• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.499-502
• /
• 2009

The auto-ignition tests of hybrid rockets with the concentrated hydrogen peroxide as an oxidizer were presented. Auto-ignition, restartability, and instant ignition were successfully demonstrated by injecting decomposed gases from $H_2O_2$ into paraffin or polyethylene fuels. In addition, much faster response time was demonstrated in case of a paraffin, which was 13 and 30 ms at ignition delay and rise time respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.429-434
• /
• 2012

Ignition delay of micro/nano aluminum particles is caused by aluminum oxide shell. The method of minimizing this ignition delay is proposed in the study. Generating and heating of particles are processed at the same time. As soon as heated particles are produced, they immediately contact with oxygen. Chemical reaction is induced on the contact surface instead of crystallization of oxide shell. Finally particles are ignited. Aluminum particles are generated by laser ablation on an aluminum plate using Nd:YAG pulse laser. Injected particles are confirmed through visualization of particles using scattering method. $CO_2$ continuous laser supplies heat to aluminum plate and generated particles. Trace of burning particles is observed in the experiment.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.20 no.11
• /
• pp.3630-3638
• /
• 1996

An experimental study has been conducted to explore the behaviors of the radiative ignition of polymethylmetacrylate(PMMA) in a confined enclosure such as the ignition delay time, PMMA surface temperature, the ignition location and the ignition process. In addition, the effects of hot wall orientation on the ignition delay and PMMA surface temperature were studied. When the hot wall is located at the bottom, ignition delay time is the shortest. Ignition surface temperature becomes the lowest for the hot top wall case. These are due to buoyancy effect. Since the radiative heat flux of hot wall is rather lower than laser source, the ignition is considered to be controlled by the mixing process. Therefore, the ignition location, where appropriate mixture of fuel and oxygen exists, occurs near the hot wall. The flame propagates along the hot wall where there exists sufficient oxygen.

• Journal of the Korean Chemical Society
• /
• v.45 no.2
• /
• pp.111-115
• /
• 2001

The ignition of NH$_3$-NO-Ar mixtures was examined in the temperature renge of 1675-2391 K behind reflected shock waves. The ignition delay times were measured by monitoring pressure profiles and the OH emissions at 1.0 cm from the end wall. A correlation between ignition delay times and concentrations of gases could be summarized in the form of mass-action expression, To complement the experiment, computer modeling study of the ignition of NH$_3$-NO-Ar mixtures was carried out using various mechanisms reported previously. The sensitivity analysis shows the reaction of NH$_2$+NO${\rightarrow}$NNH+OH is the most important step in the ignition of NH$_3$-NO-Ar mixtures.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.11 no.1
• /
• pp.118-123
• /
• 1987

In relation to the dust detonatians which have imposed severe damages on the industry, the ignitability of various dusts has been investigated on a horizontal shock tube in this study. By using a newly designed air injector, very well-distributed clouds could be obtained. The proper reflected shock conditions have been generated by placing a reflector 1.5cm behind the air injector, which reflected the incident shock wave. The incident shock waves in the range of Mach number 2.8-3.3 created the postreflected shock temperature of 1200-1600K. Experimentally the ignition delay was defined as the time interval between the arrival of a reflected shock wave at dusts and the detection of visible light. Measured ignition delays of dusts investigated were located lower than 1msec under the above conditions. These values are one-order higher than those in the incident shock wave condition. In this type of ignitiion process the following three processes are considered to play important roles; heating of a particle, generation of volatile gas by endothermic devolatilization process, and its diffusion from the particle surface and the formation of stoichiometric mixture with oxidizer.

• Journal of Aerospace System Engineering
• /
• v.17 no.1
• /
• pp.51-58
• /
• 2023

Hypergolic propellants, which can ignite themselves without an ignition source, are difficult to handle due to their corrosiveness and toxicity. Therefore, it is necessary to develop green hypergolic propellants with little or no toxicity. In this study, basic research on green hypergolic ignition propellants was conducted. With 95% hydrogen peroxide as an oxidizer and CNU_HGFv1 as a fuel, ignition and combustion characteristics of propellants were evaluated through a drop test, an ignition test, and a combustion test. As a result of the drop test, the ignition delay time was 9.7 ms. It was 27 ms in the ignition test, which was fast enough to be used as a propellant. As a result of the combustion test, a combustion efficiency of 95.4~98.1% was achieved at about 11.7 bar. It was confirmed that fast and stable combustion was possible without hard start or combustion instability.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.41 no.11
• /
• pp.749-757
• /
• 2017

To cope with the development of alternative fuels and international environmental regulations, this study provides a numerical analysis of the effects of composition and temperature changes of n-decane and ethanol on auto-ignition characteristics. CHEMKIN-PRO is used as the analysis program and the LLNL model is used as the reaction model. The numerical results show that the ignition delay time increases as the mole fraction of ethanol increases for temperatures below 1000 K, where low temperature reactions occur. Because of the high octane number of ethanol, the high percentage of ethanol delays the increase in the concentration of OH radicals that cause ignition. The oxygen concentration in the mixture is changed to apply the exhaust gas recirculation and a numerical analysis is then performed. As the oxygen concentration decreases, the total ignition delay time increases because the nitrogen gas acts as a thermal load in the combustion chamber.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.1 no.1
• /
• pp.64-72
• /
• 1997

An analytical study has been performed to investigate the unsteady ignition characteristics of pulse combustion. In many combustion applications, strain rate of the flow can significantly affect the combustion features; ignition, extinction, and reignition. In the pulse combustion, two jets (hot combustion gases and fresh mixtures) coming from the opposite side of the combustor will collide in the combustor forming a stagnation region where the chemical reaction is suppressed by the strain rate until this becomes below the critical value. In this research, the method of large activation energy asymptotic is adopted with one step irreversible kinetics to examine the ignition response to the periodic variation of the strain rate of flow. The results show the variation of the maximum value of strain rate can determine whether the ignition or extinction occur.

• Proceedings of the Korean Society for Cognitive Science Conference
• /
• 2000.05a
• /
• pp.87-92
• /
• 2000

이 연구에서는 단어를 지각하게 되면 그 단어에 대한 의미가 자동적으로 활성화되고 그림표상까지도 활성화되지만, 그림을 지각하고 난 후에는 의미표상체계는 활성화되지만 단어의 지각적 표상체계는 활성화되지 않는지를 살펴보고자 하였다. 실험 1과 2에서는 지연시간을 달리하여 그림을 지각적으로 처리를 하게 한 후 단어에 대한 점화효과를 보았으며, 실험 3 에서는 그림을 개념주도적 처리를 하게 한 후 단어에 대한 점화효과 및 암묵적 기억과 재인기억을 비교해 보았다. 실험결과 지각적 판단과제에서는 조건간의 아무런 차이가 없었지만, 의미적 판단과제에서는 동일조건과 그림조건에서의 반응시간이 통제조건을 포함한 기타 조건들에서보다 빠른 것으로 나타났다. 이러한 결과는 의미적 표상체계로부터 단어의 지각적 표상체계까지의 상호작용 통로가 존재하지 않으며, 그림자극이 단어자극의 점화효과에 영향을 주는 이유는 동일한 의미적 표상체계의 활성화가 단어자극의 지각적 표상체계까지 확산되기 때문이 아니라, 그림자극에 대한 의미적 표상체계가 활성화되기 때문이라는 점을 시사한다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.15 no.6
• /
• pp.56-62
• /
• 2011

An experimental study on design of a catalytic ignitor was performed to use an ignition source for a small bi-propellant liquid rocket engine which use hydrogen peroxide and kerosene as propellants. In the catalytic ignitor, hot gas of hydrogen peroxide which was decomposed by a catalyst induced autoignition of kerosene. Mass flow rate and O/F ratio for the ignitor were calculated by CEA code. A combustion chamber which had a quartz window and thermocouples was manufactured to determine whether the ignition is successful. Ignition performance was investigated according to exit area of fixed rings and mixture ratio. Results showed that reliable ignition performance was achieved at non-choking exit area of fixed ring and O/F ratio of 6~8.