• Proceedings of the KSME Conference
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• 2005.11a
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• pp.137.1-137.1
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• 2005

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.636-641
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• 2010

A preburner for the staged combustion in the high performance liquid rocket engine is being developed and strength experiments and finite element analyses on specimens, which simulate the brazing joint of the preburner, were performed and the results were compared. One specimen simulate the joints near oxygen injectors of head by the funance brazing and two specimens the joints of the combustion chamber cooling channel by vacuum brazing. The experiments were burst ones with strain gauges.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.50-55
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• 2011

A preburner for the high performance, staged combustion cycle liquid rocket engine is being developed. For the structural design processes, strength experiments and finite element analyses on specimens simulating the brazing joints of the preburner, were performed and compared. Total two kinds of the specimen were manufactured for the tests. One simulated the joints between the oxygen injectors and the head junctioned by the conventional vacuum brazing. The another was made to test the brazing surfaces by vacuum compression between the combustion chamber cooling channel and the outer wall. During the burst experiments, it was observed that the fractures were occurred not at the brazed joining but in the middle of the face plate and the cooling wall. In addition, the analysis showed that the predicted fracture locations and the strains were well matched with the experiment results.

• Journal of the Korean Geotechnical Society
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• v.16 no.6
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• pp.161-172
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• 2000

자연암석절리 및 인공 절리에 대하여 일정수직응력제어, 일정 수직하중제어 그리고 무한 강성제어가 가능한 암석 절리면 전단기 시험기를 개발하였다. 이 시험기는 전단변위에 의한 첩촉면적의 변화량을 계산하여 하중변화량을 조절하여 일정수직응력상태를 유지한다. 수직하중에 따른 시험기 강성에 의한 변화향이 제어 프로그램 내에서 제어되어 순수한 시편의 변위량을 출력하도록 하였다. 전단하중에 따른 시험기 강성에 의한 변위량은 상, 하부 전단상자의 상대변위 측정으로 최소화하였다. 전단거동 중의 자유도는 전당방향에 대하여 수평이도, 연직이동, 피칭, 롤링이 가능하도록 하였다. 자연절리면을 모사한 석고시편에 대하여 일정 수직응력 제어, 일정수직하중제어 그리고 무한 강성제어 조건으로 시험하여 제어상태 검증 및 비교를 하였다. 또한 경사각이 16.7˚와 22.6˚인 톱니형 시편에 대하여 시험한 결과 경사각 16.7˚와 22.6˚는 JRC로 10과 15를 나타내었으며, 첨두팽창각이 첨두전단강도에서 발생되며, Barton의 모델과 잘 일치함을 보였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.27-27
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• 1999

본 연구에서는 초음파 Immersion법을 이용하여 복합재 연소관내에 존재하는 결함을 검출하는 방법에 대하여 연구하였으며, 이를 위하여 FRP의 delamination, FRP-EPDM간의 미접착을 모사한 모의 결함 시편을 제작하여 시험하였다. 먼저 복합재료에 대한 초음파 시험방법을 최적화하기 위하여 가장 검출 감도가 좋은 탐촉자의 적용 주파수조건 및 물거리를 구하였으며, 이들 최적 조건으로 모의 결함 시편을 A, B, C-Scan하여 결함을 검출 분석하였다. 그리고 시험 자료를 바탕으로 데이터 값을 분석함으로써 복합재료에서의 음파 속도, 음향 임피던스, 반사율 및 투과율 등 복합재료의 초음파 특성을 산출하였으며, 동 시편에 대한 X-ray 필름을 촬영하여 그 결과를 초음파 시험 결과와 비교 분석하였다.

• Journal of the Korean Crystal Growth and Crystal Technology
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• v.8 no.4
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• pp.612-618
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• 1998

Monolithic SiC and SiC/C FGM layers were deposited on the graphite substrates by the CVD method and their thermal properties of the two specimens were investigated by thermal shock test for comparison. Temperature profiles and thermal stress distributions on thermal shock test were calculated by a commercially used computer program to see the thermal stress differences inside of two specimens. The specimens coated with FGM were expected to show a efficient relaxation of thermal stresses at the interface and they were not cracked under the actual $\Delta$T=1600 K experimental condition. This result proved that the experimental results were well accorded with the expectation from the theoretical calculations.

• Composites Research
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• v.27 no.2
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• pp.77-81
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• 2014

In this study, it was performed damage assessment and repair of small scale aircraft adopted on composite. This aircraft adopted the sandwich structure to skin of wing. This study aims to investigate the residual strength of sandwich composites with nomex honeycomb core and carbon fiber face sheets after the open hole damage by the experimental investigation. The 4-point bending tests were used to find the bending strength, and the open hole was applied to introduce the simulated damage on the specimen. The bending strength test results after open hole were compared with the results of no damaged specimen test. In addition, The damaged composite structure was repaired using external patch repair method after removing damaged area. After that, this study presents comparison results of the experimental investigation between the damaged and the repaired specimen. It was found that the bending strength of repaired specimen was recovered up to 95% of undamaged specimen.

• Composites Research
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• v.22 no.2
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• pp.24-29
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• 2009

This study aims to investigate the residual strength of sandwich composites with Al honeycomb core and carbon fiber face sheets after the quasi-static indentation damage by the experimental investigation. The 3-point bending test and the edge-wise compressive strength test were used to find the mechanical properties, and the quasi-static point load was applied to introduce the simulated damage on the specimen. The damaged specimens were finally assessed by the 3-point bending test and the compressive strength test. The investigation results revealed the residual strength of the damaged specimens due to the quasi-static indentation. The both test results showed that the residual strength of the damaged specimen was decreased according to increases of the damaged depth.

• Composites Research
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• v.23 no.5
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• pp.15-21
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• 2010

In this study, repair and maintenance schemes of the damaged composite structure was investigated, and a repair process of the carbon/epoxy laminate composite structure was investigated numerically and experimentally. The composite laminates were damaged by drop weight type impact test machine. The damaged composite structure was repaired using external patch repair method after removing damaged area. The compressive strength test and analysis results after repairing the impact damaged specimens were compared with the compressive strength test and analysis results of undamaged specimens and impact damaged specimens. Finally, the strength recovery capability by repairing were investigated.

• Proceedings of the Korean Nuclear Society Conference
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• 1996.11a
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• pp.45-52
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• 1996

고리 1 호기 원자로 감시？슐에서의 고속중성자 플루언스를 계산하기 위하여 MCNP코드로 3차원 모델링을 하였다. 중성자선원은 MCNP에 의해 계산된 핵연료봉출력분포를 사용하였고 원자로심부터 원자로 압력용기 밖까지 1 MeV이상의 중성자를 수송시켰다. 감시？슐은 실제의 같은 크기로 모델링하였고 감시？슐안의 시편은 원자로 압력용기와 같은 재질의 직육면체로 가정하였다. 그리고 MCNP에 의해 감시시편내의 방사화 시료의 핵반응단면적을 계산하였다. 또한 MCNP에 의해 이론적으로 계산된 감시？슐에서 중성자 플루언스와 기존의 감시시험에서 측정된 포화방사능으로 부터 계산된 실험적 감시？슐 중성자 플루언스를 비교하였다. 이론적 ？슐플루언스와 실험적 ？슐플루언스의 비는 대체로 1.0에서 크게 벗어나지 않았으나 감시시험과 시편에 따라 크게 벗어나는 경우도 있었다. MCNP에 의한 유효반응단면적의 계산방법이 기존의 방법보다 모델링 및 계산의 불확실성을 최소화 할 수 있으므로 이번 연구에서 고려하지 못한 원자로심의 연소도를 고려한다면 매우 신뢰성이 높은 결과를 얻을 수 있다.