• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.91-104
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• 2002

Jet noise of propulsion systems is major source of acoustic loads of launch vehicles and sounding rockets. The investigation of characteristics of jet noise is inevitable for successful missions. In this paper, the mechanism of generation of acoustic loads due to jet noise was investigated. The major parameters that change the characteristics of acoustic loads were also suggested so that effects of the parameters could be investigated. The temporal and spatial characteristics of acoustic loads of KSR-III was demonstrated. The results show that the maximum value of the acoustic loads is found in the octave bands whose center frequencies are 250 Hz and 500 Hz. Finally, the methods and the facilities for the further investigation of acoustic loads were proposed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.936-938
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• 2017

In this paper, the progressive failure analysis of a bolted composite joint which is used in combustion tubes of projectiles and weapon systems is performed. Hashin's failure criterion is considered as fiber tensile failure mode, fiber compressive failure mode, matrix tensile failure mode, and matrix compressive failure mode for this analysis. And this criterion is used to make user subroutine, UMAT. Through the progressive failure analysis we predicted failure strength and compared failure strength with specimen test result.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.521-528
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• 2017

In this paper, the numerical analysis for heat conduction of silica/phenolic composite material, which is used for solid rocket nozzle liner or insulator, was conducted. 1-D Finite Difference Method for the analysis of silica/phenolic during the firing of solid rocket motor was used to calculate the heat conduction considering the surface ablation and the thermal decomposition. The boundary condition at the nozzle wall took into account the convective heat transfer, which was obtained by integration equation. The numerical results of the surface ablation and char depth were compared with the results of test motor that is TPEM-10. It was found that the result of calculation is favorably agreed with the thermal response of test motor.

• Proceedings of the Mineralogical Society of Korea Conference
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• 1996.10a
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• pp.61-72
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• 1996

중국 토양표토의 유황함량은 27에서 967mg S/kg(평균 233.2mg S/kg, n=632)범위에 있다. 이중 홍토(Haplic Acrisols)와 황갈색토(Eutric Cambisols)는 양쯔 및 Huaihe강 사이에 중국 중앙에 분포하고 유황함량은 각각 146과 159mg S/kg이다. 황색 목장토(Gleyic Cambisols)와 회색 목장토(Umbric Fluvisols)는 가장 높은 전 유황함량과 가장 높은 유황공급력을 가지고 있으나 제일 인산석회 침출 유황함량(현지유효 유황함량으로 평가)은 가장낮다. 그러나 황갈색 및 홍토는 이와는 반대 특성을 지니고 있다. Shajiang 흑토(Calcic Vertisols)와 논토양(Mollic/Eutric Fluvisols과 Anthraquic 상)은 총 유황함량, 인산 침출 유황함량과 잠재 유황 공급력에서는 중간에 속하고 남부 Huaihe강에 걸쳐있는 논토양에서 유황함량은 재배기간중 균형 상태에 있으나 전(前)작물에서 특히 밀과 유채에서는 부족한 상태이다. 황산염($SO_4^{2-}$)은 토양중 상하로 이동 되면서 균형을 유지하여 토양 수분함량과 밀접한 관계가 있다. 따라서 제일인산칼슘 용액침출 유황 함량을 가지고 표토에서 유황의 과부족을 진단하기는 그리 쉬운 일이 아니다 중국에서 수행된 유황시비 시험에서 20개 작목에서 평균 $4.3-40\%$의 수량증수를 기록하였으며 유황시비는 증수뿐만 아니라 작물의 질을 개선하나 담배잎의 연소성은 유황함량과 부의 상관이 있다.

• Nuclear Engineering and Technology
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• v.27 no.4
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• pp.603-618
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• 1995

원자력 발전소 및 동위원소 사용기관에서 발생되는 가연성 고체 폐기물 및 유기폐액의 소각기술의 활용에 있어서 이의 안전성 확보를 위한 기술적 기준의 설정을 위한 고려인자들을 조사하였다. 국내외의 소각기술 활용현황을 알아보았고 본 기술의 국내 도입시 필요한 기술적 안전지침에 관한 외국의 사례를 조사하고 국내 관련 규정도 검토, 비교, 분석하여 주요 고려항목을 도출하였다. 안전성 확보를 위한 고려 항목을 크게 일반산업시설 적용항목, 원자력시설 상 안전조건, 소각시설의 기술적 요구사항, 기타 제반사항으로 나누어 제시할 수 있었다. 이들 내용은 기존 원자력 및 환경시설에 적용되는 안전성분석보고서 및 환경영향평가서로 작성될 수 있다고 보았으며 시설의 개요, 시설의 기술적 사항과 이에 따르는 안전을 위한 조건, 폐기물의 인수조건 등이 포함되며 기존 관련 법규의 적용 및 확인이 필요하였다. 기술적 사항에는 공정의 제염계수, 연소효율, 소각재의 형상, 배기가스의 방출농도, 작업자 및 인근주민의 피폭등이 확인되어야 하며 소각재의 처리방법 및 조건이 제시되어야 하고 소각재의 침출특성 등이 주요한 인자라고 보았다. 아울러 소각대상폐기물의 인수조건이 명시되어 소각성능에 따른 이의 안전성이 입증되어야 한다. 따라서 인허가 후 건설된 시설에서의 사용전 시험소각절차의 제시 및 이에 대한 관련 규제기관의 검사제도가 있어야 하며 품질보증절차 역시 관련지침에 따라 실시되어야 한다. 이와 같은 내용을 포함하는 안전기술지침의 설정이 절대적으로 필요하며 본 연구조사 결과의 활용이 기대된다.

• Resources Recycling
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• v.5 no.2
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• pp.45-51
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• 1996

Domestic coal contains approximnlely 03 to 7 percentage of sulfur. When the suliur in coal is burned, exhaust gas , nay be thc causc of air pollution problcms as well as acid rain. Thc government dccideil lo strengthen the environmcnlal protection policy a1 the 270 ppm of SO, for the coal-Ered plants and to stari in Ian. 1, 1999. This study was carried out lo rcmove the stlfur and mineral mancrs in the samplw using wet msg~xiic separatol ant1 oil agglomeration apparatus. The rcsults for the wet magnetic separalion showed that the total sulfur removal from Kangnung coal sample was 60.8% with 82.6% combustible recovery. For the results of oil agglomeration testa, combustible recavety, ash nod sulfur rcmovcl horn Maro coal sample were 98.0, 70.9 and 95.7 percent, respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.47-52
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• 2004

In the design of scramjet intake for hypersonic flight, a variety of aerothermodynamics phenomena are encountered. These phenomena include blunt leading - edge effects, boundary layer development issues, transition, inviscid / viscous coupling, shock - shock interactions, shock / boundary - layer interactions, and flow profile effects. For intakes that are designed to operate within a narrow Mach number / altitude envelope, an understanding of a few of these phenomena might be required. In this work several predominant flowfield phenomena (viscous phenomena, boundary - layer separation, and combustor entrance profile) are discussed to investigate the performance of the intake at the altitude and angle of attack extremes of the HyShot flight experiment.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.199-202
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• 2008

This paper presents a mathematical-physical model to predict the performance of a gas pusher used as a separation system powered by a gas generator. The empirical coefficients of heat loss and friction were determined from experiments. Based on the grain configuration of the gas generator, the analytical approach of combustion, flow and movement of a piston inside the chamber of a gas generator and a gas pusher was simulated by numerical method. The prediction method developed can be usefully applied to the design of separation mechanism systems.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.529-531
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• 2012

The temperature coefficient of a gun propellant could be reduced by applying an appropriate surface coating material. The burning rates of those propellants do not very strongly depend on the propellant temperature. It is a good method to increase the muzzle velocity of gun ammunitions by utilizing the permissible maximum pressure in the gun barrel independent of the propellant temperature. During this study, properties of surface coated propellants were confirmed by results in tests of a closed bomb and 40mm Gun firing, and confirmed that production of coating propellant could be possible.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.196-200
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• 2012

To acquire indigenous development abilities of a future space launcher, bi-propellant liquid rocket engines using environmentally clean propellants such as hydrogen peroxide and methane have been developed by Chungnam national university. The necessary development technologies for the future liquid rocket engines were defined and have been acquired step-by-step in advance by sub-scale liquid rocket engines. Core techniques of design/manufacture/experiments to develop a future prototype liquid rocket engine will be obtained by this study.