• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.272-274
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• 2008

A development of hydrazine decomposition catalyst for monopropellant thruster has been performed by Korea Aerospace Research Institute(KARI). The goal of this development is to product a catalyst showing the equivalent performance with space-proven catalysts. Catalyst production and physical/chemical analysis were conducted by Chonnam National University and the analysis result was compared with the result of other catalysts and our own specification. Using the developed prototype catalyst, short firing test was performed in a reactor to verify basic performance of catalyst. After the successful reactor test, hot firing tests were carried out in atmospheric and vacuum condition using 5N thruster to verify durability and safety of catalyst. In this paper, the catalyst development status will be presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.151-154
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• 2007

The purpose of this study is to identify the basic concept of thruster design through the visualization firing test on a hydrazine thruster. We designed the visual catalyst bed on the basis of the 1lbf hydrazine thruster for a low earth orbit satellite and observed visually the internal catalyst bed reaction.

• Proceedings of the KAIS Fall Conference
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• 2004.11a
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• pp.255-258
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• 2004

Hydrazine is a weak base and strong reducing agent in the aqueous solution and is primarily utilized as a high-energy rocket propellant and an oxygen scavenger in boiler or feedwater. The objective of this study was to investigate the physicochemical properties and reactions of hydrazine and the catalytic and thermal decomposition by the temperature change. Hydrazine was fast decomposed with the catalyst of lower activation energy and at the higher temperature.

• 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.

• Journal of Sensor Science and Technology
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• v.14 no.5
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• pp.297-301
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• 2005

Nanocrystalline SnO and $SnO_{2}$ powder have been prepared by hydrazine method. Sn-Hydrazine complex was formed by the reduction between aqueous $SnCl_{2}$ solution and hydrazine monohydrate. $SnO_{2}$ nano powder was prepared by the decomposition of Sn-Hydrazine complex at $450^{\circ}C$. When NaOH was added to Sn-hydrazine complex, SnO powder with nano-sheet morphology could be prepared. This can be attributed to the role of $OH^{-}$ ion as a reducing agent.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.645-648
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• 2011

Hydrazine which has been used as monopropellant shows high performance, but because of its high toxicity research for new green propellant that could replace hydrazine is going on. Ionic liquid propellant that is one of the green propellant has lower toxicity, higher specific impulse, and higher density than hydrazine. To design the thruster which use Hydroxylamine Nitrate (HAN), one of ionic liquid propellant, as a propellant, a quantity of catalyst for full decomposition of a propellant is needed. In this study, reference point for HAN thruster design could be suggested through a design of a small scale thruster which used HAN propellant, and propellant decomposition capability evaluation with characteristic velocity efficiency.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.292-295
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• 2004

Firing performance test of hydrazine decomposition catalyst which is used in mono-propellant thruster of satellite and launcher was peformed. Equipment for catalyst test was developed and with this equipment reaction delay time, catalyst activity, granule stability of the catalyst firing performance was measured and analyzed.

• Proceedings of the KAIS Fall Conference
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• 2012.05a
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• pp.452-454
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• 2012

본 논문에서는 열분해 및 촉매반응의 의한 Hydrazine의 Ammonia 전환율을 연구하였다. 원자력발전소 2차 계통은 물/증기 순환계통으로 기기 및 배관의 부식을 억제하고, 증기발생기(Steam Generator, SG)의 부식생성물 유입을 최소하기 위해 전휘발성처리법(All Volatile Treatment, AVT)을 적용하여 계통수의 pH를 약염기성으로 유지하고 있다. 또한 Hydrazine을 이용하여 계통수의 용존산소제거 및 환원성 분위기를 유지하고 있다. 현재 사용되는 AVT는 대부분 단일 아민(Ammine)으로 계통 전 영역에서 pHt를 약염기성으로 유지하기 어렵다. 따라서 복합 아민을 이용하여 단일 아민의 상호단점을 보완한 수처리법을 적용해야한다. 하지만 복합 아민을 적용할 경우 추가 아민 주입설비, 설치부지, 시설유지보수 및 관리가 요구되므로 기존 주입약품을 이용하여 아민을 공급할 수 있는 연구가 필요하다. 따라서 본 연구에서는 Hydrazine의 열분해 및 촉매반응을 이용한 Ammonia 전환율을 조사하였다.