 상의 북한군 자주포진지(self-propellent artillery position)를 매칭하는 기법을 제안한다. 먼저 입력되는 위성 영상을 잡음환경에 강인한 가우시안-라플라시안 연산자를 이용하여 에지(edge)를 추출한다. 추출된 에지 영상의 각 픽셀에 대해 가장 가까운 에지까지의 거리를 나타내는 거리 변환(distance transform) 영상을 생성한다. 템플릿 영상은 다양한 자주포진지 영상에서 샘플링된 영상으로 에지를 추출한 후 거리 변환을 거친다. 마지막으로 템플릿 영상을 입력된 거리 변환 영상에 윈도우 슬라이딩(window sliding)하여 최소값의 가지는 위치를 구한다. 제안 기법은 잡음에 강인한 가우시안-라플라시안 연산자를 사용하여 기상조건에 의한 입력 영상의 편차에도 효율적인 매칭이 가능하다. 또한 에지 기반의 챔퍼 매칭을 이용하기 때문에 비 균일 조명 환경에서도 강인한 매칭이 이루어진다. 전산 모의 실험에서 제안 알고리즘은 입력 위성 영상 상의 자주포진지를 적은 계산량으도 신뢰있게 매칭함을 보여준다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.29-32
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• 2009

This study is for development combustion test facility of liquid rocket engine system using hydrogen peroxide/kerosene as propellent. For this new facility, we construct thrust measure system, propellent supply system, control and data acquisition system. To perform 200N liquid rocket engine combustion test, operation scenario and sequence were designed. Result of combustion test propellents were supplied to engine stably and confirm of development combustion test facility very well.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.167-176
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• 2014

The pyrovalves are widely used in aerospace industry for the opening and closing of flow channel due to the light-weight, high reliability and zero-leakage. In the United States, the loss of some spacecrafts using hydrazine as the propellent were proven by the blowby. Blowby is defined as the leakage of pyrovalve ignition combustion gas to the flow channel. Since then, the interference fit was applied for the sealing of piston to prevent the blowby. In this study, literature survey on pyrovalve technology is summarized mainly for AIAA papers. Common problems, improvement method, and performance comparisons of pyrovalves are also presented.

• 한국연소학회:학술대회논문집
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• 2014.11a
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• pp.311-313
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• 2014

High pressure combustion with multiphase--liquid, gas, and supercritical phase--mixtures are widely used technology in the high efficiency liquid propellent rocket engine. This is the typical characteristics differentiate from the combustor of conventional air-breathing engines. Therefore, successful research of high pressure combustion at supercritical condition is essential to develope a high efficiency liquid rocket engine. Numerical studies have been carried out to explore capabilities of numerical method for LOx-CH4 non-premixed flames at high pressure. In this paper, corresponding numerical results are presented and compared with experimental result of MASCOTTE facility.

• Journal of ILASS-Korea
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• v.21 no.1
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• pp.13-19
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• 2016

Atmospheric spray characteristics were experimentally compared between liquid-gas and liquid-liquid sprays of a pintle injector. In order to study spray characteristics, water and air were used as the simulants and the visualization technic was adopted. Spray images were acquired by using a backlight method by a high-resolution CMOS camera. As a result, when the pintle opening distance increased, liquid sheets became unstabled and fluttering droplets increased. In the liquid-gas case, the breakup performance increased as the pressure of gas injected from the annular orifice increased. In the liquid-liquid case, atomization efficiency decreased as the pressure of liquid injected from the annular orifice increased. Spray angles presented a similar trend between two cases. At the same momentum ratio, the spray angle of liquid-liquid case was lower than the angle of liquid-gas case.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.148-154
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• 2004

As a rocket propellent of hydrocarbon fuels, the characteristics of liquefied natural gas was evaluated with the viewpoint of the constituents and content, the cooling performance as a coolant, and characteristic velocity and specific impulse as parameters of the engine performance. Content of methane was a principal factor to determine the characteristics as a rocket propellant and more than 90 % of it was needed as a fuel and coolant in the regenerative cooled liquid rocket engine. Some constituents of the liquefied natural gas can be frozen by the pre-cooling of the pipe lines, therefore they can be a factor disturbing the normal working of engine. In case the content of methane is around 90% in the liquefied natural gas, a normalized stoichiometric O/F mixture ratio of 0.75 is suggested for a nominal operation condition to get the maximum specific impulse and characteristic velocity.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.181-189
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• 2010

개방형 액체로켓엔진 시스템에 대한 동특성 예측 프로그램을 작성하였다. 이 프로그램을 통해 얻은 펌프 시동 시 시간에 따른 압력 및 유량 변화 결과를 수류실험장치를 구축하여 실험적으로 검증하였다. 수류실험장치는 실제 액체로켓엔진 추진제 공급 계통에서 구성품의 형태와 배치위치, 가스발생기와 주연소실로 분기되는 유량비를 기준으로 모사되었다. 측정 시 관로가 채워진 상태에서 펌프를 시동하였으며 펌프는 전동기로 구동된다. 동특성 예측 프로그램의 작성을 위해 구성품별 동특성 모델링을 수행하고 엔진 시스템을 기준으로 각 모델링을 순차적으로 통합하였다. 구성품의 동특성 파라미터를 측정 반영하였고 압력 밸런싱을 통해 수렴 조건이 결정된다. 수렴된 밀도와 유량을 가지고 다음 시간에서의 초기 입력 값으로 대체하여 계산을 수행하였다. 천이 작동 상태에서 엔진 시스템 내의 물리량 변화를 전산 예측과 더불어 실험적으로 측정하고 비교하였다.