• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.378-382
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• 2008

A 50 N monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. Ninety percent hydrogen peroxide was selected as a propellant, since it is much less hazardous than hydrazine. A scaled down thruster with aluminum oxide loaded with the platinum in the reaction chamber was tested to determine propellant decomposition onto a catalyst. A scaled up 50 N thruster, with a catalyst bed of 3 cm in diameter and 4 cm in length, was evaluated by decomposition efficiency based on temperature, ${\eta}_T$, efficiency of characteristic velocity, ${\eta}_{C^*}$, and measurement of thrust. The performance of a 50 N thruster was 40.5 Newton in thrust, about 100 % in ${\eta}_T$, and 98 % in ${\eta}_{C^*}$, and 125 sec in specific impulse at sea level.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.58-61
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• 2009

The characteristics of nitrous oxide catalytic decomposition were studied to utilize the nitrous oxide as a propellant. The Ru and Pt were selected as nitrous oxide decomposition catalysts and loaded in the $Al_2O_3$ support using an impregnation method. The nitrous oxide conversions as a variation of GHSV and reaction temperature were measured in a tubular reactor. At the low GHSV and high temperature, the conversion was increased, and Ru/$Al_2O_3$ catalyst showed better performance than Pt/$Al_2O_3$ catalyst.

• Journal of Korean Society for Atmospheric Environment
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• v.11 no.2
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• pp.131-136
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• 1995

The experiment for decomposing CFF-113 by a honeycomb catalyst was carried out in this study. Benzene and water were used as decomposing agents. The reaction of decomposition was from 600 .deg.C to 900.deg.C. Benzene was injected at 900.deg.C and then the catalyst was heated to 1100.deg.C by the heat of combustion of it. The electric power of the reactor was turned off when the combustion was started. The reaction temperature, however, was main trained and the decomposition of CFC-113 continued at that time. It was found that the highest decomposition efficiency was 80% at the ratio of benzene/CFC-113 of 20/1 in this experiment.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.407-412
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• 2006

Most of the monopropellant thrusters use catalyst for decomposing hydrazine. The thruster lifetime is determined mainly by catalyst lifetime, which can be investigated by firing tests. For the development of hydrazine decomposition catalyst, Hot-fire test to verify long-life performance of catalyst is required. This study describes the development of test equipment for long duration hot-firing and test/evaluation plan.

• 한국신재생에너지학회:학술대회논문집
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• 2006.06a
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• pp.85-88
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• 2006

A fluidized bed reactor made of quartz with 0.055m I.D. and 1.0m in height was employed for the thermocatalytic decomposition of propane to produce $CO_2$-free hydrogen. The fluidized bed was proposed for the continuous withdraw of product carbons from the reactor. The propane decomposition rate used carbon black N33O as a catalyst. The propane decomposition reaction was carried out at the temperature range of $600{\sim}800^{\circ}C$, paropane gas velocity of $1.0 U_{mf}\;3.0U_{mf}$ and the operating pressure of 1.0 atm. Effect of operating parameters such as reaction temperature, gas velocity on the reaction rates was investigated. The carbon which was by-product of methane decomposition reaction was deposited on the catalyst surface that was observed by SEM. Resulting production in our experiment were not only hydrogen but also several by products such as methane, ethylene, ethane, and propylene.

• 한국신재생에너지학회:학술대회논문집
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• 2007.06a
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• pp.81-85
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• 2007

A fluidized bed reactor is made with quartz. The size of FBR is 0.055 m I.D. and 1.0 m in height. The FBR was employed for the thermocatalytic decomposition of propane to produce hydrogen without $CO_{2}$. The fluidized bed was proposed for the continuous withdraw of product carbons from the reactor. Carbon black DCC-N330 is used to decompose the propane gas. The propane decomposition reaction over carbon black catalyst in a fluidized bed reactor was carried out the temperature range of 600 ${\sim}$ 800 $^{\circ}C$, propane gas velocity of 1.0 ${\sim}$ 4.0$U_{mf}$($1U_{mf}$ = 0.61cm/s) and the catalyst loading of 100 ${\sim}$ 200g. Production of $H_{2}$ such as other reaction temperature, gas velocity, catalytic loading on the reaction rates was investigated. The carbon depositied on the catalyst surface was observed by FE-SEM. The particle size of the carbon black was observed by Particle size analyzer. Resulting production in the experiment was not only hydrogen but also several by-products such as methane, ethylene, ethane, and propylene.

• Journal of Korean Society for Atmospheric Environment
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• v.13 no.4
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• pp.319-325
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• 1997

The catalytic decomposition of CFC-113(1,1,2-trichloro-1,2,2-trifluoroethane) was studied over an activated carbon catalyst in a fixed-bed reactor at the temperature from 300 to 600$^\circ$C, the space velocity (SV) of 1800 $\sim 14400h^{-1}$ and the mole ratio(decomposition agent/CFC-113) of 0.25 $\sim$ 5. In the absence of a decomposition agent, the decomposition efficiency of CFC-113 was low but when a decomposition agent was added to the gas stream, it was dramatically increased with the increase of temperature. In particular, in the presence of n-hexane as the decomposition agent it showed a high decomposition efficiency compared with benzene at 400$^\circ$C. It was found that the decomposition activity of CFC-113 was very sensitive to reaction temperature. Thus it is expected that to raise the reaction temperature is more effective than to increase the residence time and the amount of decomposition agent. Over the activated carbon catalyst more than 99% decomposition was achieved at the reaction temperature of 600$^\circ$C, SV of 7200$h^{-1}$, the mole ration $(C_6H_{14}/CFC-113)$ of 1 in this study.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.101-104
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• 2009

KARI have been started development process of hydrazine decomposition catalyst for monopropellant thsuter from 2004 in cooperation with Chonnam National University and Hanwha Corps. Through the various trial and error, a catalyst that satisfies all the properties for space propulsion system was developed in 2009 and then the life firing test and qualification firing test was completed. In this paper, we will describe the development process of catalyst, the physical/chemical properties of final product and brief test results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.110-113
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• 2007

For the development of hydrazine decomposition catalyst, Hot-fire test to verify performance of catalyst is required. The purpose of a long-life firing test is to demonstrate the capability of a design to perform for the maximum duration or cycles of operation. This paper describes the progress of the catalyst performance test, explains the test matrix, and presents the test results.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.22 no.2
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• pp.644-650
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• 2021

This study characterized the reforming of methane with carbon dioxide, which is a major cause of global warming. The methane decomposition reaction with carbon dioxide was carried out using transition metal catalysts. The reactivity of tin was lower than that of a transition metal, such as nickel and iron. Most of the decomposition reaction occurred in the solid state. The melting point of tin is 505.03 K. Tin reacts in a liquid phase at the reaction temperature and has the advantage of separating carbon produced by the decomposition of methane from the liquid tin catalyst. Therefore, deactivation due to the deposition of carbon in the liquid tin can be prevented. Methane decomposition with carbon dioxide produced carbon monoxide and hydrogen. Ni was used to promote the catalyst performance and enhance the activity of the catalyst and lifetime. In this study, catalysts were synthesized using the excess wet impregnation method. The effect of the reaction temperature, space velocity was measured to calculate the activity of catalysts, such as the activation energy and regeneration of catalysts. The carbon-deposited tin catalyst regeneration temperature was 1023 K. The reactivity was improved using a nickel co-catalyst and a water supply.