• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2003년도 춘계학술발표대회 논문집
• /
• pp.125-128
• /
• 2003

Low-velocity impact damage is a major concern in the design of structures made of composite materials, because impact damage is hidden inside and cannot be detected by visual inspection. The piezoelectric thin film sensor can be used to detect variations in structural and material properties for structural health monitoring. In this paper, the PVDF and PZT sensors were used for monitoring impact damage initiation in Gr/Ep composite panel to illustrate this potential benefit. A series of impact test at various impact energy by changing impact mass and height is performed on the instrumented drop weight impact tester. The wavelet transform(WT) is used to decompose the piezoelectric sensor signals in this study. Test results show that the particular waveform of sensor signals implying the damage initiation and development are detected above the damage initiation impact energy. And it is found that both PZT and PVDF sensors can be used to detect the impact damage.

• Steel and Composite Structures
• /
• 제20권3호
• /
• pp.719-729
• /
• 2016

There are great needs of simple but reliable mechanical nonlinear behavior analysis and performance evaluation method for frames constructed by steel and concrete composite beams or columns when the structures subjected extreme loads, such as earthquake loads. This paper describes an approach of simplified macro-modelling for composite frames consisting of steel-concrete composite beams and CFST columns, and presents the performance evaluation procedure based on the pushover nonlinear analysis results. A four-story two-bay composite frame underground is selected as a study case. The establishment of the macro-model of the composite frame is guided by the characterization of nonlinear behaviors of composite structural members. Pushover analysis is conducted to obtain the lateral force versus top displacement curve of the overall structure. The identification method of damage degree of composite frames has been proposed. The damage evolution and development of this composite frame in case study has been analyzed. The failure mode of this composite frame is estimated as that the bottom CFST columns damage substantially resulting in the failure of the bottom story. Finally, the seismic performance of the composite frame with high strength steel is analyzed and compared with the frame with ordinary strength steel, and the result shows that the employment of high strength steel in the steel tube of CFST columns and steel beam of composite beams benefits the lateral resistance and elasticity resuming performance of composite frames.

• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2001년도 춘계학술발표대회 논문집
• /
• pp.69-73
• /
• 2001

Damage induced by low-velocity impact on the curved composite laminates was experimentally evaluated for CFRP cylindrical shells with the radius of curvatures of 50, 150, 300, and 500 mm. The result was then compared with that of flat laminates. The radius of curvatures and the effective shell stiffness appeared to considerably affect the dynamic impact response of curved shells. Under the same impact energy level, the maximum contact force increased with the decreasing radius of curvatures, with reaching 1.5 times that for plates at the radius of curvature of 50 mm. Since the maximum contact force is directly related to the impact damage, curved laminates can be more susceptible to delamination and less resistant to the low-velocity impact damage. The distribution of delamination along the thickness direction of curved laminates are also different from that of flat plates. Delamination was distributed rather even]y at each interface along the thickness direction of curved laminates. This implies that the effect of curvatures has to be considered for the design of a curved composite laminate.

• 한국정밀공학회지
• /
• 제29권6호
• /
• pp.654-663
• /
• 2012

Damage induced by low velocity impact loading in aircraft composite is the form of failure which is frequently occurred in aircraft. As the consequences of impact loading in composite laminates, matrix cracking, delamination and eventually fiber breakage for higher impact energies can be occurred. Even when no visible impact damage is observed, damage can exist inside of composite laminates and carrying load of the composite laminates is considerably reduced. The objective of this study is to evaluate and predict residual strength behavior of composite laminates by impact loading and for this, tensile test after impact was carried out on composite laminates made of woven CFRP.

• 한국정밀공학회:학술대회논문집
• /
• 한국정밀공학회 2002년도 추계학술대회 논문집
• /
• pp.689-692
• /
• 2002

Composite materials, when damaged under thermal or mechanical loadings, show property changes. Among many mechanical properties of composite materials. the stiffness tend to be reduced due to micro-cracking, debonding, or delamination caused by external loadings. This research presents results regarding the detecting technique of internal damages within composite that experienced low-velocity impacts. Post-damage evaluations were made experimentally using flexural and compression loadings. Preliminary finite element analysis was made and compared with analytical solutions. The experimental results to determine the degree of damage will be compared with finite element results.

• Composites Research
• /
• 제26권2호
• /
• pp.79-84
• /
• 2013

본 연구에서는 적층판 시편의 피로손상 균열진전 시험결과와 적층보강판 구조의 응력강도 해석결과를 기초로 충격손상을 모사한 원공과 노치손상을 내재한 보강재 본딩접합 적층보강판 구조의 피로손상 균열진전 수명예측에 대하여 고찰하였다. 그리고 적층보강판 구조시편에 대한 손상허용 시험결과와 손상진전 수명예측 해석결과를 비교분석한 결과 손상균열 길이 변화에 따라 최종파단에 대한 잔여강도를 예측하고 손상허용성 평가를 할 수 있었다.

• 한국정밀공학회지
• /
• 제10권4호
• /
• pp.152-162
• /
• 1993

The purpose of this study is to investigate problems of residual bending strength and the impact damage experimentally when CFRP composite laminates are subjected to Foreign object damage. The specimens composed of four types of CR/EPOXY and a CF/PEEK composite laminates which involved difference of fiber stracking orientation and matrics. The result were summariged as follows : 1) It is found that both orthotropic and guasi-isotropic composite laminates are increasimg lineally between impact energy and damage delamination area. 2) Delamination devel- opment energy(mm$^{2}$J) OF cf/epoxy composite aminates is less than that of CF/PEEK. 3) When impact energy is applied to specimens within 3J, the residual strength of orthotropic is greater than guasi-isotropic composite laminates. On the other hand, it is predicted that residual bending strength of orthotropic composite laminates is less than that of quasi-isotropic when impact energy is more thaen 3J. 4) It is found in CF/PEEK that for the impact side compression, residual of bending strength versus impact energy is almost constant, while in case of impact side tension, residual bending strength is decreased rapidly near 1.2J. of impact energy due to the effect of delamination buckling.

• Composites Research
• /
• 제25권4호
• /
• pp.105-109
• /
• 2012

최근 국내에서 미국과 상호항공안전협정 체결을 위한 소형 항공기가 연구 개발 중이다. 연구 대상 항공기는 경량화 하여 연료 절감을 위해 전기체 복합재료가 적용되었다. 그러나 복합재 구조는 외부의 충격 손상에 취약한 구조이다. 따라서 항공기 구조물은 충격 손상에 대한 압축 파손 강도를 고려하여 손상 허용 설계가 반드시 수행되어야 한다. 이는 복합재 구조 항공기 인증에 매우 중요한 요소이다. 본 연구에서는 항공기 복합재 구조에 적용된 두꺼운 적층판에 대한 손상 허용 연구를 수행하였다. 두꺼운 적층판의 세 가지 형태인 손상이 없는 시편, 구멍 손상 및 충격 손상이 적용된 시편의 압축 하중 하에서 손상 허용 기준이 평가되었다.

• Structural Engineering and Mechanics
• /
• 제80권5호
• /
• pp.563-583
• /
• 2021

Composite materials, composed of multiple constituent materials with dissimilar properties, are actively adopted in a wide range of industrial sectors due to their remarkable strength-to-weight and stiffness-to-weight ratio. Nevertheless, the failure mechanism of composite materials is highly complicated due to their sophisticated microstructure, making it much harder to predict their residual material lives in real life applications. A promising solution for this safety issue is structural damage detection. In the present paper, damage detection of composite material via electrical resistance-based technique and infrared thermography is reviewed. The operating principles of the two damage detection methodologies are introduced, and some research advances of each techniques are covered. The advancement of IR thermography-based non-destructive technique (NDT) including optical thermography, laser thermography and eddy current thermography will be reported, as well as the electrical impedance tomography (EIT) which is a technology increasingly drawing attentions in the field of electrical resistance-based damage detection. A brief comparison of the two methodologies based on each of their strengths and limitations is carried out, and a recent research update regarding the coupling of the two techniques for improved damage detection in composite materials will be discussed.

• 항공우주시스템공학회지
• /
• 제7권1호
• /
• pp.39-43
• /
• 2013

In this study, damage assesment and repair technique of aircraft adopted on Sandwich composite structure were performed. The sandwich composite structure were damaged by drop weight type impact test machine. The damaged sandwich composite structure was repaired using external patch repair method after removing damaged area. This study presents comparison results of the experimental investigation between the impact damaged and the repaired specimen.