• Aerospace Industry
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• s.95
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• pp.10-13
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• 2007

• Current Industrial and Technological Trends in Aerospace
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• v.2 no.2
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• pp.70-83
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• 2004

• Aerospace Industry
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• v.19
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• pp.6-10
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• 1994

• Aerospace Industry
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• s.107
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• pp.18-19
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• 2010

• Aerospace Industry
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• v.85
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• pp.4-9
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• 2004

• Bulletin of the Korean Space Science Society
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• 2006.04a
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• pp.110-110
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• 2006

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.2
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• pp.165-172
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• 2014

This study was focused on the investigation of the liquid propellants for the launch vehicle, past, present and future trends in worldwide. In general, storable and hypergolic propellants are used for the military purposes and comparing to this, the kerosine fuel and cryogenic propellants are used for the launching systems. Although liquid propulsion is seemed as a mature technology, the requirements of a renewed interest for space exploration has led to the development of a family of new engines, with more design margins, simpler to use and to produce associated with a wide variety of thrust and life requirements.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.8
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• pp.85-90
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• 2003

To control spacecraft including satellite, we should understand precisely the performance of propulsion system and the program logic with appropriate format for satellite operations. In this study, the thruster performance functions was generated by using the best curve fitting for performance data from bi-propellant thrusters. Detailed thruster performance data are, in general, company proprietary information, therefore real firing tests were performed to understand the basic characteristics of the performance curve. Experimental rocket motor utilize liquid oxygen and kerosine as propellant and designed average thrust was 100 pound.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.232-241
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• 2004

KARI(Korea Aerospace Research Institute) is achieving the KSLV program according to National Space Technology Development Program. In this paper, the authors are intend to introduce the Integrated Power Plant(IPP) test facility which will be constructed for the variety of tests on KSLV program. IPP test facility refers to comprehensive testing equipment for liquid rocket launch vehicle. Using this facility, KARI can verify the adaptedness of parts and subsystems for launch vehicle and finally can qualify the system characteristics of launch vehicle doing kinds of test including hot firing test. IPP test facility will make it possible to simulate the vehicle launching circumstances and to predict the performance of launch vehicle during its flight test.

• Journal of Aerospace System Engineering
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• v.18 no.4
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• pp.109-116
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• 2024

The validity of the analysis results was confirmed based on the insulation test results, and the vaporization mass generated in the common bulkhead was calculated to evaluate the common bulkhead propellant tank's insulation performance. The analysis results were validated by comparing the transient heat transfer analysis with the insulation test results. A transient heat transfer analysis was subsequently conducted on the common bulkhead propellant tank, considering the internal heat conduction in the propellant tank and natural convection heat transfer due to the outside air. This analysis extracted the heat flux generated in the common bulkhead and quantified the vaporization mass, a key indicator of insulation performance. Consequently, the vaporization mass was calculated at 0.09 kg, below the insulation design standard of 0.12 kg for the common bulkhead propellant tank, confirming it meets the insulation performance standard.