• Journal of Industrial Technology
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• v.30 no.A
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• pp.75-81
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• 2010

We described the operating principles of two different type of igniters for lightning of Ceramic Metal Halide Lamp(CMHL) and also provide some useful comparisons. One is for magnetic ballast, the other one is for electronic ballast which operates lamp by low-frequency square-waveform. Ignition voltage of lamp depends on the structure of igniter, such as the length and electrical characteristics of cable, which make troubles for ignition in real sites. Therefore, we measured and analyzed ignition voltages from igniters which are used in magnetic and electronic ballast in cables at a distance of 5 meters between a lamp and a igniter to suggests an applicable solution in real sites.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.416-417
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• 2017

In this study, Three-Dimensional igniter modeling and computational Analysis for PMD internal flow analysis have been conducted. The igniter modeling used the lumped parameter method and the computational analysis has been performed in conjunction with the commercial program STAR-CCM+. The result of computational analysis has been compared with those of CBT and PMD experiments.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.301-306
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• 2008

A pyrogen igniter was designed to satisfy the required condition of kick motor system for the space launch vehicle. We analyzed the ignition characteristics and performed the combustion tests to verify the internal ballistic performance. In the design process, the arc-image test was carried out to find the sufficient heat flux as varying the initial pressure from 10 to 700kPa. The analysis indicated that the initial pressure condition would delay ignition time within a range from 100 to 500ms. The combustion test with an inert chamber was also performed to understand the ignition characteristics with the variation of the initial pressure of free chamber volume. Finally, we confirmed that the igniter could provide the acceptable energy to ignite the propellant of kick motor at the ground test. The result of the ground tests showed that the ignition delay time was within the design range at the atmospheric pressure condition.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.112-117
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• 2004

This work is on numerical and experimental studies on the new type igniter using aerodynamic energy. The aerodynamic igniter consists of a nozzle and a resonance tube. The supersonic jet from a nozzle coming into the resonance tube generates pressure oscillation between the nozzle and the resonator. This oscillation changes the kinetic energy to thermal energy in the resonator under a certain condition. In this study, sonic and supersonic nozzles were tested in two different resonators, results has been compared. And geometrical optimum values of a supersonic nozzle has been suggested to reduce aerodynamic loss and friction in the expanded surface of the nozzle.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.21 no.8
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• pp.20-26
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• 2007

A high ignition voltage is required to turn on the metal halide discharge(MHD) lamp. The igniter with high frequency resonance circuit needs more devices, such as sidac, arc-gab, SCR(silicon control rectifier), DIAC and so of which increase the complexity and decrease the reliability of the ignitor. This paper analyzes and designs a simple LC resonance type igniter without any extra switch devices. Moreover, the igniter will not influence the steady-state operation of the lamp. Through the mathematical analysis, the computer simulation and experiment results of a prototype ballast for 1[kW] metal halide lamp(MHL) lamp, the proposed igniter was verified to be effective.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.85-91
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• 2012

This paper describes the results of study on reaction of insensitive igniter in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. The Slow Cook Off(SCO) test following the regulation of MIL-STD-2105D was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The auto-ignition temperature measured was approximately $140^{\circ}C$ and it corresponded to Type V(Burning) reaction in SCO test, while the temperature by Kissinger equation was calculated to be $165.5^{\circ}C$.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.3
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• pp.76-82
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• 2013

Survey on the hypergolic igniter and its rupture discs for liquid rocket engines was performed. The patents of the igniters for US MC-1 and Russia RD-170 engines and the discs for NASA's space vehicle were analyzed. The types of discs and holders, characteristics related to rupture pressures and working fluids, and ASME standards of the discs were examined. Also, survey on structural analyses of the disc were performed. Typical design features and experimental results of the currently developing igniter by the authors were presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.125-128
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• 2010

A pyrotechnic igniter with a relatively simple configuration was developed to secure the stable and reliable ignition of the gas generator in space launch vehicles. It was designed not only to provide a sufficient heat flux for the propellant ignition but also to ensure a structural safety under the conditions of very high temperatures and pressures. The burning tests of the igniters have been performed to decide several design parameters, and consequently the performance tests have proved that the pyrotechnic igniter developed in this study meets the design requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.213-218
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• 2012

Survey on the hypergolic igniter and rupture disc for liquid rocket engines was performed. The patent of the igniter for US MC-1 and Russia RD-170 Engine and the disc for NASA's space vehicle were analyzed. The types, characteristics, performances, design parameters and ASME standards of the disc are examined. The performances have manufacturing tolerance, reverse pressure, flow disturbance, fragmentation, material, working fluid and operating ratio. Also, survey on structural analyses of the rupture disc were performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.520-526
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• 2012

The appearance of the negative differential pressure(NDP), in which the shot base pressure is higher than the breech pressure, indicates that a potential damage on the gun system is increased. In order to safeguard the gun system, the igniter must be designed to minimize the NDP during the firing process. From this reason, the effect of igniter's burning rate on the NDP of the interior ballistics has been investigated through the numerical simulations. The NDP has been increased with increment of the coefficient in the burning rate of the igniter. A sudden change of the chamber pressure has been shown in case of using a singular coefficient.