Study of damage behavior and repair effectiveness of patch repaired carbon fiber laminate under quasi-static indentation loading

Damage caused due to low-velocity impacts in composites leads to substantial deterioration in their residual strength and eventually provokes structural failure.This work presents an experimental investigation on the effects of different patch and parent laminate stacking sequences on the enhancement of impact strength of Carbon Fiber Reinforced Polymers(CFRP)composites by utilising the adhesively bonded external patch repair technique.Damage evolution study is also performed with the aid of Acoustic Emission(AE).Two different quasi-isotropic configurations were selected for the parent laminate,viz.,[45°/45°/0°/0°]s and[45°/0°/45°/0°]s.Quasi Static Indentation(QSI)test was performed on both the pristine laminates,and damage areas were detected by using the C-scan inspection technique.Damaged laminates were repaired by using a single-sided patch of two different configurations,viz.,[45°/45°/45°/45°]and[45°/0°/0°/45°],and employing a circular plug to fill the damaged hole.Four different combinations of repaired laminates with two configurations of each parent and patch laminate were produced,which were further subjected to the QSI test.The results reveal the effectiveness of the repair method,as all the repaired laminates show higher impact resistance compared to the respective pristine laminates.Patches of[45°/0°/0°/45°]configuration when repaired by taking[45°/45°/0°/0°]s and[45°/0°/45°/0°]s as parents exhibited 68%and 73%higher peak loads,respectively,than the respective pristine laminates.Furthermore,parent and patch of configuration[45°/0°/45°/0°]s and[45°/0°/0°/45°],respectively,attain the highest peak load,whereas[45°/45°/0°/0°]s and[45°/45°/45°/45°]combinations possess the most gradual decrease in the load.

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

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.

Analysis of vibration attenuation characteristics of large thickness carbon fiber composite laminates

The vibration attenuation and damping characteristics of carbon fiber reinforced composite laminates with different thicknesses were investigated by hammering experiments under free boundary constraints in different directions.The dynamic signal testing and analysis system is applied to collect and analyze the vibration signals of the composite specimens,and combine the self-spectrum analysis and logarithmic decay method to identify the fundamental frequencies of different specimens and calculate the damping ratios of different directions of the specimens.The results showed that the overall stiffness of the specimen increased with the increase of the specimen thickness,and when the thickness of the sample increases from 24mm to 32mm,the fundamental frequency increases by 35.1%,the vibration showed the same vibration attenuation and energy dissipation characteristics in the 0°and 90°directions of the specimen,compared with the specimen in the 45°direction,which was less likely to be excited and had poorer vibration attenuation ability,while the upper and lower surfaces of the same specimen showed slightly different attenuation characteristics to the vibration,the maximum difference of damping capacity between top and bottom surfaces of CFRP plates is about 70%.

Corrosion damage evolution and mechanical properties of carbon fiber reinforced aluminum laminate

Fiber metal laminates(FMLs),a kind of lightweight material with excellent comprehensive performance,have been successfully applied in aerospace.FMLs reinforced with carbon fiber have better mechanical properties than those with glass or aramid fiber.However,carbon fiber binding metal may lead to galvanic corrosion which limits its application.In this paper,electrochemical methods,optical microscope and scanning electron microscope were used to analyze the corrosion evolution of carbon fiber reinforced aluminum laminate(CARALL)in corrosive environment and explore anti-corrosion ways to protect CARALL.The results show that the connection between carbon fiber and aluminum alloy changes electric potential,causing galvanic corrosion.The galvanic corrosion will obviously accelerate CARALL corroded in solution,leading to a 72.1%decrease in interlaminar shear strength,and the crevice corrosion has a greater impact on CARALL resulting in delamination.The reduction of interlaminar shear strength has a similar linear relationship with the corrosion time.In addition,the adhesive layers between carbon fiber and aluminum alloy cannot protect CARALL,while side edge protection can effectively slow down corrosion rate.Therefore,the exposed edges should be coated with anti-corrosion painting.CARALL has the potential to be used for aerospace components.

DELAMINATION FORMATION AND DELAMINATION PROPAGATION OF COMPOSITE LAMINATES UNDER COMPRESSIVE FATIGUE LOADING

Fatigue tests of the smooth composite laminates and the notched composite laminates under compressive cyclic loading have been carried out. The damage mechanism is discussed and analyzed. Damage evolution is monitored using stiffness decay. From these tests, it is found that the initial delamination occurs at the free boundary of smooth specimens, or the notch boundary of notched specimens, subjected to the compression-compression cyclic load. A point of view in relation to two-phases of compression fatigue delamination of composites is proposed, namely, compression-compression delamination consists of the delamination formation phase and the delamination propagation, and there is a 'damage transition point' to separate this two-phases. Furthermore, an empirical modulus degradation formula and its parameters fitting method are presented. According to the test data handling results, it is shown that this formula is univocal and can fit the test data conveniently. In addition, two kinds of new anti-buckling devices are designed for these tests. At last, the E-N curves, the D-N curves and the S-N curve of the smooth carbon fiber reinforced composite laminates of T300/648C are determined to predict the fatigue life of the notched composite laminate. And the E-N curve of the notched specimens at the given load ratio R = 10 and minimum load Pmin = -0.45 kN is also measured to verify the estimated result of fatigue life.

Automatic Damage Detection and Monitoring of a Stitch Laminate System Using a Fiber Bragg Grating Strain Sensor

There are numerous aspects and questions related to the use of composite materials for primary structures in aircraft where the structural integrity is the most important factor. This is especially true if the main concerns are that the material should have good reliability and durability for the primary structural application. Composite laminates are highly sensitive to out-of-plane failure due to their low inter laminar fracture toughness. An alternate method to increase the damage resistance is through three-dimensional fibrous reinforcement such as through-the-thickness stitching with a single fiber as the thread. Recent studies have shown that the stitching of standard laminates can enhance damage tolerance to levels obtainable with toughened resin systems. However, for next-generation aircraft, material improvement alone is not enough to assure or increase the safety and reliability of the structure. Continuous damage monitoring during operation will become an important issue in aircraft safety. Embed ding fiber Bragg grating (FBG) technology into the composite structure as strain sensors could potentially solve the above problem because the FBG can be used to detect and characterize the damage before it reaches a critical stage. The model used to represent this problem is a 6 × 6 Vectran stitched carbon/ epoxy laminate under tension loading, and the real-time monitoring using the FBG strain sensors is combined with acoustic emissions that were conducted during the test. A numerical laminate theory using a rebar element and first-ply failure criterion is performed to determine the preferred area on the specimen for the placement of the FBG before manufacturing and testing. Experiments are presented to determine the damage growth that was quantified with an ultrasonic (water immersion) c-scan. In this research, the FBG successfully detected and characterized the damage in the carbon/epoxy stitch laminate caused in tension loading cases. The FBG is enhanced with acoustic emission data and can quantitatively predict the damage growth.

Detection of stacking orientation error of CFRP composite laminates using ultrasound waves

A jig was developed for generating a shear wave. A pyramid with an isosceles triangle with two 45o was made of aluminum to generate shear waves using two longitudinal transducers based on ultrasonic-polarized mechanism. Also, the signal splitter was connected to the pulser jack on the pulser/receiver and to the longitudinal transducers. Therefore, an experimental way was performed in order to make shear wave on the bottom of aluminum alloyed pyramid. Also, a jig was manufactured and developed for generating a shear wave based on the computer numerical simulation. It is found that the experimentally shear wave variation of newly-designed jig is consistent with computer numerical simulation results and shear wave ultrasonic application can be very useful to detect the defects in CFRP composites.

CFL增强RC梁的疲劳累积损伤模型

通过碳纤维薄板(CFL)增强钢筋混凝土(RC)梁的三点弯曲疲劳试验,得到了构件疲劳寿命曲线及其跨中挠度、抗弯刚度的演化规律;采用增强梁的剩余抗弯刚度来定义损伤变量,建立了描述其损伤、断裂过程的疲劳累积损伤模型,并对CFL增强RC梁的疲劳损伤演化历程进行了数值分析.结果表明,文中提出的疲劳累积损伤模型能够准确地描述包括混凝土开裂、CFL与混凝土剥离、钢筋屈服等破坏模式在内的CFL增强RC梁的疲劳损伤、破坏过程.

CFL增强RC梁抗弯疲劳强度的实验研究

疲劳强度是进行结构抗疲劳设计的重要力学参量。通过对5组24条碳纤维薄板(CFL)增强RC梁进行三点弯曲常幅疲劳试验,得到了增强梁的容许疲劳寿命和极限疲劳寿命S-N曲线及其相应的表达式,并推定其容许疲劳强度和极限疲劳强度分别为其极限承载力的62%和68%。还给出了新的疲劳寿命曲线的表达形式:载荷做功的功率H与增强梁的疲劳寿命N的关系曲线(H-N曲线),并由此推定了增强梁的容许疲劳强度和极限疲劳强度所对应的功率值。

环境温度对CFL增强RC梁承载能力的影响

对温度场中碳纤维薄板(CFL)增强钢筋混凝土(RC)梁在不同破坏模式下的承载能力进行理论分析.研究结果表明,环境温度的变化对CFL增强RC梁的承载能力有一定程度的影响:(1)当环境温度升高30K时,CFL厚度分别为0.1、0.2、0.3和0.4mm的增强RC梁的开裂载荷分别提高了5.37%、10.46%、15.9%和20.94%;(2)CFL厚度为0.1mm和0.2mm的增强RC梁的破坏模式为CFL拉断,其极限承载力随环境温度的升高呈下降趋势,但降低幅度小于3.5%;(3)CFL厚度为0.3mm和0.4mm的增强RC梁的破坏模式为混凝土压碎,其极限承载力随环境温度的升高呈上升趋势,但升高幅度小于3.5%.

CFL增强RC梁疲劳寿命的试验推定

在对5组23根碳纤维薄板（CFL）增强RC粱（1850mm×100mm×200mm）进行常幅弯曲疲劳试验的基础上，探讨了增强梁的跨中挠度、载荷循环次数、载荷等级以及疲劳寿命等变量之间的关系，得到了一组相应的线性关系式．据此提出了一种预测CFL增强RC梁疲劳寿命的新方法：在指定的疲劳载荷水平下，只需对CFL增强RC梁实施一些非破坏性的少量循环载荷试验（载荷循环次数推荐值为10～1000），就能够较好地预测该载荷条件下CFL增强RC梁的疲劳寿命．

CFL加固受弯钢板中表面裂纹应力强度因子的数值分析

借助ANSYS建立了碳纤维薄板(CFL)加固钢板中半椭圆型三维表面裂纹的应力强度因子有限元计算模型,讨论了CFL厚度、裂纹形状比、裂纹面积对CFL加固受弯钢板中三维表面裂纹应力强度因子的影响.研究结果表明:CFL加固含裂纹的钢结构能够大幅度地降低裂纹的应力强度因子;应力强度因子的降低速率随CFL厚度的增加而减小;裂纹面积越大的表面裂纹,在CFL加固后其应力强度因子降低的幅度越大,加固效果越明显;对于含细长裂纹的受弯钢板,CFL正面加固的效果更为显著.

受弯CFL加固RC梁界面疲劳裂缝扩展行为研究

碳纤维薄板(CFL)与混凝土粘结界面的疲劳性能是CFL加固RC梁关键的力学问题之一。应用疲劳与断裂力学方法给出了受弯CFL加固RC梁界面疲劳裂缝尖端的应力强度因子计算方法,并结合理论推导与一系列的疲劳实验研究,对加固梁中CFL与混凝土界面疲劳裂缝扩展的规律和预测方法进行了分析。结果表明:1)CFL的应变值与界面裂缝的应力强度因子的大小成正比,是界面疲劳裂缝扩展寿命的决定因素。当CFL的应变值小于疲劳破坏门槛值时,界面疲劳裂缝不会发生扩展;2)界面裂缝扩展主要分为萌生、稳定扩展、失稳扩展三个阶段。受弯CFL加固RC梁的界面疲劳裂缝的扩展寿命可以用类似于Paris公式的方法较准确地预测。

随机变幅疲劳荷载下CFL增强RC梁疲劳寿命的试验研究

基于321国道上1个月内通过某桥的随机车流量数据,经过一系列的转换得到试验用的随机变幅疲劳荷载谱,并通过MTS810疲劳试验机实现了随机变幅疲劳荷载下碳纤维薄板(CFL)增强RC梁三点弯曲疲劳试验。试验结果表明:与普通RC梁相比,CFL的加固显著提高了随机疲劳荷载作用下RC梁的疲劳寿命,改善了其疲劳性能;随机变幅荷载下增强梁的疲劳损伤演化和疲劳破坏模式与常幅疲劳荷载相同;但随着疲劳荷载水平和荷载幅值的增大,随机变幅疲劳荷载作用下构件的疲劳寿命低于常幅疲劳荷载作用下得到的寿命,因此结构设计中采用常幅疲劳试验结果估算实际服役构件的疲劳寿命和进行疲劳设计是不安全的。

桥梁拼接中CFL技术的理论研究

讨论了桥梁拼接技术中伸缩缝连接、刚性连接和碳纤维薄板(CFL)连接3种方案。基于3个基本假定,应用有限元原理建立CFL弹性薄壳单元模型,给出了CFL弹性薄壳单元刚度矩阵。以一座跨径组合为5×30 m的5跨预应力混凝土连续箱梁拓宽工程为例,对刚性拼接和CFL拼接结构分别建立三维有限元模型。重点研究了CFL拼接结构的三维仿真模型。对于不同拼接方案,对比分析新旧桥拼接后结构内力及位移的变化情况。研究结果表明,相对于常用的刚性拼接方案,CFL拼接方案对于既有箱梁的轴力、弯矩、剪力的变化影响较小,是桥梁拓宽工程中的一种可行的纵缝拼接方案。

CFL增强RC梁正截面抗弯疲劳设计

FRP材料在砼结构的加固工程中已得到广泛的应用,但现行加固规程主要采用静力作用下的极限状态设计方法,没有考虑疲劳荷载作用对结构性能的影响,在结构的使用中偏于不安全。通过对等幅循环荷载下碳纤维薄板(CFL)增强RC梁三点弯曲疲劳实验,得到CFL增强梁的刚度、挠度、混凝土裂纹扩展以及CFL与混凝土的界面的疲劳损伤演化规律,揭示了在等幅循环荷载下增强梁的疲劳破坏机理;通过对CFL增强RC梁正截面疲劳极限状态的分析,考虑施加的荷载幅值、疲劳破坏模式、FRP与混凝土的粘结应力对结构疲劳寿命的影响,提出了CFL增强RC梁在等幅循环荷载作用下的正截面抗弯疲劳设计方法。

CFL增强RC梁抗弯刚度的衰减规律

在对4组共20根碳纤维薄板（CFL）增强钢筋混凝土（RC）梁进行三点弯曲疲劳试验的基础上，探讨了增强梁的抗弯刚度与损伤变量、荷载循环次数、荷载等级以及疲劳寿命之间的关系，得到以下结论：（1）抗弯刚度的衰减曲线包括初始的快速减小阶段、稳定衰减阶段和构件失稳后的快速减小阶段；（2）增强梁正则化抗弯刚度和循环次数在稳定衰减阶段有较好的线性关系；（3）线性刚度比介于0．55—0．79之间，平均值为0．67；（4）破坏刚度比介于0．53～0．73之间，平均值为0．63；（5）增强梁疲劳破坏时损伤变量约为0．37．

CFL加固RC梁疲劳寿命预测

目的建立疲劳寿命预测模型,为加固构件的抗疲劳设计提供新的方法.方法提出了一种可以同时考虑钢筋、混凝土和碳纤维耦合作用下的动态损伤模型.定义加固梁的剩余抗弯刚度为损伤变量,在正截面应力分析的基础上,运用分段线性原理,分析了碳纤维薄板加固梁在疲劳载荷下刚度衰减规律.结果利用动态损伤模型,数值模拟了碳纤维薄板加固钢筋混凝土梁受弯构件疲劳损伤全过程,计算了加固梁的疲劳寿命.结论由于考虑了组成材料损伤机制不同而造成的疲劳损伤过程中的应力重分布现象,动态损伤模型能够较好地预测CFL增强RC梁的疲劳寿命.

CFL增强RC梁挠度分析(英文)

碳纤维薄板(CFL)加固RC梁技术已成功地应用于桥梁工程。该方法的关键科学问题之一是疲劳荷载下增强梁的变形规律。结合一系列疲劳试验,给出了挠度的发展规律,提出界面疲劳裂缝扩展寿命的预测方法。分析结果表明:构件挠度扩展主要分为三个阶段:快速增加、稳定扩展、失稳扩展,其中第二阶段是构件疲劳寿命的主要阶段,在此阶段挠度缓慢增加,增加量与加载次数成线性关系。采用理论与实验相结合的方法给出了疲劳荷载下挠度的计算公式和疲劳寿命的预测公式,可以较好地符合试验结果。

常幅循环荷载下CFL增强RC梁弯曲疲劳性能研究

通过碳纤维薄板(CFL)加固RC梁三点弯曲疲劳实验,得到了常幅疲劳荷载作用下加固梁挠度、CFL与钢筋应变的演化规律;试验过程中加固梁刚度的疲劳损伤、CFL与混凝土界面的疲劳剥离都呈现初始快速扩展、稳定扩展、失稳扩展的三阶段发展规律。通过对CFL加固梁的疲劳破坏机理的分析,指出钢筋的疲劳屈服导致CFL的剥离是加固梁最主要的破坏模式,其疲劳寿命主要取决于控制截面受拉钢筋的应力幅值,提出采用疲劳损伤第二阶段的钢筋应力幅值的△S-N曲线与国外试验结果吻合较好。