• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.74-77
• /
• 2009

Ignition performance tests were performed to develop a catalytic ignitor which used hydrogen peroxide and kerosene. Ignition characteristics were investigated by exit area of the catalytic bed, shape of kerosene injector and lead time of purge gas. The results showed that exit area of catalytic bed must be enough for non chocking condition and kerosene must be sprayed with swirl in the middle of catalytic bed. Also in case without preheating of catalytic bed, hydrogen peroxide must be leaded by 3sec, and purge gas must be supplied simultaneously or lately with kerosene.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
• /
• v.23 no.6
• /
• pp.24-30
• /
• 2009

We compared 3 kinds of ignitor characteristics and represented the procedure in order to turn the HID lamp on. Also, we analysed the cable characteristic based on the length between ignitor and the HID lamp and proved it theoretically. In practice, the ignition voltage contains a lot of problems because it is easily changed by the structure of ignitors, cable length and characteristics. In this paper, therefore, 3 ignitors, which are LC resonant typed, arc-gap circuit typed and drive frequency variable typed, have simulated and analysed with the 25[m] cable length. After careful consideration of comparisons made of all the ignitors' and cables' characteristics, a number of possible solutions were finalized.

• Proceedings of the Materials Research Society of Korea Conference
• /
• 1994.05a
• /
• pp.101-101
• /
• 1994

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.21 no.1
• /
• pp.36-48
• /
• 1997

In order to establish the ignition system for lean burn, the influence of the number of spark plug, spark times and spark intervals on discharge pattern of spark energy on ignitability and combustion characteristics were evaluated. It showed that, ignitability remarkably increased with the case of multiple spark ignition system than with the case of single spark and the lean limit extended fuel/air equivalence ratio by 0.1, the increase of magnitude and lasting time of capacity component and inductance component was multi spark discharge in a row.

• 한국연소학회:학술대회논문집
• /
• 2003.12a
• /
• pp.139-143
• /
• 2003

Study on the ignition characteristics of combustor and gas generator for LOx-kerosene liquid rocket engine was performed experimentally through a series of combustion tests of sub-scale engine combustor and gas generator. Characteristic of gas-torch ignitor based on gaseous methane and gaseous oxygen was compared with hypergolic ignition using propellant tri-ethyl-aluminium. Gas-torch ignitor showed good performance on igniting sub-scale liquid rocket engine combustor and gas generator. It was observed that the ignition delay is also affected by the extent of nitrogen in the combustion chamber.

• Journal of Industrial Technology
• /
• v.27 no.B
• /
• pp.9-14
• /
• 2007

In this paper, four types of igniters were modeled and their characteristics were researched. And then we analyzed and experimented the effect on the control IC operation in this system. Due to the high ignition voltage, the DC power line on control IC is contaminated with the impulsive noise voltage. So the control IC operation is stopped. Therefore we have found that contamination of DC power noise is reduced by shielding, grounding pattern, and filtering method. We showed that the experimental results are agreed with the theoritical value obtained by the four types of ignitor models.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.05a
• /
• pp.202-205
• /
• 2010

Auto ignition of hybrid rocket using $N_2O$ catalytic decomposition was studied in the present study. The hybrid rocket consists of catalytic igniter, solid fuel, combustor, and nozzle. The Ru/$Al_2O_3$ catalyst for $N_2O$ decomposition was synthesized by an impregnation method, and $N_2O$ conversion as reaction temperatures was measured. The temperature change of the catalytic ignitor was measured at the operating condition, and the possibility for the auto ignition of hybrid rocket was validated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.730-733
• /
• 2017

An ignitor for the initiation of burning propellants becomes one of the most critical components for the operation of liquid rocket engines. The important phenomenon of the igniter is thermoacoustic resonance. This paper mainly includes experimental results on thermoacoustic resonance phenomenon from distance between nozzle and resonance tube. The ultimate goal is to develop an ignitor capable of multiple ignitions based on research results about the usage of the thermoacoustic resonance phenomenon.

• The Transactions of The Korean Institute of Electrical Engineers
• /
• v.58 no.10
• /
• pp.1947-1953
• /
• 2009

Metal halide (MH) lamps have been largely used due to high luminous efficiency, good color rendering, and long life. Since the metal halide lamps have problems of high ignition voltage and acoustic resonance. Thus, the design of ballast is very difficult for engineers. This paper proposes prototype of electric ballast in order to solve above two problems. The proposed electric ballast is consisted of EMI filter, full wave rectifier circuit, active PFC, DBI(Dual Buck Inverter), dimming circuit and ignitor circuit. The DBI supplies both rectangular voltage and current to the lamp. As the result of the experiment, the acoustic resonance was eliminated and the ignitor circuit was designed to generate high ignition voltage than 5kV. It makes the dimming circuit possible to control the lamp power in range between 230W and 350W.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.117-119
• /
• 2017

The multi-stage catalytic igniter for hybrid rocket auto ignition is described in this paper. After charging the catalyst and pre-heating the first stage, the $N_2O$ was supplied at the first stage with the low mass flow rate, and then the $N_2O$ with the high flow rate was supplied into the second stage. Even though the $N_2O$ flow rate was high, it was decomposed by supplying the high temperature gas which was evolved from the $N_2O$ decomposition in the first stage. This multi-stage ignitor resulted in the decrease of the ignition time in comparison with the previous ignitor, and confirmed the possibility of $N_2O$ decomposition with the high flow rate using the multi-stage catalytic-ignition system.