• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.11
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• pp.386-393
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• 2019

In this study, we investigated the cause of a voltage controller failure that occurred in the operation of a combat vehicle and attempted to establish a solution for the failure. The failure in the voltage controller was found to be related to thermal resistance, which could be identified by disassembly analysis and a high temperature operation test. Especially, in the disassembly analysis, there was damage caused by high temperature such as soot on the molding material and cracking of the resisters. In addition, in the high temperature operation test, the test results show that the internal temperature of the voltage controller was relatively higher than the external temperature. This means that the voltage controller failure could be attributed to the excessive heat and insufficient thermal resistance. In order to improve the thermal resistance of the voltage controller, several designs with changing circuits and structures were devised. Improvement of thermal resistance was verified by measuring reduction of internal temperatures in the high temperature comparison test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.8
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• pp.120-125
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• 2002

In the preceding tests using the KSR-III Sub.(I) engines, it was observed that the heat resistant capability of the engines was not enough for the mission. So Sub.(I) Mod. engines were designed and tested. The Sub.(I) Mod. engines have three major design parameters - the arrangement of main injectors, the impinging angle of main injectors and thermal barrier coating. More than twenty experiments were carried on to evaluate engine performance and heat resistance capability with respect to design parameters. In this study, the test results are introduced. Analysing the result of Sub.(I) engine tests, it is found that decreasing the impinging angle, adopting the H-type arrangement(rather than radial type arrangement) and adopting the thermal barrier coating can increase heat resistance capacity substantially. Also, engine performance evaluation is conducted using specific impulse and characteristic velocity parameter. The results show that the performance variation is small(about 5%) and the performance is better in the case of radial arrangement. It is suspected that these phenomena are caused by the change of flame structure atomization mixing characteristic of sprays and the distortion of recirculation zone. Also from the low frequency instability point of view, it is observed that reducing the impinging angle and adopting the H type arrangement can increase the instability characteristics.

• Magazine of the Korea Concrete Institute
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• v.10 no.5
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• pp.109-115
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• 1998

철근콘크리트 구조물이 과소설계되어 있거나 과다 하중이 작용하게 되면 그 구조물의 구조성능을 파악하여 보수.보강을 시행하게 된다. 최근에 가장 맣이 사용되는 보수.보강 재료로는 특히 휨내력을 보강하는데 탄소섬유를 들 수 있다. 탄소섬유쉬트는 내열성과 내호염성에 있어서 회재가 발생할 경우 보강재료로서 충분한 성능을 가지고 있다. 그러나 이를 접착시키는데 사용되는 에폭시는 유기계 물질로서 화재시 유독가스가 발생하고 내열성능도 30$0^{\circ}C$정도에도 지탱하기 어려워 화재 발생이 가능한 구조물에 사용하기 어렵다. 이 연구에서는 무기계 폴리머 복합재료로 접착된 탄소섬유를 고온(약 800~100$0^{\circ}C$, 1시간)으로 가열한 후 가열된 섬유판의 인장, 휨 전단내력을 검토하여 내열성능을 파악하고 이 섬유쉬트로 보강한 철근콘크리트 부재의 휨 성능을 실험적으로 규명하여 화재의 위험이 있는 구조물에 구조적인 보강재료로 사용이 가능한가를 검토하였다. 연구 결과, 개발된 무기계 폴리머 복합체는 인장강도, 휨강도 및 접착강도가 유기계 접착제와 유사하게 나타났고 800~100$0^{\circ}C$ 정도로 1시간 가열한 이후에도 상온 시험체 휨내력과 전단내력의 63%, 33% 정도를 유지하여 화재의 위험이 있는 부위에도 사용이 가능한 것으로 판단되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1192-1195
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• 2017

This paper describes the heat resistance characteristics of the imaging device installed in behind the engine due to monitoring the engine condition, and this paper includes the introduction and development of the imaging probe. Because the imaging device which is at the rear end of the engine is exposed to a high temperature and high pressure, the stability of the device should be secured by changing the device shape and supplying cooling water. The imaging probe in ADD engine test facility is installed at the rear end of the engine, and it is designed by reflecting the heat resistance characteristics to ensure the stability of the device.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.305-308
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• 2005

This paper presents a fabrication of a full-stale combustion chamber of a liquid rocket engine for a ground hot firing test. Engine drawings for manufacturing were prepared after conceptual and detail designs. The combustor is composed of a head and a chamber. SUS316L is used for materials of the head because of the good quality in low temperature. Inner materials of the ablative cooling chamber is silica/phenolic and outer case materials is the SUS316L. Materials of the regenerative cooling chamber are C18200 and SUS316L. After lathe, general milling and MCT machinings, components were finished by electrolytic polishing. A brazing method was applied for bonding the injectors and the injector plate, the regenerative cooling chamber because of structure configurations.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.3
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• pp.107-115
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• 1998

This paper deals with the study on injection with EPDM(Ethylene propylene dien ter polymer) the gap which narrow, long, and tubular between an ablative composite tube and a steel motor case. Small size motor assembly was designed and manufactured for man-portable air defense propulsion system. Motor assembly is consisted with steel tube, ablative composite tube and insulation rubber. Ablative composite tube was made of carbon/phenolic prepreg by rolling process and insulation rubber was made of EPDM by TPM(Trans-power molding) process. To select the insulation rubber material, we tested ablative insulation property and degradation property at first and we tested fluidity, adhesive property and hardness of EPDM rubber. Finally we designed TPM process to manufacture motor case assembly and the motor case assembly was examined by non-destructive test(X-ray).

• Journal of the Computational Structural Engineering Institute of Korea
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• v.14 no.4
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• pp.495-503
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• 2001

In a functionally graded materials(FGM), two constituent material particles are mixed up according to a specific volume fraction distribution so that its thermoelastic behavior is definitely characterized by such a material composition distribution. Therefore, the designer should determine the most suitable volume fraction distribution in order to design a FGM that optimally meets the desired performance against the given constraints. In this paper, we address a numerical optimization procedure, with employing interior penalty function method(IPFM) and FDM, for optimizing 2D volume fractions of heat-resisting FGMs composed of metal and ceramic. We discretize a FGM domain into finite number of homogenized rectangular cells of single design variable in order for the optimization efficiency. However, after the optimization process, we interpolate the discontinuous volume fraction with globally continuous bilinear function in order to enforce the continuity of volume fraction distributions.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1282-1291
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• 1989

본 연구에서는 이러한 연구의 시작단계로 노즐내의 열 경계층 방정식을 정리하고 압축성 와점도모델을 도입하여 유한 차분법을 이용한 전산프로그램을 작성 하였다. 한편 실제로 추진모테에서는 고온 고속의 열기류가 분출되기 때문에 추진 하고 있는 동안 노즐벽을 형성하고 있는 내열재가 심하게 손상되어 표면의 상태가 매우 거칠게 된다. 더구나 경우에 따라서는 내열재가 용발(ablation)하게 된다. 이러한 상태를 감안하여 마찰계수와 열전달 계수를 합리적으로 추정해야만 노즐의 설계와 주변장치를 합리적으로 수행할 수 있다. 따라서 본 연구에는 주로 경계층 내의 압력구배, 압축성의 효과, 물성치의 변화를 고려한 기존 난류모델에 근거하여 프로그램을 작성하고, 이것을 토대로 노즐표면 조도의 영향 및 분출(blowing)의 영 향을 중점적으로 고려하여 그 특성을 연구하였다. 노즐벽에서 분출을 고려한 이유는 표면이 용발할 때 표면의 온도가 거의 일정하게 유지된 상태로 노즐표면이 화학작용을 수반하면서 가스화됨을 초보적으로 고려해보기 위함이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.193-198
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• 2010

In solid propellant rocket motors, $Al_2O_3$, one of combustion products, can be accumulated inside a combustion chamber. A special rocket motor was designed and tested to simulate thermal reaction of rubber insulator affected by the deposited slag. We successfully demonstrated through a dynamic radioscopy that the slag was deposited at the location as designed. In this paper we present a new test method which can simulate a high temperature and pressure environment in combustion chamber to evaluate material characteristics of rubber insulator and can provide design data to decide its thickness for a new solid rocket motor. The solid rocket motor, which has an average chamber pressure of 770 psia and a burning time of 50 seconds, was tested. The results show that erosion of EPDM insulator is more affected by a gas velocity rather than by the thermal reaction of slag with a high thermal capacity.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.9-14
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• 2011

In solid propellant rocket motors, $Al_2O_3$, one of combustion products, can be accumulated inside a combustion chamber. A special rocket motor was designed and tested to simulate thermal reaction of rubber insulator affected by the deposited slag. We successfully demonstrated through a dynamic radioscopy that the slag was deposited at the location as designed. In this paper we present a new test method which can simulate a high temperature and pressure environment in combustion chamber to evaluate material characteristics of rubber insulator and can provide design data to decide its thickness for a new solid rocket motor. The solid rocket motor, which has an average chamber pressure of 770 psia and a burning time of 50 seconds, was tested. The results show that erosion of EPDM insulator is more affected by a gas velocity rather than by the thermal reaction of slag with a high thermal capacity.