• 천문학회지
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• 제34권1호
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• pp.35-40
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• 2001

For the planned experiments of Korea Sounding Rocket-III (KSR-III), we have constructed a model of MUV dayglow in the mid-latitude. The model computes relative intensities of individual emission lines in the Vegard-Kaplan and 2PG band systems of $N_2$ in the wavelength range of 2500-3500${\AA}$. In addition to the emission lines, solar scattered continuum was computed by an extended LOWTRAN7 code, in which we have included solar scattering in altitudes higher than 100 km by using MSIS90 thermosphere model. Ratios among vibrational bands of VK and 2PG system, were computed from the observed MUV dayglow spectra of Cleary et al. (1995). The model provides MUV dayglow intensitiy profiles with a wavelength resolution of 3.13${\AA}$ as a function of altitude. The computed intensity profiles have been utilized in designing the KSR-III airglow photometers.

• 한국유체기계학회 논문집
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• 제6권4호
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• pp.50-57
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• 2003

The hydraulic performance analysis of a turbopump with an inducer for a liquid rocket engine was performed using three-dimensional Navier-Stokes equations. A simple mixing-plane method and a full interaction method were used to simulate inducer/impeller interaction. Two methods show almost similar results due to the weak interaction between the inducer and impeller since the inducer outlet blade angle is lather small. But, when the inducer and the impeller are closely spaced near the shroud region, flow angles at the impeller inlet show different results between two methods. Thus, the full interaction method predicts about $2\%$ higher pump performance than the mixing-plane method. And the effects of prewhirl at the impeller inlet are also investigated. As the inlet flow angle is increased, the head rise and the efficiency are decreased. The computational results are compared with measured ones. The computational results at the design point show good agreements with experimental data, however under-predicts the head rise at high mass flow rates compared to the experiment.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.89-92
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• 2009

고농도 과산화수소를 추진제로 이용하는 연구가 활발해짐에 따라서 고농도 과산화수소의 국내 생산을 위한 과산화수소 증류에 관한 연구가 필요하게 되었다. 과산화수소의 열분해를 막기 위하여 진공 증류법을 이용하였으며, 증류 압력은 Raoult's law를 이용하여 $40^{\circ}C$ 이하에서 증류가 이루어 질 수 있도록 30 torr로 선정하였다. 실험을 위한 변수로는 증류 온도를 선정하였으며, 증류에 걸린 시간과 증류 후에 계산한 수득율을 성능 평가 대상으로 선정하였다. 실험 결과, 대체로 증류에 소요된 시간이 짧을수록 수득율이 낮으며, 리시버 내의 물의 과산화수소 농도도 더 높은 것을 확인하였다. 또한 비슷한 시간 동안 증류를 수행하였을 경우, 증류 온도가 높을수록 더 높은 농도에 도달하며, 수득율이 낮은 경향을 보였다.

• 천문학회지
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• 제33권3호
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• pp.165-172
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• 2000

A baffle system for an airglow photometer, which will be on board the Korea Sounding Rocket-III(KSR-III), has been designed to suppress strong solar scattered lights from the atmosphere below the earth limb. Basic principles for designing a baffle system, such as determination of baffle dimensions, arrangement of vanes inside a baffle tube, and coating of surfaces, have been reviewed from the literature. By considering the constraints of the payload size of the KSR-III and the incident angle of solar light scattered from the earth limb, we first determined dimensions of a two-stage baffle tube for the airglow photometer. We then calculated positions and heights of vanes to prohibit diffusely reflected lights inside the baffle tube from entering into the photometer. In order to evaluate performance of the designed baffle system, we have developed a ray tracing program using a Monte Carlo method. The program computed attenuation factors of the baffle system on the order of $10^{-6}$ for angles larger than $10^{\circ}$, which satisfies the requirements of the KSR-III airglow experiment. We have also measured the attenuation factors for an engineering model of the baffle system with a simple collimating beam apparatus, and confirmed the attenuation factors up to about $10^{-4}$. Limitation of the apparatus does not allow to make more accurate measurements of the attenuation factors.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.344-349
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• 2003

The purpose of this study is to ascertain the ability of New type cutter using Hybrid Rocket Propulsion System to cut normal carbon steel and also compound metal like stainless steel which cannot be cut by regular oxygen-acetylene cutter. To compare cutting performance, Two different types of experiment with oxygen-acetylene and Hybrid Combustion cutters were performed. As a result, Hybrid Combustion cutter is used to cut both carbon steel and stainless steel with cutting speed of 400mm/min(carbon steel) and 250mm/min(stainless steel). Otherwise, oxygen-acetylene cutter can be used to cut only carbon steel with cutting speed of 500 $^{\sim}$ 700mm/min. The possibility of Hybrid Combustion cutter as a cutting machine was confirmed.

• 한국연소학회지
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• 제5권1호
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• pp.43-53
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• 2000

Experimental studies on determination of the supply leading time of propellants to combustion chamber have been made to stably and efficiently guarantee the ignition process with liquid rocket engine. The propellant used is a Jet A-1 as fuel and a liquid oxygen as oxidizer. Unlike impinging FOOF type of injectors are arranged radially and the designed O/F ratio is 2.34. The present experiment program also includes the stability on the quadlet type of ignitor using the triethylalumimum as an ignition source and injector life tests. Experimental results clarifies that the propellant supply through LOx leading to combustion chamber is proper for stable ignition and combustion processes based on the fuel and oxidizer manifold pressures, combustion chamber pressure, and the variation of flame length from the nozzle exit with lapse time, and shows that the leading supply time of propellants affects the engine performance little. The effect of positioning cooling holes is remarkable to protect the injector face.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제28회 춘계학술대회논문집
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• pp.17-21
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• 2007

초음파를 이용한 로켓 모타의 비파괴검사는 X-ray 검사에 비하여 경제성이 우수하고, 미접착 등의 결함 검출이 우수한 편이다. 그리고 전용 시설 없이 현장에서 실시간으로 검사가 가능하며 방사선 작업에 비하여 안전한 방법이다. 본 논문에서는 초음파 다중반사에 의한 추진제/라이너 미접착 검출 기법에 대하여 실험 및 이론적 모델링으로 분석하였다. 실험 결과, 추진제/라이너 미접착의 신호가 정상 접착과 구별되는 뚜렷한 신호 차이를 보였으며, 실험에서 측정한 신호와 이론적 모델링 신호가 대체적으로 일치하였다.

• 항공우주기술
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• 제5권2호
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• pp.195-204
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• 2006

로켓엔진에서의 고주파 연소불안정을 제어하기 위하여 널리 사용되는 음향공에 대하여, 3차원 선형 음향해석을 수행하여 음향공의 감쇠 능력을 정량화하고자 하였다. 선형음향해석에 의한 공진주파수는 상온에서 고전적 이론에 의한 공진주파수와 약 6% 압력 비에 의한 결과와는 약 10%의 차이를 보임을 확인하였다. 음향공의 개수에 따른 acoustic impedance 특성을 살펴보았고, 본 연구의 결과가 기존의 결과와 정량적으로 유사함을 확인하였다. 기하학적으로 동일한 음향공이 여러 개 설치된 연소실에서는 음향장의 특성과는 상관없이 각각의 음향공이 동일한 acoustic impedance 특성을 보임을 확인하였다. 이로써 acoustic impedance를 도입하여 음향공의 최적 동조를 위한 설계 절차를 확립하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.419-426
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• 2008

As pulse detonation engine(PDE) does not need compression mechanisms such as compressors because self-sustained detonation waves are able to compress propellant gases by their incident shock waves, the PDE can have a simple straight-tube structure. In this study, we propose an autonomous driving valve system of the PDE, which fill premixed gases into the PDE tubes at high frequency with high mass flow rate. The proposed valve is composed of only three parts: a piston, a cylinder, and a spring. This valve system can produce intermittent flow at high mass flow rate, and also can keep stable reciprocal motion by using the propellant-gas enthalpy. When the cylinder content product is assumed to be constant, experimental results of the mass flow rate were approximately equal to the calculation model. We confirmed the autonomous driving valve performance by experiments, and concluded that this extremely simple valve with no electrical power and controller can be used as the PDE propellant supply system.

• Journal of Astronomy and Space Sciences
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• 제17권1호
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• pp.99-106
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• 2000

When a deployed probe is biased by a high positive potential during a space experiment, the payload is induced to a negative voltage in order to balance the total current in the whole system. The return currents are due to the responding ions and secondary electrons on the payload surface. In order to understand the current collection mechanism, the process was simulated with a combination of resistor, inductor, and capacitor in SPICE program which was equivalent to the background plasma sheath. The simulation results were compared with experimental results from SPEAR-3 (Space Power Experiment Aboard Rocket-3). The return current curve in the simulation was compatible to the experimental result, and the simulation helped to predict the transient plasma response to a high voltage during the plasma sheath formation.