薄层合板单面贴补修理拉伸性能研究

贴补修理是工艺简单、应用较广的复合材料结构修补技术。对含有孔穿透损伤的复合材料层合板单面贴补修理试验件进行拉伸试验,保持补片的铺层顺序、厚度不变,改变补片的直径,考察补片直径对单面贴补修理效果的影响,并根据试验过程中采集的试验件相应位置的应变数据以及载荷位移曲线分析其失效机理。结果表明,单面贴补修理试验件的强度恢复率约为34%～50%,且贴补修理对于含穿透孔损伤层合板的刚度具有一定的恢复作用,而且随着补片直径的增大,强度恢复率增高。当补片直径较小时,胶层先于母板发生破坏,此时的修理效果不明显;当补片直径增大到一定程度后,胶层承载能力较高,此时贴补修理对损伤件的拉伸强度有一定的提高作用。在试验基础上建立了有限元模型,能有效预测贴补修理件的破坏模式、拉伸强度,并可分析得到试验件的应力分布;改变有限元模型参数,研究最佳效果的补片尺寸与损伤孔径之间的关系。结果表明,当补片直径比损伤孔径大30 mm～40 mm时可获得较高的修理效率。为复合材料层合板设计贴补修理方案提供了参考。     

基于Zinoviev理论的含孔复合材料层合板三维有限元渐进失效分析

建立了含孔复合材料层合板的三维有限元模型,以二维Zinovie理论为基础,结合改进的三维Hashin准则,对二维Zinoviev理论进行了简化和拓展,提出了适用于三维模型的刚度退化方案,完成了对层合板的渐进失效分析。从纤维失效、基体失效、分层失效三个方面讨论了层合板在拉伸载荷作用下的失效过程,并预测了层合板的拉伸极限强度及破坏模式。数值模拟结果与试验基本吻合,验证了所提出退化模型的正确性。     

复合材料层合板贴补修理稳定性研究

论文针对胶接修理的贴补修理方式,基于MSC.PATRAN(有限元分析)软件建立层合板和双筋及格栅加筋板的有限元模型,对于常见的一边固定一边受平面压力的情况,进行屈曲分析,研究补片的尺寸和厚度对于修理稳定性的影响,然后找出屈曲特征值随补片参数变化的规律。研究结果表明,补片直径和修补后模型的屈曲特征值之间的变化关系并不是简单的线性关系;补片的直径和厚度取某特定区间的时候整个模型最稳定;对于加筋层合板来说,筋条可以分担部分载荷,所以加筋板筋条间的母板损伤修补效率比层合板有所提高。     

基于ANSYS的复合材料层合板的拉伸失效模拟

基于ANSYS的APDL语言开发复合材料层合板的拉伸失效模块,实现有限元分析的参数化建模和累积失效分析.采用Solid64宴体单元建立复合材料层合板的三维模型,依据改进的三维Haisin失效准则对结构单元进行失效判断,并对失效单元进行刚度退化.当失效单元贯穿所有单层时,复合材料层合板结构彻底失效.通过对铺层方式为[0/45/-45/90]s复合材料层合板结构拉伸模拟,探讨其拉伸破坏形式,得到层合结构的最终拉伸强度,并把其拉伸强度与文献实验结果进行对比,得到的结果与实验一致.该方法简便直观,便于工程运用.     

基于响应面法的CFRP层合板挖补修理结构的单目标优化

对于CFRP层合板挖补修理结构的优化问题,首先通过三维实体单元建立三维损伤累积模型并通过试验验证所建立的仿真模型的有效性,然后采用拉丁超立方试验设计方法和响应面法构建了拉伸强度代理模型,最后基于遗传算法和代理模型进行联合优化。研究结果表明:数值模型与仿真模型吻合度较好,误差在10%以内,表明所建立的有限元模型具有有效性。拉伸载荷下挖补结构的失效模式以胶层的剪切失效为主,胶层损伤起始于层合板和补片0°层对应的位置,然后向四周扩展,胶层失效后补片失去承载能力,母板继续承载并在最窄处断裂。最佳胶层厚度、挖补角度和旋转角度分别为0.1035 mm、2.5°和0°。与常规挖补结构相比,拉伸强度提高了12.57%。采用遗传算法对CFRP层合板挖补结构进行优化,对提高挖补结构的力学性能具有重要意义。     

斜面挖补修理复合材料的有限元分析

利用有限元软件ANSYS建立了复合材料层合板斜挖补修理的三维有限元模型,分析了不同挖补角对胶层剪应力和修补结构承载能力的影响。计算结果表明,在其他参数不变的前提下,合理选择挖补角可提高复合材料修理结构的承载能力,对更有效实施复合材料结构斜挖补修理方案设计具有一定的指导意义。     

复合材料加筋层合板阶梯式挖补修理的稳定性分析研究

基于有限元方法,研究了复合材料加筋层合板阶梯式挖补修理的稳定性问题。利用商用有限元分析软件MSC.Patran/Nastran,建立了复合材料层合板阶梯式挖补修理结构稳定性三维有限元分析模型。并通过所得屈曲特征值计算出修补结构临界失稳载荷,拟合出临界失稳载荷图,分析得出不同筋距、加筋数、挖补阶数和胶层厚度对复合材料层合板阶梯式挖补修理结构稳定性的影响规律。     

残余热应力对复合材料修理金属裂纹板影响分析

本文建立了复合材料胶接修理金属裂纹板的三板有限元模型;采用分析金属裂纹板裂纹尖端应力强度因子的方法,分析了残余热应力对复合材料修理金属裂纹板修理效果的影响。结果表明,残余热应力对单面修理结构的影响小于双面修理结构。残余热应力对单面修理结构的影响由于裂纹板宽度比值不同而不同。补片与母板的热膨胀系数相差越大,残余热应力对修补效果影响越大。     

某型中翼前梁修补结构的剩余强度研究

为确定某型复合材料中翼结构在胶接修补后的剩余强度,以层合板渐进损伤理论为基础,建立了复合材料胶接修补有限元模型,研究了搭接长度与补片厚度对中翼修补结构压缩强度的影响.对前梁胶接修补结构进行限制载荷试验,并比较中翼前梁裂纹周围结构在修补前后的应力应变,结果显示,选择阶梯型搭接修补方式,在补片铺层层数为22层,搭接长度为3...     

复合材料阶梯挖补修理中附加铺层的优化设计

基于有限元软件ANSYS,建立了三维复合材料层合板阶梯形挖补修理的有限元模型,分析了附加铺层大小、附加铺层厚度和附加铺层方向等修理参数对复合材料结构挖补修理强度的影响规律。这些影响规律对复合材料结构阶梯挖补修理方案设计具有指导意义。     

Study of tensile failure mechanisms in scarf repaired CFRP laminates

Bonded scarf repairs are used in composite structures when high strength recovery is desired or when there is a requirement for a smooth surface to satisfy aerodynamic requirements. Experimental and finite element study is carried out to understand the damage propagation and ultimate strength of scarf patch repaired CFRP laminates under uni-axial tensile load here. The ultimate strength and damage propagation in scarf repaired laminates has been investigated with respect to change in scarf angle and patch diameter. It is revealed from the results that damage is initiated in adhesive film at the bonded interface of 0° plies of parent laminate and patch in and then propagates in circumferential direction around scarf patch. It is found that some damage occurs in the parent laminate before the damage initiation in the adhesive film. After the adhesive film failure, the damage in parent laminate quickly propagates transversely to the free edge sides of the laminate and failure occurs. The results of this investigation provide further insight into the damage mechanisms in scarf repairs of composite structures under tensile load. This study may be helpful in improving the design and analysis techniques for scarf patch repair of composite structures.     

Research on the mechanical properties prediction of carbon/epoxy composite laminates with different void contents

The influence of the porosity on the static mechanical strength of the carbon fiber fabric reinforced epoxy composites laminates was investigated. The tensile, compressive, bending, and interlaminar strength test on the CFRP laminates with porosity of 0.33% and 1.50% were conducted and simulated by a finite element analysis model. The article proposes the failure criterion of the static mechanical strength of the fabric fiber reinforced composites based on the improved Hashin failure criterion that is suitable for the undirectional composite laminates. The basic composite strength parameters are used to evaluate the mechanical properties of CFRP laminates with different porosities. A finite element analysis model is established by using software ABAQUS™ combined with the sudden stiffness degradation model. The experiment results show that the tensile, compressive, bending, and interlaminar strength decrease with the increasing porosities. The tensile, compressive, bending, and interlaminar strength of the fabric carbon fiber reinforced epoxy composites laminates are simulated accurately by the finite element model. POLYM. COMPOS., 14–20, 2016. © 2014 Society of Plastics Engineers     

基于SPH方法的鸟撞复合材料层合板数值分析

采用光滑粒子流体动力学法(SPH)耦合有限元法对复合材料层合板受鸟撞击的过程进行了数值模拟。复合材料层合板采用渐进损伤模型,鸟体采用SPH粒子建立模型,利用ANSYS/LS-DYNA显示动力分析模块分析了复合材料层合板结构非线性接触。分析了鸟撞层合板过程中鸟体损伤及层合板单层纤维失效和基体失效情况,分析了鸟体的入射角方向及层合板采用不同铺层时对层合板吸能效果的影响。计算结果表明,合理设计层合板铺层可以提高层合板的吸能效果。     

基于加速试验方法的复合材料长期寿命预测

将跨尺度失效理论(Micro-Mechanics of Failure,简称"MMF")、加速试验方法(Accelerated Testing Methodology,简称"ATM")和渐进损伤分析(Progressive Damage Analysis,简称"PDA")三种方法相结合,提出了一种可以预测复合材料长期寿命和失效过程的分析方法。对MMF失效准则进行改进,区分了基体拉伸和压缩细观失效模式。建立了MMF/ATM/PDA方法有限元计算流程,并在ABAQUS中使用用户自定义材料(UMAT)实现。通过对不同温度下复合材料纵向和横向单向板的拉伸、压缩试验测得静载和疲劳寿命,得到复合材料MMF/ATM细观临界值。采用MMF/ATM/PDA方法对准各向同性开孔板压缩长期寿命进行了预测,并对破坏过程进行了模拟,分析了纤维和基体的失效过程。试验结果和预测结果吻合良好,验证了方法的合理性。     

Experimental investigation of repair of impact-damaged aircraft winglet under static bending moments

Bending behaviours of the repaired aircraft winglet were investigated in this paper. Impact damage was firstly inflicted at the center of three pristine winglets by using a drop-weight impact device. The damaged core was restored by filling in the same foam and the damaged skin was repaired by bonding to a three-dimensional scarf patch accompanied with an additional external layer (Doubler). Then, the ultimate load-bearing capacity and failure mechanism of the repaired winglets under static bending moments were studied and compared with the pristine ones. Furthermore, the influence of the stress state of the patch (tension or compression) was discussed by attaching the patch on the top and bottom respectively during testing. The experimental results show that the repaired winglets retain approximately 82% of the load capacity of pristine winglets. Damage occurs along the bolt holes on the composite skin of pristine winglets, while the repaired winglets fail due to the shear crack of the foam and debonding between the foam core and the composite skins. Finally, finite element method were used to explore the failure mechanism for repaired and pristine winglets by comparing the stress distributions. In addition, parametric studies were conducted.     

复合材料胶接修补结构疲劳性能的数值和试验研究

为研究室温下复合材料胶接修补结构的疲劳性能,以三维渐进损伤理论为基础,创建了复合材料胶接修补模型,利用材料损伤判断子程序实现对修补结构的静拉伸失效载荷及剩余强度的预测分析,并进行了相关试验的对比分析。采用5种不同尺寸的圆形补片来评价修补效果,并利用超景深仪对修补试件的疲劳损伤扩展模式进行微观测量。结果表明:静载拉伸中,尺寸为3.5r的修补结构承载能力最好;疲劳循环中,尺寸为2.5r的修补结构剩余强度提升效果最好;疲劳载荷下,当循环次数较低时,修补结构的主要损伤为基体开裂,而随着循环次数的增大,主要损伤为纤维断裂。     

Progressive failure analysis of carbon-fibre/epoxy composites laminates to study the effect of stitch densities under in-plane tensile loading

Through thickness reinforced stitched laminates with different stitch densities (0.11 and 0.028?mm^?2) were studied in order to analyse effects on laminate behaviour, under in-plane tensile loading based on continuum mechanics. Multi-layered stitched laminates with the stacking sequence [+45/90/?45/0₂/+45/90₂/?45/0]_s were modelled on a lamina-wise basis to analyse the macroscopic damage and local stress–strain constitutive behaviour. Interfaces between lamina and stitch yarns were assumed to be perfectly glued and were modelled by the contact capability. Discretisation procedures using the principle of virtual work were applied in addition to discretisation of the contact traction. Progressive failure analysis with Puck’s failure criteria was conducted to characterise the failure behaviour of the laminate. This analysis showed that reinforcement density is one of the key factors affecting strength, stiffness and crack propagation in composite laminates. By suppressing the damage initiation, densely stitched laminates showed 15.2% higher in-plane stiffness than moderately stitched laminates. The results obtained by the finite element technique are consistent with the experimental results.     

Nonlinear stress analysis of v-notched aluminum plates repaired with the wet patch technique

In this study, V-notched aluminum plates were repaired using the wet patch technique. Two different repair operations, single-side and double-side composite patches, were applied to the notched plates. Four layers of woven carbon fiber textile and with the same reinforcement angle were used as a composite patch. Previously, the epoxy was saturated onto the prepared carbon fiber textiles and glued to the plates, and then those plates were placed in a vacuum medium. The repaired plates were experimentally tested under tension load. A nonlinear stress analysis was carried out using the finite element methodology in addition to the experimental results. As major foci of the study, the effects of repair type and notch size on failure behavior and plastic stress distribution were examined. As a result, it was found that the notch depth affects the repair performance far more than the notch width. Debonding failure load between the patch and the plate in plates repaired with a single-side patch was found to be two times higher than the yield load. For the double-side patch, the yield load was close to the debonding load and this repair method increases the debonding load more than a single-side patch.     

三维中空复合材料天线罩的有限元结构分析

某类型天线罩外形尺寸较大,减重要求高,三维中空复合材料可满足该类型天线罩透波和结构高强的要求。针对上述使用要求和实际工况,选择三维中空织物复合材料为主体结构,玻璃纤维增强环氧树脂复合材料为补强面层,制备三维中空结构天线罩,采用有限元分析软件建立三维中空结构天线罩的有限元模型,对该类型天线罩在使用工况下的刚度、强度和稳定性进行分析,其计算结果满足刚度、强度和稳定性的要求,并通过压力试验验证中空夹层天线罩的变形量与有限元分析结果保持一致,从而指导该天线罩的铺层设计、优化及材料的选用。     

准静态压痕作用下复合材料层合板损伤阻抗与损伤容限实验研究

参照标准实验方法,开展了复合材料层合板对准静态压痕力的损伤阻抗和损伤容限实验研究,获取了接触力、压痕深度、压头位移等实验数据,并对含静压痕损伤层合板进行了剩余压缩强度试验。研究了压痕深度-接触力与剩余压缩强度-压痕深度的变化关系,并讨论了准静态压痕过程中的损伤演变过程和层合板的压缩破坏模式。结果表明:当层合板表面出现目视勉强可见压痕时,初始损伤发生,压痕深度随接触力增大而明显增大,同时剩余压缩强度随压痕深度增加而明显降低;当达到最大接触力时,层合板失去承载能力,背面可看到大量纤维断裂。对于含静压痕损伤的层合板,压缩破坏模式为贯穿损伤区域的层合板断裂。