• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.517-521
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• 2009

A unsteady internal ballistic analysis model was proposed to take account for the variance of local variance of pressure and velocity along the grain surface of a hybrid rocket combustor. The model of concern in the study was fairly comparable with the test result. The local variation of the oxidizer mass flow rate along grain surface results in chamber pressure, regression rate, and gas velocity change along its flow direction.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.243-246
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• 2008

The combustion characteristic of solid fuel with chamber pressure were experimentally studied in hybrid combustion. This paper was experimental confirmed whether solid fuel affected not only oxidizer mass flux but also chamber pressure. Poly-Ethylene(PE) was used as fuel, GOX was used as oxidizer. Chamber pressure was controled by nozzle throat diameter 6mm and 9mm. In low oxidizer mass flux, solid fuel regression rate was affected not only oxidizer mass flux but also chamber pressure. As well, the regression rate increase as chamber pressure increase with same oxidizer mass flux.

• The Journal of the Acoustical Society of Korea
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• v.35 no.3
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• pp.208-215
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• 2016

To control and improve a combustion behavior of an engine, various studies for the in-cylinder pressure have been consistently carried out. In this paper, the level of the combustion noise for a diesel engine is estimated from the in-cylinder pressure and defined as the combustion noise index. The combustion noise index is calculated from the FFT(Fast Fourier Transform) of the in-cylinder pressure and its validity is verified. The control system based on the combustion noise index is developed and implemented in a vehicle. A number of injection parameters are controlled to meet the desired combustion noise index, and the combustion noise of a vehicle is improved up to 4.0 dB(A) in the specified frequency band.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1992.10a
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• pp.31-35
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• 1992

자동차 관련 소음 및 진동중 엔진과 관련된 것은 흡.배기계 소음과 엔진 자 체의 각 구동 부위 및 연소실 소음으로 대별하여 볼수 있다. 특히 연소실 소 음의 경우에는 엔진 내부에서 발생하는 진동과 압력파가 엔진을 진동시키고, 이러한 엔진의 진동이 방사음을 발생시켜 형성되는 만큼 그 해석 및 공학적 접근 방법이 용이하지 않다. 연소실 소음은 압력의 갑작스런 변화에 의한 폭 발소음과 피스톤과 실린더 벽면의 충돌에 의한 피스톤 슬랩(piston slap)으로 크게 구분할 수 있으며 압력이 높지 않고 압력의 변화가 빠르지 않을 경우 에는 피스톤 슬랩이 기계적 소음의 주 원인이 되는 것으로 알려져 있다. 본 고에서는 피스톤 슬랩에 의한 진동 현상을 예측하기 위한 이론적 접근 방법 을 제시하고 이의 타당성을 검증하기 위한 실험적 방법을 제시하고자 한다. 또한, 피스톤과 실린더의 간극 진단을 위해 슬랩 신호를 이용하는 방법에 대 해 살펴보고, 피스톤과 실린더의 충돌 속도를 통해 슬랩 신호를 줄이기 위한 엔진의 설계 방법에 대해 살펴보고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.6-6
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• 1999

액체 로켓 엔진은 추진기관 공급 시스템으로 작동이 된다. 추진기관 공급 시스템에는 유공압장치 및 각종 배관, 필요한 압력과 유량을 연소실과 가스발생기로 공급하는 시스템, 엔진의 점화 및 정지, 발사체의 사용 목적에 따라 부과되는 기능을 수행하기 위한 장비들이 포함된다. 공급시스템은 크게 가압가스를 이용하는 방법과 터보펌프를 이용하는 방법의 두 가지로 나눌 수 있다. 잘 알려진 바와 같이 일반적으로 추력이 큰 로켓엔진의 경우에는 터보 펌프식이, 추력이 크지 않은 경우에는 가압가스 방식이 이용된다. 일반적으로 가압가스 방식은 연소실 압력이 커질수록 추진제 탱크의 압력도 커지므로, 그 두께가 두꺼워져서 비효율적이 된다. 따라서 연소실 압력이 비교적 크지 않은 추력이 약 10t 내외에서 많이 사용되고, 시스템이 터보 펌프식보다 구조가 매우 간단하므로, 작동의 신뢰도는 매우 높다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.3
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• pp.237-243
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• 2010

In this study, the effect of the shape of a pintle(obstacle) on thrust-modulation performance and drag in a pintle rocket was investigated by a cold flow test and by computational fluid dynamics. Pintle movement caused a monotonic increase in the chamber pressure. Thrust generated by the pressure distribution on the pintle body was linearly changed to the chamber pressure, and this thrust was greater than that generated by the nozzle-wall pressure distribution. Because the shock pattern in the nozzle changes with the shape of the pintle body and pressure ratio, the thrust generated by the nozzle-wall pressure is not directly affected by chamber pressure. The drag due to the pintle(obstacle) can be minimized for a fully linear pintle shape, regardless of chamber pressure.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.18 no.1
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• pp.345-350
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• 2017

Downsizing is widely applied to diesel engines in order to improve fuel efficiency and reduce exhaust emissions. Engine sizes are becoming smaller but pressure and temperature inside combustion chambers are increasing. Therefore, research for fuel spray under high pressure and temperature conditions is important. A constant volume chamber which simulates high temperature and pressure likely to be found in diesel engines was developed in this study. Pressure and temperature were increased abruptly because of ignition of the pre-mixture in the constant volume chamber. Then pressure and temperature were gradually decreased due to the heat loss through the chamber wall. Fuel spray occurred when temperature and pressure were reached at the target condition. In this experiment, the temperature condition should be exactly defined to understand the relation between fuel evaporation and ambient temperature. A fast response thermocouple was developed and used to measure the temporal and spatial temperature distribution during the combustion process inside the combustion chamber. In the results, the core temperature was slightly higher than the bulk temperature calculated by the gas equation. Ed-note: do you want to say 'ideal gas equation'? This was attributed to the heat transfer loss through the chamber wall. The vertical temperature deviation was higher than the horizontal temperature deviation by 5% which resulted from the buoyancy effect.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.261-264
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• 2008

This study experimentally examines combustion characteristics of a hybrid rocket in which solid paraffin is used as a fuel, while oxidizer is pure oxygen. Especially, the experiment investigates the effects of chamber pressure and configuration of fuel grain. The pressure inside the combustion chamber is varied by changing a flow rate of oxidizer. The regression rate is observed to increase as the chamber pressure does. There also exists the effects of shape of fuel grain on thrust. Characteristic of paraffin hybrid rocket changes with shape of fuel grain. When there is a room near the injector, thrust increases. On the other hand, the room near the nozzle does not contribute to thrust increasement.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.163-167
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• 2008

This paper presents pressure fluctuation characteristics of a 30 ton-f class liquid rocket engine combustor. Combustion stability of the combustor was evaluated using the results 46 firing tests performed with a varying O/F ratio and chamber pressure. The RMS value of pressure fluctuation during the steady state combustion was less than 2.6% of the static chamber pressure, demonstrating static stability of the combustion phenomenon. The decay time of pressure fluctuation caused by forced disturbance of a pulse gun was found to be less than 3.5 msec verifying dynamic stability of the combustor.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.1
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• pp.9-15
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• 2012

An unsteady internal ballistic performance model was proposed to take account for the variance of local regression rate along the grain port of a hybrid rocket combustor. The characteristic parameters of hybrid rocket motor was investigated. The performance model of concern in the study was fairly comparable with the test result. The combustion coefficients and local burning characteristics of a hybrid rocket motor were evaluated. The local variation of the oxidizer mass flow rate results in the changes of local regression rate, pressure, temperature, and gas velocity to flow direction, which was analyzed quantitatively.