• 한국해양공학회지
• /
• 제25권6호
• /
• pp.56-59
• /
• 2011

The demand for cold rolled steel (CR) for structural members is gradually increasing. If no surface treatment (coating for corrosion resistance) for CR is conducted, its use is very limited because CR is vulnerable to corrosion. Therefore, we need to develop a coating solution to provide high corrosion resistance for CR. In this study, an organic/inorganic coating solution with Si and Ti (Si polysilicate 7 wt.% + Urethane 13 wt.% + Ti amorphous 0.5 wt.%; LR-0727(1)) was used to evaluate the corrosion resistance of CR under a salt spray test. The specimens with the LR-0727(1) coating were heat treated in a drying oven at $120{\sim}210^{\circ}C$for 5 min. The corrosion resistance was investigated using a salt spray test of 7 h. In addition, an adhesive test was conducted. Rust showed under a heat treatment of $150^{\circ}C$, but no vestiges were found over $160^{\circ}C$. The specimens with heat treatment at $160^{\circ}C$ or more did not experience delamination. From these results, it is considered that the temperature limit for optimum heat treatment is $160^{\circ}C$ considering energy efficiency.

• Composites Research
• /
• 제12권3호
• /
• pp.1-7
• /
• 1999

Al2024-T3 판재에 카본/에폭시(carbon/epoxy) 라미네이트를 섬유배열 방향 $0^{\circ}$/$90^{\circ}$ 및 $\pm$$45^{\circ}$로 2 Plies 보강하여 CPAL(Carbon Patched ALuminum alloy)재를 제작하고, 응력비 R=0.2, 0.5에서 피로균열전파 실험을 실시하였다. X-Ray와 초음파 C-Scan 장비를 이용하여 A/2024-T3 판재의 균열과 CFRP 라미네이트 박리 거동을 조사하여 피로균열 지연 거동과 지연기구(mechanism)를 연구하였다. A/2024-T3 시험편에 비해서 CPAL 시험편은 피로균열전파속도가 현저하게 지연되었으며, 지연 정도는 $0^{\circ}$/$90^{\circ}$ CPAL이 $\pm$$45^{\circ}$ CPAL 시험편보다 크고, 응력비 R=0.2에서 응력비 R=0.5보다 크게 나타났다. CPAL 시험편의 피로균열 지연 효과는 균열후방의 박리 및 비박리 CFRP 라미네이트가 A/2024-T3 판재의 균열열림(COD)을 감소시키는 균열브리징미케니즘(crack bridging medhanism) 때문에 발생함을 확인하였다.

• 비파괴검사학회지
• /
• 제18권4호
• /
• pp.278-291
• /
• 1998

연속섬유강화 복합재료의 경우 보강섬유의 파괴, 모재의 파괴, 섬유와 모재의 분리, 층간파괴 등의 복합적인 파괴현상이 동반되고 특히 균열성장과 균열성장 정지가 균열가교 현상 때문에 반복되므로 안정성장과 불안정성장이 불규칙하게 반복된다. 따라서 주균열 성장의 개시점과 불안정 파괴점에서의 파괴인성치를 정확하게 결정한다는 것은 매우 어려운 것이다. 본 연구에서는 CFRP에 대하여 파괴인성 실험과 병행하여 실시간으로 결함을 검출하는 새로운 방법인 AE분석법 및 비디오 마이크로 스코프를 이용하여 파괴과정을 기록하여 검토, 분석함으로서 손상의 정도와 파괴기구를 규명하였을 뿐만 아니라 주균열 성장의 개시점, 균열가교 역할을 하는 섬유다발의 파단점, 균열의 불안정 파괴 개시점을 찾아 이를 기초로 균열진전 저항곡선에 의한 파괴인성치를 평가하여 신뢰성 있는 파괴인성 측정법을 제시하였다.

• 비파괴검사학회지
• /
• 제37권2호
• /
• pp.99-105
• /
• 2017

Many composite materials are used in the aerospace industry because of their excellent mechanical properties. However, the nature of aviation exposes these materials to high temperature and high moisture conditions depending on climate, location, and altitude. Therefore, the molecular arrangement chemical properties, and mechanical properties of composite materials can be changed under these conditions. As a result, surface disruptions and cracks can be created. Consequently, moisture-impregnating defects can be induced due to the crack and delamination of composite materials as they are repeatedly exposed to moisture absorption moisture release, fatigue environment, temperature changes, and fluid pressure changes. This study evaluates the possibility of detecting the moisture-impregnating defects of CFRP and GFRP honeycomb structure sandwich composite materials, which are the composite materials in the aircraft structure, by using an active infrared thermography technology among non-destructive testing methods. In all experiments, it was possible to distinguish the area and a number of CFRP composite materials more clearly than those of GFRP composite material. The highest detection rate was observed in the heating duration of 50 mHz and the low detection rate was at the heating duration of over 500 mHz. The reflection method showed a higher detection rate than the transmission method.

• 한국강구조학회 논문집
• /
• 제27권4호
• /
• pp.359-370
• /
• 2015

본 연구에서는 AFRP 스트립과 강재사이의 부착거동에 관한 실험적 연구를 수행하였다. 실험적 연구를 통해 AFRP 판과 강판사이의 계면부착거동을 관찰하고, 계면부착응력을 산정하는 것이 본 연구의 목표이다. 실험변수로는 부착길이와 AFRP의 두께를 선택하였으며, 18개의 일면전단시편 제작하여 실험을 수행하였다. 실험결과 부착길이와 AFRP 두께가 증가함에 따라 하중값을 증가하였으며, 부착길이와 AFRP 두께가 증가함에 따라 각각 63%, 86%의 하중값이 증가하였다. 끝으로 강재와 AFRP 사이의 부착응력-슬립관계를 산정하였다. 부착응력-슬립관계는 탄성선형거동을 보이고 있으며, 부착길이와 AFRP 두께는 부착응력과 파괴에너지에 영향을 덜 미치는 것으로 나타났다.

• 한국항공우주학회지
• /
• 제36권9호
• /
• pp.841-850
• /
• 2008

본 연구에서는 탄소 복합재와 알루미늄 2024-T3 단일겹침 체결부에 대해, 체결방법을 접착, 리벳, 리벳/접착 하이브리드의 세 가지로 변화시키면서 체결방법에 따른 파손하중과 파손모드를 실험을 통해 연구하였다. 세 가지 체결방법에 대해 각각 겹침길이 3가지와 적층순서 2가지, 총 82개의 시편을 제작하였다. 접착제는 FM73m, 리벳은 NAS9308-4-03을 사용하였다. 접착 체결과 하이브리드 체결에서는 겹침길이가 커짐에 따라 파손하중이 증가하였고, 리벳 체결에서는 겹침길이에 따른 파손하중 변화가 나타나지 않았다. 단순 접착 및 리벳 체결부에서는 적층순서에 따른 일관된 경향을 발견하기 어려운 반면, 하이브리드 체결부에서는 인접층의 적층각 차이가 작은 적층판을 사용한 체결부의 파손하중이 높게 나타났다. 접착 체결과 하이브리드 체결의 주된 파손모드는 층간분리이고 리벳 체결은 국부적 베어링 파손을 동반한 리벳 파손으로 나타났다.

• 한국해안해양공학회지
• /
• 제18권1호
• /
• pp.15-20
• /
• 2006

해저환경에서 PMC(고분자기지 복합재)는 금속재 구조물에 비해 부식성이 우수한 것으로 알려져 있다. 해저환경에서 고분자기지 복합재의 파괴특성에 대한 이해는 증가하는 해저구조물 제조에 반드시 필요하다. 본 연구에서, 파괴시험은 해수흡수 된 카본/에폭시 복합재에 대해 정수압을 네단계(0.1 MPa, 100 MPa, 200 MPa and 270 MPa)로 증가시켜 수행하였다. 파괴인성은 정수압에서의 일인자방법을 적용하였다. 파괴거동은 모든 정수압에서 선형적이었고 파괴인성은 정수압이 증가할수록 증가하였다.

• Clinics in Shoulder and Elbow
• /
• 제19권4호
• /
• pp.197-201
• /
• 2016

Background: The purpose of the study was to compare the degree of degeneration of the articular and bursal layers of delaminated supraspinatus tendons based on histological examination. Methods: Fifty-four patients with a full-thickness rotator cuff tear were included in the study. Tendon specimens were harvested during arthroscopic rotator cuff repair from the lateral torn edges of the articular and bursal layers of the delaminated tear. Harvested samples were stained with H&E dye and evaluated based on a semi-quantitative grading scale. Results: There were no significant differences in the seven histological characteristics of tendon degeneration: fiber structure, fiber arrangement, round nuclei, regional variations in cellularity, vascularity, collagen stainability, and hyalinization between the articular and bursal layers of the delaminated rotator cuff tear (all p>0.05). Total degeneration scores of articular and bursal sides were $13.1{\pm}3.85$ points and $13.2{\pm}3.42$ points, respectively, and were not significantly different (p=0.958). Conclusions: The study demonstrates that tendon degeneration was similar in the articular and bursal sides of the delaminated full-thickness rotator cuff tear, suggesting that degeneration would be a main etiology for the rotator cuff tear not only in the articular side but also in the bursal side. Considering potential disadvantages of subacromial decompression, this study tentatively suggests routine use of subacromial decompression as well as the need for halting or recovery from rotator cuff degeneration for better rotator cuff repair.

• 한국안전학회지
• /
• 제25권3호
• /
• pp.34-39
• /
• 2010

Unidirectional Carbon Fiber Reinforced Plastics (CFRP) are advanced materials which combine the characteristics of the light weight, high stiffness and strength. For those reasons, the use of the unidirectional CFRP has increased in jet fighters, aerospace structures. However, unidirectional CFRP composites have a lot of problems, especially delamination, compared with traditional materials such as steels and aluminums, and so forth. Therefore, the interlaminar fracture toughness for a laminate CFRP composite is very important. In this study, The mode II interlaminar fracture toughness was measured by using center notched flexure(CNF) test specimen. The CNF specimens using unidirectional carbon prepreg were fabricated by a hot-press with the gage pressure and temperature controller. And three kinds of a/L ratio was applied to these specimens. Here, we discuss the relations of the crack growth and the mode II interlaminar fracture under the four point bending CNF test. From the results, we shows that mode II interlaminar was occurred when the more $a_0$/L ratio, the less load. And $G_{IIC}$ also were obtained as 5.33, 2.9 and $0.58kJ/m^2$ according to $a_0$/L ratio=0.2, 0.3 and 0.4.

• Structural Engineering and Mechanics
• /
• 제74권6호
• /
• pp.723-735
• /
• 2020

This study is reported the adhesion failure in adhesive bonded composite and specifically for the T-joint structure. Three-dimensional finite element analysis has been performed using a commercial tool and the necessary outcomes are obtained via an eight noded solid element (Solid 185-element) from the library of ANSYS. The structural analysis input has been incurred through ANSYS parametric design language (APDL) code. The normal and shear stress distributions along different layers of the joint structure have been evaluated as the final outcomes. Based on the stress distributions, failure location in the composite joint structure has been identified by using the Tsai-Wu stress failure criterion. It has been found that the failure index is maximum at the interface between flange and web part of the joint (top layer) which indicates the probable location of failure initiation. This kind of failures are considered as adhesion failure and the failure propagation is governed by strain energy release rate (SERR) of fracture mechanics. The different adhesion failure lengths are also considered at the failure location to calculate the SERR values i.e. mode I fracture (opening), mode II fracture (sliding) and mode III fracture (tearing) along the failure front. Also, virtual crack closure technique (VCCT) principle of fracture mechanics steps is used to calculate the above said SERRs. It is found that the mode I SERR is more dominating compared to other two modes of failure for the joint considered. Finally, the influences of various parametric (geometrical and material) effect on SERR of the joint structure are evaluated and discussed in details.