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Flexural rigidity evolvement laws of reinforced concrete beams strengthened with carbon fiber laminates

Journal of Chongqing University 2007年第1期6卷 67-72页

作者：牛鹏志 College of Traffic & Communications South China University of Technology Guangzhou 510640 P.R. China

Extensive research has shown that externally bonded carbon fiber reinforced polymer （CFRP） laminates are particularly suitable for improving the fatigue behavior of reinforced concrete （RC） beams. This paper presents the research on flexural ngidity evolvement laws by testing 14 simple-supported RC beams strengthened with carbon fiber laminates （CFL） under cyclic load, and 2 under monotone load as a reference. The cyclic load tests revealed the peak load applied onto the surface of a supported RC beam strengthened with CFL is linear to the logarithm of its fatigue life, and the flexural rigidity evolvement undergoes three distinct phases： a rapid decrease from the start to about 5% of the fatigue life; an even development from .5% to about 99% of the fatigue life; and a succedent rapid decrease to failure. When the ratio of fatigue ＂cycles to the fatigue life is within 0.0.5 to 0.99, the flexural rigidity varies linearly with the ratio. The peak load does not affect the flexural rigidity evolvement if it is not high enough to make the main reinforcements yield. The dependences of the flexural rigidity of specimens formed in the same group upon their fatigue cycles normalized by fatigue life are almost coincident. This implies the flexural rigidity may be a material parameter independent of the stress level. These relationships of flexural rigidity to fatigue cycles, and fatigue life may be able to provide some hints for fatigue design and fatigue life evaluation of RC member strengthened with CFL; nevertheless the findings still need verifying by more experiments.

关键词： flexural rigidity carbon fiber laminate reinforced concrete beam fatigue

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The Effect of Internal Delamination Damage on the Tensile Strength of Aeronautical Composites

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Acta Mechanica Solida Sinica 2022年第6期35卷 979-986页

作者： Qiang Wang Qiuyu Chen Yujie Chen Jiandong Li Qun Li School of Equipment Management and Unmanned Aerial Vehicle Engineering Air Force Engineering UniversityXi’an710051China State Key Laboratory for Strength and Vibration of Mechanical Structures School of AerospaceXi’an Jiaotong UniversityXi’an710049China School of Air and Missile Defence Air Force Engineering UniversityXi’an710051China

For aeronautical composite materials,the appearance of internal delamination has a fatal impact on their mechanical properties and may even seriously threaten aircraft flight *** this study,the effect of internal delamination damage with different sizes and depths on the tensile strength of aeronautical composites was ***,based on carbon-fiber-reinforced composites commonly used in aircraft,laminate specimens with internal delamination damages of different depths and diameters were fabricated,and tensile tests of composite materials were carried ***,the finite element model for the carbon-fiber-reinforced laminate specimens was established,and the validity of the model was verified by comparing its simulation results with the experimental ***,by changing the geometric parameters of the internal delamination damage model,the influence of delamination damage on the tensile strength of carbon-fiber-reinforced composites was analyzed and *** results show that,on the one hand,for the internal delamination damages of the same area,the closer is the delamination damage to the surface layer,the lower is the tensile *** particular,the closer is the delamination damage to the surface layer,the greater is the decrease in tensile strength,which exhibits an obvious nonlinear *** the other hand,for the internal delamination defects of the same depth,the difference in delamination area has little effect on the tensile *** law provides a reference for the damage detection and maintenance focus of aeronautical composite structures,which is of great significance to ensure the safe use of aeronautical composites.

关键词： Aeronautical composites carbon fiber laminate Delamination damage Tensile strength Finite element simulation

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PREDICTION OF FATIGUE LIVES OF RC BEAMS STRENGTHENED WITH CFL UNDER RANDOM LOADING

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Acta Mechanica Solida Sinica 2008年第4期21卷 359-363页

作者： Rongwei Lin Peiyan Huang Chen Zhao Xinyan Guo Xiaohong Zheng College of Traffic and Communications South China University of Technology Guangzhou 510640 China

The investigation on fatigue lives of reinforced concrete （RC） structures strength- ened with fiber laminate under random loading is important for the repairing or the strengthening of bridges and the safety of the traffic. In this paper, two methods are developed for predicting the fatigue lives of RC structures strengthened with carbon fiber [aminate （CFL） under random loading based on a residual life and a residual strength model. To discuss the efficiency of the model, 12 RC beams strengthened with CFL are tested under random loading by the MTS810 testing system. The predicted residual strength approximately agrees with test results.

关键词： carbon fiber laminate predicted method fatigue life random load RC structure

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