• 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 Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.48-55
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• 2012

An ambient hot-firing test was carried out for the hydrazine thruster which may be employed in the space launch vehicles. The thruster is designed to produce 67 N (15 $lb_f$) of nominal steady-state thrust at an inlet pressure of 2.41 MPa (350 psia). A scrutiny into the performance characteristics of thruster is made in terms of thrust, propellant supply pressure, mass flow rate, chamber pressure, and temperature at the steady-state firing mode. As a result, it is ensured that the practical performance efficiencies are above 89.1% compared to its ideal requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.399-404
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• 2010

Test results including the variation of propellant-inlet pressure, pulsed thrust, and environment vacuum with the accompanying thermal responses are presented for the pulse-mode operation of a set of monopropellant hydrazine thrusters producing $0.95lb_f$ of nominal steady-state thrust at an inlet pressure of 350 psia. The test data are reduced into the impulse bit, specific impulse, and force centroid that are the factors typically characterizing pulse-mode performance of small rocket engines. With a scrutiny to the performance parameters, their comparison to the reference criteria of 1 lbf standard monopropellant rocket engine are successfully made.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1061-1067
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• 2017

Since the 1960s hydrazine is used as a propellant to power rocket, satellites or deep space missions. Due to hydrazine's high toxicity and operating cost, the request for Green Propellant as energetic ionic liquids(HAN, ADN), nitrous oxide blends is growing. Nitrous Oxide Fuel Blend(NOFB) having advantage of a bipropellant performance as well as the advantage of a mono-propellant in respect to the simple propellant tank and feed system. It is worth replacing traditional hydrazine based propellant system if handled and designed properly.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.3
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• pp.1-8
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• 2015

A ground hot-firing test(HFT) was accomplished to draw a correlation between the pressure oscillation intensity of combustion chamber and thrust response characteristics in a 70 N-class hydrazine thruster which has been developed recently. Monopropellant grade hydrazine was adopted as a propellant for the HFT, and combustion-chamber characteristic length, propellant injection pressure were applied as test parameters. It was confirmed that the decrease of thrust-chamber diameter and injection pressure augmented the pressure oscillation of stagnation chamber in the test condition specified, and the oscillation hampered the pulse response performance of test models.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.175-178
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• 2011

A performance characteristics and application status of liquid-monopropellants used for 3-axis control thrusters are surveyed, in this paper. Hydrogen peroxide was widely used as monopropellant until mid-1960s, but it is rapidly replaced with hydrazine which has better performance of specific impulse, storability, and so on. Hydrazine is mostly employed as a liquid-monopropellant of satellite, interplanetary spacecraft, and space launch vehicle owing to its moderate performance features.

• 월간산업보건
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• s.281
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• pp.49-57
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• 2011

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.49-56
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• 2005

Hot firing performance test of hydrazine decomposition catalyst used for monopropellant thruster of the satellite and the launch vehicle was performed. Test equipment for catalyst test was developed in collaboration with Hanwha Corp., reaction delay time, catalyst activity and granule stability of the catalyst firing performance were measured and analyzed with the equipment. In addition, the current development of prototype catalyst is introduced.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.167-176
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• 2014

The pyrovalves are widely used in aerospace industry for the opening and closing of flow channel due to the light-weight, high reliability and zero-leakage. In the United States, the loss of some spacecrafts using hydrazine as the propellent were proven by the blowby. Blowby is defined as the leakage of pyrovalve ignition combustion gas to the flow channel. Since then, the interference fit was applied for the sealing of piston to prevent the blowby. In this study, literature survey on pyrovalve technology is summarized mainly for AIAA papers. Common problems, improvement method, and performance comparisons of pyrovalves are also presented.

• Proceedings of the Korean Institute of Industrial Safety Conference
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• 2000.06a
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• pp.120-123
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• 2000

최근 첨단 과학기술의 급속한 발전에 따라 각종 화학물질이 여러분야에서 제조되고 또한 취급되고 있다. 이들 화학물질은 그 합성, 정제 및 사용법 등에 대해서는 각종 문헌에 잘 기재되어 있으나 그 위험성에 대해서는 충분히 파악되어 있지 않았거나 발표되어 있지 않은 것이 많아 대상이 되는 반응조건 이나 제조조건을 변경해야하는 경우 제조자 스스로 결정해야 하는 경우가 많아 뜻하지 않은 재해가 발생하는 예가 증가하고 있다. 따라서 본 연구에서는 의약품 및 농약 등 합성시 중간체로서 널리 사용되고 있으나 구조적인 특성상 열에 매우 불안정하여 산안법상 위험물중 폭발성물질로 분류되어 있는 니트로페닐하이드라진에 대한 열분해 특성을 시차주사열량계(DSC) 및 가속 속도열량계(ARC) 이용하여 그 위험성을 평가하였다. (중략)