• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2001년도 추계학술발표대회 논문집
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• pp.105-110
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• 2001

Autoclave curing using the vacuum bagging method is widely used for the manufacture of advanced composite prepreg airframe structures. Due to increasing use of advanced composites, specific techniques have been developed to repair damaged composite structures. In order to repair the damaged part, it is required that the damaged areas be removed, such as skin and/or honeycomb core, by utilizing the proper method and then repairing the area by laying up prepreg (and core) then curing under vacuum using the vacuum bagging materials. It shall be cured either in an oven or autoclave per the original specification requirements. Delamination can be observed in the sound areas during and/or after a couple times exposure to the elevated curing temperature due to the repeated repair condition. This study was conducted for checking the degree of degradation of properties of the cured parts and delamination between skin prepreg and honeycomb core. Specimens with glass honeycomb sandwich construction and glass/epoxy prepreg were prepared. The specimens were cured 1 to 5 times at $260^{circ}F$ in an autoclave and each additionally exposed 50, 100 and 150 hours in the $260^{circ}F$ oven. Each specimen was tested for tensile strength, compressive strength, flatwise tensile strength and interlaminar shear strength. To monitor the characteristics of the resin itself, the cured resin was tested using DMA and DSC. As a results, the decrease of Tg value were observed in the specific specimen which is exposed over 50 hrs at $260^{circ}F$. This means the change or degradative of resin properties is also related to the decrease of flatwise tensile properties. Accordingly, minimal exposure on the curing temperature is recommended for parts in order to prevent the delation and maintain the better condition.

• 한국원자력학회:학술대회논문집
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• 한국원자력학회 2005년도 추계학술발표회
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• pp.989-990
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• 2005

• 한국원자력학회:학술대회논문집
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• 한국원자력학회 2005년도 추계학술발표회
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• pp.967-968
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• 2005

• 한국건설순환자원학회논문집
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• 제4권3호
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• pp.243-249
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• 2016

본 연구에서는 시멘트계 보수재 코팅이 철판의 부식 저항성에 미치는 영향을 평가하가 위해 보통 철판(Normal), 용접철판(Welding), 용접 후 보수재 철판(Welding & coating)의 세 가지 경우에 대하여 7일간 ICM(Impressed Current Method)를 통하여 부식을 촉진시켰다. 이후 Faraday 법칙을 통해 얻은 이론 부식률, 실험 부식률 그리고 부식 실험 후 측정한 휨 강도를 비교 평가하였다. Normal case와 Welding case에서는 약 70% 수준의 부식률이 측정되었으며, Welding & coating case에서는 약 17%정도의 부식률이 측정되었다. 이는 시멘트계 보수재료의 코팅이 염화물 이온의 침투를 효과적으로 차단하였으며 이로 인해 부식전류의 발생이 억제되었기 때문이다. 휨 강도 역시 부식률 평가와 같은 경향을 나타내었으며 Welding & coating case에서 Welding case 대비 약 3.4배 큰 강도가 평가되었다. 시멘트계 보수재 코팅이 용접부에 시행되면 용접부 철판의 부식 차단에 효과적일 것으로 판단된다.

• 한국건축시공학회지
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• 제17권3호
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• pp.235-243
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• 2017

본 연구에서는 탄산화가 이미 진행된 콘크리트 구조물을 대상으로 촉진 탄산화 실험을 실시하였다. 각 보수재별 탄산화 속도계수를 도출 후 보수후의 탄산화 진행 예측식을 이용하여 탄산화 진행 예측한다. 또한 신뢰성 확보를 위하여 FDM과 FEM 해석을 통한 탄산화 깊이 예측을 비교했다. 그 결과 보수후 탄산화 예측식을 이용하면 탄산화 깊이를 예측할 수 있으며, 초기 $Ca(OH)_2$ 농도 40%로 가정할 때 해석 값과 실험값이 거의 유사함을 알 수 있었다.

• Composites Research
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• 제36권2호
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• pp.108-116
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• 2023

본 논문에서는 복합재료로 제작된 구조물의 유지보수 자동화를 위한 소형 매니퓰레이터 플랫폼 개발을 위해 기구학적 설계와 다물체 동역학 해석을 수행하였다. 매니퓰레이터의 기구학적 설계를 수행하기 위해 기존복합재 보수 공정을 고려하였다. 보수용 패치 적층 공정을 고려하여 매니퓰레이터와 엔드 이펙터의 기본 제원을 선정한 뒤 3-D 설계를 수행하였다. 이후 보수공정을 고려한 역기구학 해석을 통해 시뮬레이션 및 제어에 필요한 변수를 MATLAB에서 생성하였다. 플랫폼의 구조안정성 평가를 위해 Altair Inspire와 Optistruct를 통한 다물체 동역학 해석을 수행하였다. Inspire에서 진행된 시뮬레이션을 기반으로 Optistruct에서 다물체 동역학 해석을 수행한 뒤 시간에 따른 최대 변위와 Von-Mises 응력 결과를 통해 구조안정성을 검증하였다. 설계검증을 위해 플랫폼의 실제 제작 및 제어를 수행하여 시뮬레이션과 비교한 결과, 실제 보수과정 경로와 시뮬레이션이 잘 일치하는 것을 확인하였다.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 1999년도 추계학술발표대회 논문집
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• pp.154-159
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• 1999

In this paper we present tile results of an experimental investigation on the physical and mechanical properties of carbon fiber grid, polymer mortar, and carbon fiber grid reinforced plain concrete flexural members. In order to repairing and reinforcing damaged and/or deteriorated existing concrete structural members, new materials have been developed and utilized in the construction industries. But the physical and mechanical behaviors of the material are not well understood. To use the material effectively various aspects of the material must be throughly investigated analytically as well as experimentally. In this investigation we found the physical and mechanical properties of carbon fiber grid and polymer mortar which are directly utilized in the repair and reinforcement design of damaged or deteriorated concrete structures. In addition, we also investigate the strengthening effect of carbon fiber grid on the plain concrete flexural test specimens. It was found that the material can be used to repair and strengthen the concrete structures effectively.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2000년도 추계학술발표대회 논문집
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• pp.115-118
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• 2000

The development of high-strength fibers such as boron/epoxy and carbon/epoxy and adhesives has made it possible to repair cracked metallic plates by bonding reinforcing patches to the plate over the crack. In this study, aluminum 6061-T6 alloy plates with the high strength are applied to specimens with a cracked bolt hole to study the effect of diverse patch materials on the fatigue behavior of this structure. Additionally, the observation of the effort of different patch sizes on the specimen was performed. The results shows that the patch repair can improve the static strength by about 17% and the fatigue life by 200% compared with non-repaired case. And it was also revealed that the patching method along to crack growth direction is mort efficient in cost and weight reduction.

• 접착 및 계면
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• 제3권1호
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• pp.30-36
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• 2002

In this paper, some idea about the use of Metal and ceramic filled epoxy adhesive, Anaerobic adhesive and RTV silicone in the assembly, maintain and repair of machinery and equipment is given. Many examples which have been successfully used in Chinese industry are introduced: ${\bullet}$ Wear, Abrasion, Corrosion/Erosion Resistance and Metal Rebuilding Worn shafts, Scored Hydraulic Ram, Bearing Housings, Slurry Pumps (Bodies & Impellers), Slide-ways, Heat Exchangers, Cracked Castings and Molds. Leaking Pipes and Tanks. ${\bullet}$ Locking and Retaining Thread, Bearing, Keyways, Bolts, Nuts, Studs, Gears, Collars, Motors. ${\bullet}$ Scaling and Gasketing Flanges, Pipe Joints, Machined surfaces.

• 대한치과보철학회지
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• 제46권3호
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• pp.261-268
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• 2008

STATEMENT OF PROBLEM: Detachment of the magnetic assembly from the denture base has been a problem in magnetic overdenture patients. PURPOSE: The objectives of this study were to compare the dislodging force by the fixing materials and the designs of the magnetic assembly, and to compare the effect between the fixing materials and the designs of the magnetic assembly. MATERIAL AND METHODS: Two fixing materials, Jet denture repair $acrylic^{(R)}$ and Super-$Bond^{(R)}$ C&$B^{(R)}$ and two types of magnetic assembly designed with or without wing were used. Each magnetic assembly was fixed in the chamber of the denture base resin block ($Lucitone^{(R)}$199) with each fixing material respectively. These specimens were thermocycled 2,000 cycles in the water held at $4^{\circ}C$ and $60^{\circ}C$ with a dwell time of 1 min each time. Each specimen was seated in a testing jig and then a push-out test was performed with a universal testing machine at a cross head speed of 0.5 mm/min to measure the maximum dislodging forces. RESULTS: Comparing the fixing materials, Super-Bond C&$B^{(R)}$ showed superior dislodging force than Jet denture repair $acrylic^{(R)}$. Comparing the design of the magnetic assemblies, the wing design magnetic assembly showed better dislodging force. Combination of the Super-Bond C&$B^{(R)}$ as a fixing material and wing design magnetic assembly revealed a greatest dislodging force. The kind of fixing material was more influential than the type of magnetic assembly. CONCLUSION: The dislodging force of Super-Bond C&$B^{(R)}$ was significantly higher than Jet denture repair $acrylic^{(R)}$. And the dislodging force of magnetic assembly which have wing design was significantly higher than magnetic assembly which have no wing design.