• Proceedings of the Korean Information Science Society Conference
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• 1999.10c
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• pp.230-232
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• 1999

KOMPSAT(KOrea Multi-Purpose SATEllite) Flight Software[2]의 개발 단계에서 통합 및 시험, 검증 시험을 위해 실제 시스템과 유사한 환경을 제공하는 개발도구로서 STB(Software Test BED)를 개발하였으며 STB 구성중에서 Command/Telemetry (CMD/TLM) 테스트를 위해 개발한 Command Generator / Telemetry Analyzer에 관한 내용을 본 논문에서 설명하고자 한다. 통신간에 사용되는 프로토콜은 [1]에서 언급한 바와 같이 CCSDS 프로토콜을 따르고 모든 관련된 Command 와 Telemetry 형식 또한 [1]에서 언급한 바와 같다. 이 구현된 소프트웨어를 이용하여 Flight Soaftware내의 CMD/TLM 처리 소프트웨어의 기능시험과 검증시험을 수행하였다.

• Journal of the Korean Professional Engineers Association
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• v.45 no.5
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• pp.48-54
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• 2012

• Journal of the Korean Professional Engineers Association
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• v.31 no.6
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• pp.60-68
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• 1998

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.77-81
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• 2012

In a cryogenic propellant tank the pressurant is contracted due to heat loss and the propellant itself evaporates. On a restartable propulsion system such phenomena are more intensive because the propellant contacts with the pressurant on the larger surface during the coast flight. Such heat and mass transfer phenomena should be considered for estimating the amount of pressurant. On the hypothesis that the heat and mass transfer quasi-equilibrium is achieved during the coast flight, the calculation process of the equilibrium pressure is presented. On the process the amount of loaded helium on the Falcon-1 second stage is calculated.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2013.06a
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• pp.325-328
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• 2013

본 논문에서는 ToF(Time-of-Flight) 카메라의 거리 잡음을 제거하는 방법으로 거리와 진폭에 따른 거리 잡음 모델링을 이용한 적응적인 SUSAN(Smallest Univalue Segment Assimilating Nucleus) 필터를 제안한다. ToF 카메라의 거리 잡음 제거를 위해서 기존에 제안된 여러 가지 방법들은 거리 잡음의 특성을 고려하지 않거나 진폭에 따른 거리 잡음의 특성만을 고려하였다. 하지만 실제 ToF 카메라의 거리 영상에 포함되는 거리 잡음은 진폭과 거리에 따라서 변화하기 때문에 거리와 진폭을 모두 고려한 거리 잡음 모델링이 필요하다. 따라서 제안하는 방법은 우선 거리와 진폭의 변화에 따른 ToF 카메라의 거리 잡음 특성을 모델링 한다. 이후 제안하는 방법은 생성된 거리 잡음 모델에 의해 인자가 결정되는 적응적 SUSAN 필터를 이용하여 ToF 카메라의 거리 영상의 잡음을 제거한다. 실험 결과 제안하는 방법은 기존의 ToF 거리 영상의 거리 잡음제거 방법에 비해 보다 효과적으로 거리 영상의 잡음을 제거하면서 디테일을 잘 보존하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.201-205
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• 2011

In a cryogenic propellant tank the pressurant is contracted due to heat loss and the propellant itself evaporates. On a restartable propulsion system such phenomena are more intensive because the propellant contacts with the pressurant on the larger surface during the coast flight. Such heat and mass transfer phenomena should be considered for estimating the amount of pressurant. On the hypothesis that the heat and mass transfer quasi-equilibrium is achieved during the coast flight, the calculation process of the equilibrium pressure is presented. On the process the amount of loaded helium on the Falcon-1 second stage is calculated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.225-229
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• 2003

The exact performance simulation of propulsion system is a key element in the prediction of the aircraft performance. The specification performance analysis using the installed loss of KT-1 showed a large difference with the engine performance measured during the flight tests. This indicates that a method to estimate the more exact performance is needed. The study on the performance simulation with performance map correction along the engine operating line shows the good consistent results through all the flight conditions and engine conditions. The correction factors of the map were resulted from the comparative analysis between the flight test and the simulation of installed engine performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.299-302
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• 2008

A unified numerical analysis including combustion was conducted in order to study on performance of ramjet propulsion. The geometry of concern includes the entire flow path of a ramjet extending from intake to exhaust nozzle. Acceleration mode and cruise mode were considered in several equivalence ratios. Pressure distributions, terminal shock train range at the intake, temperature distributions in the combustors, and fuel mass fraction at the nozzle exit were investigated for each flight mode.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.93-96
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• 2009

Advances in high speed flight technologies and engine efficiencies increase heat load on the aircraft. As the temperature of air flow is too high to cool the structure at hypersonic flight speeds, it is necessary to utilize the aircraft fuel as the primary coolant. By undergoing endothermic reaction, such as thermal decomposition or catalytic decomposition, aircraft fuels have heat sink potential. These fuels are called endothermic fuels. The endothermic reaction can be improved by catalysts, but limited by coke deposition. In this study the essential technologies of endothermic fuels are described, and intended to be used for basic research.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.1
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• pp.76-81
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• 2016

At negative-g condition, a float-type valve can open the passage of fuel in order to it flows continuously through a pressurized fuel tank system. Since specialized test conditions and high-cost supports are required, it is truly difficult to test the valve in a real high-speed test. Therefore, this paper contains performance analysis of a float-type fuel supply valve through flight tests conducting roll and negative-g maneuvers.