T700/双马复合材料蜂窝夹芯结构损伤修复实验研究

本文制备了复合材料蜂窝夹芯结构件和三种孔径的半穿透损伤件,采用挖补工艺对损伤件进行了两种不同体系的修复,并测试了完好件、损伤件和修复件在常温和高温下的力学性能。两种体系修复后测试结果表明,高温修复(同质修复)和中温修复(异质修复)对损伤构件的性能恢复差异较小,但是由于同质修复工艺性差,固化温度高于177℃,容易造成其他构件的损伤,而异质修复工艺性较好、固化温度低,所以采用异质修复工艺能够实现对损伤构件的性能恢复,且适合于外场快速修复。     

复合材料蜂窝夹芯修补结构弯曲特性与温度相关性研究

建立复合材料蜂窝夹芯修补结构的渐进损伤分析模型,研究修补后蜂窝夹芯结构在弯曲载荷作用下的极限承载能力及损伤破坏模式,并进一步研究修补结构弯曲性能与温度的相关性。通过编写VUMAT子程序,设置补片以及蜂窝损伤板的失效准则及刚度退化模式,选用Cohesive单元以模拟修补结构中胶层的损伤状况,完成复合材料蜂窝夹芯修补结构的渐进损伤分析。研究结果表明:结构弯曲承载能力和胶层的粘结能力受温度影响较大,结构弯曲承载强度随温度的升高而减小,且脱粘失效会破坏结构的完整性;蜂窝夹芯结构面板基体损伤首先发生在90°方向铺层处,纤维基体剪切损伤首先发生在面板0°铺层处,并沿垂直于施载方向扩展至自由边界。     

三种复合材料夹芯结构在弯曲载荷下破坏行为研究

制备了帽型、泡型、工字型三种夹芯结构复合材料,研究三种夹芯结构在弯曲载荷下的响应行为,并利用有限元的方法研究夹芯结构在弯曲载荷下Von-Mises应力分布,利用Tsai-Hill屈服准则判定有限元模型的屈服情况,观察发生屈服的区域。结果表明,帽型夹芯结构具有最大的弯曲刚度与抗弯强度。三种夹芯结构发生破坏的区域不同,帽型夹芯结构破坏主要出现在压头区域、上面板的压头边缘区域、芯子压头正下方的拐角处;泡型夹芯结构破坏出现在芯子支撑区域;工字型夹芯结构破坏出现在下面板支撑区域。     

三维编织复合材料胶接接头力学性能试验研究

为了比较三维编织复合材料阶梯型和嵌套式搭接接头的胶接修复效果,对搭接长度相同的两种接头进行了拉伸和弯曲力学性能研究。通过实验得到两种接头及完好试件的载荷-位移曲线,对比了修补后的试件强度与完好试件的强度,得到了接头试件的修复效率,并分析和总结了拉伸与弯曲试验试件的损伤过程及损伤形貌。实验结果显示:阶梯型胶接接头拉伸载荷作用下的修复率为37.75%,弯曲载荷作用下的修复率为66.25%;嵌套式胶接接头拉伸载荷作用下的修复率为18.97%,弯曲载荷作用下的修复率为21.44%。对比试验结果得出阶梯型胶接接头力学性能较好。     

缝合增强泡沫夹芯结构复合材料力学性能研究

采用机械缝合设备连续制备了"X"型构型缝合增强泡沫夹芯结构预成型体,并采用真空导入模塑工艺(VIMP)整体成型了缝合增强泡沫夹芯结构复合材料。实验研究了面板纤维布层数、面板纤维布穿透缝合层数、缝合角度、缝合针距及纱线股数对缝合增强泡沫夹芯结构复合材料弯曲性能和平压性能的影响规律。实验结果表明:与未缝合结构相比,缝合结构在质量未明显增加的情况下,弯曲性能和压缩性能得到了显著提高,其弯曲刚度最大提高了4.66倍,破坏载荷最大提高了13.8倍;压缩强度和压缩模量最大分别提高了26.2倍和15.2倍。     

5228A树脂基无胶膜蜂窝夹芯结构粘结性能研究

本文采用高树脂含量的5228A预浸料作为胶接层制备出无胶膜蜂窝夹芯结构,通过超声无损检测、滚筒剥离断面形貌及滚筒剥离强度测试等分析了无胶膜蜂窝夹芯结构粘接性能随成型压力及胶接层树脂含量的变化规律。研究表明,5228A树脂体系具有可控的流变特性,可适用于无胶膜蜂窝夹芯结构的制备;5228A树脂基预浸料具有良好的工艺性能,所制备的无胶膜蜂窝夹芯结构内部质量良好,蒙皮及蜂窝的粘结性能优良;蜂窝夹芯结构滚筒剥离强度随成型压力提高而提高,蜂窝夹芯结构滚筒剥离强度随胶接层树脂含量的升高而提高。     

复合材料蜂窝夹芯结构紧固件连接拉脱失效行为研究

结合数值仿真计算和试验研究,得到了复合材料蜂窝夹芯结构紧固件连接在拉脱载荷作用下的破坏形式及承载能力,揭示了相应的失效机理。介绍了复合材料夹层结构的刚度理论,并建立了有限元模型,数值预测了结构的失效模式与极限载荷,通过与试验结果的对比,证明了本文数值模拟方法的有效性。试验与数值计算结果均表明复合材料蜂窝夹芯结构的失效区域主要集中于连接区域,故为提高结构承载能力,尝试将连接区域的蜂窝挖空后进行灌封,并对此局部灌封形式的复合材料蜂窝夹芯结构进行数值计算,结果表明,采用对复合材料蜂窝夹芯结构连接区域蜂窝灌封的方式,其性能要优于挖空蜂窝灌封的结构,承载能力有显著提高。     

碳纤维/PMI复合材料在湿热环境下的损伤扩展分析

运用三点弯曲试验研究和数值模拟的方法对新型材料碳纤维/PMI泡沫夹芯复合材料在高温湿热的弯曲性能以及损伤扩展进行了分析。研究结果表明：复合材料在高温湿热下的弯曲破坏载荷误差为9.13‰,预测了复合材料在湿热环境下的最大破坏载荷和破坏趋势。同时发现复合材料在湿热环境下的破坏机制：夹芯结构首先发生芯层压缩失效,然后才是剪切失效,结构最后的破坏是由剪切失效引起的,损伤扩展过程与试验保持一致。     

不同增强方式下泡沫夹芯复合材料三点弯曲性能研究

研究了缝合及加强筋增强方式下泡沫夹芯复合材料的三点弯曲性能.采用万能试验机分别进行了缝合与未缝合碳纤维、玻璃纤维、玻碳混杂纤维泡沫夹芯复合材料的三点弯曲实验,分别得出各自的载荷-挠度曲线,再引入加强筋的方式进一步研究缝合碳纤维泡沫夹芯复合材料的弯曲性能.结果表明,玻碳混杂纤维泡沫夹芯复合材料较玻璃纤维泡沫夹心复合材料性...     

损伤单曲层压壳胶接修复结构力学性能测试与分析

实际工程结构中存在大量的大曲率的曲面复合材料结构,因其特殊的外形和气动性要求,其复合材料补片胶接修理参数不能简单等同于平面复合材料结构。针对尺寸(长度L×曲率半径R×圆心角θ)为300mm×50mm×π/3rad、中心位置含20mm穿透型孔洞损伤的单曲层压壳结构,采用两种不同类型补片进行胶接修复试验,并对其力学性能进行测试与分析。结果表明:损伤孔的存在极大地降低了层压壳结构失效载荷、强度及模量,其损失率高达61%以上,而经胶接修复后其失效载荷、强度及模量可以得到明显改善,甚至恢复到完好程度;同时,采用楔形补片进行修复对改善修复结构中补片和损伤母板局部应力状态是十分有利的。     

Effect of patch hybridization on the tensile behavior of patch repaired glass/epoxy composite laminates using acoustic emission monitoring

This paper investigates the tensile response of damaged glass/epoxy composite laminates repaired using hybrid external patches. Hybrid external patches based on glass and Kevlar woven fabrics bonded on both faces of the damaged parent laminate were considered. Five different kinds of plain weave woven fabrics with a different ratio between glass and Kevlar fibers (100/0, 75/25, 50/50, 25/75 and 0/100) were used as the external patches. The intention of using these hybrid patches was to combine the excellent tensile stiffness of Kevlar fiber with the superior resin adhesion property of glass fiber. The virgin and damaged specimens were taken as the reference specimens for comparison of residual mechanical properties and damage mechanisms. Damage evolution and the failure progression of the repaired glass/epoxy specimens were monitored using real-time Acoustic Emission (AE) monitoring technique. The Acoustic Emission (AE) results depict different damage profiles and link them with mechanical test results to reveal the load to a change in failure mechanisms during mechanical loading concerning the influence of each hybrid patches on the performance of repaired glass/epoxy specimens. Good correlation of the acoustic emission results with the photographic images of fractured specimens was obtained. Specimens repaired with the equal volume fraction of glass and Kevlar fibers in the external patches presented the most favorable residual tensile response by effectively releasing the stress concentration in the damaged area.     

Nomex蜂窝夹层复合材料的成型工艺研究

针对Nomex蜂窝填充双马树脂基复合材料夹层结构在固化成型过程中易出现的蜂窝芯边缘塌陷问题进行研究。通过采用不同的成型工艺方法,以及对共固化工艺参数进行调整,研制出相应的双马来酰亚胺树脂基碳纤维/蜂窝夹层结构层板,并且对夹层结构的力学性能、内部质量以及平面拉伸性能进行测试。在此基础上分析了成型压力参数对夹层结构质量的影响。相关工艺试验表明蜂窝芯塌陷的原因主要是固化过程中蜂窝芯边缘的滑移引起的蜂窝局部失稳,通过采取分步成型、蜂窝先胶接后修型的方法能够有效地解决Nomex蜂窝夹层结构填充双马树脂基复合材料结构成型过程中的蜂窝芯塌陷问题。     

Post curing effect of poly epoxy on visco‐elastic and mechanical properties of different sandwich structures

Poly epoxy is a high performance room temperature cured epoxy system which provides excellent physical and mechanical properties. However, the effects of post curing of this resin system on the properties of different sandwich structures are unknown. This study aims to evaluate the effect of post curing (at 70°C for 2 hr) on the edgewise compressive and flexural strengths of a sandwich structure, constructed with Styrofoam and honeycomb as core materials and a plain weave carbon fabric as face sheet. Tested factors evaluated from edgewise compressive tests were as follows: peak load, compressive strength, and crash energy absorption of sandwich structures while core shear stress and bending stress of sandwich structures were determined and compared with flexural tests. It was observed that post curing affects significantly on the bending and compressive strengths of the sandwich structures. However, the data obtained for crash energy absorption suggested that the effect of post curing on the core shear strength and the total deflection was statistically insignificant. The matrix polymer was also inspected using dynamic‐mechanical thermal analysis to assess the changes in glass transition temperature and degree of conversion due to post cure. POLYM. COMPOS., 2013. © 2013 Society of Plastics Engineers     

夹层结构预埋玻璃纤维板拉脱强度研究

夹层结构在飞机复合材料结构中大量使用,其连接处力学性能影响飞机结构的完整性。采用玻璃纤维板G10-t0.25"预埋于碳纤维材料面板纸窝芯的夹层结构中,针对20 mm、30 mm、40 mm等不同预埋件直径,开展拉脱试验。试验结果表明:较典型金属后埋件结构,拉脱载荷有较大提高,随着预埋件直径的增加,拉脱载荷不断增加;当预埋件直径大于30 mm后,预埋件直径的增加对拉脱载荷的提高影响不大。     

固化压力对夹层结构力学性能的影响

通过测试不同固化压力下的Nomex蜂窝夹层结构的力学性能，讨论了固化压力对蜂窝夹层结构性能的影响。结果表明，在固化压力0．2－0．5MPa下，夹层结构的平拉强度、平压强度、剪切强度无明显变化，而侧压强度与弯曲刚度则随压力的增大而发生明显的变化。     

共固化成型无人机用复合材料/蜂窝夹层结构面板的性能

针对无人机结构工程设计和工艺方案需要,通过试验比较几种预浸料在共固化成型工艺状态下制备的蜂窝夹层结构面板与在相同固化工艺条件下制备的层压板的力学性能,得出可直接采用共固化工艺制造无人机飞机机体结构的结论.性能结果显示,由所选择的适用于共固化工艺的预浸料所制备的面板与层压板试样的力学性能基本是相当的,但面板的层间剪切强度却明显比层压板的低.     

Experimental and Numerical Investigations of Honeycomb Sandwich Composite Panels With Open-hole Damage and Scarf Repair Subjected to Compressive Loads

The mechanical analysis of adhesive repair of honeycomb sandwich composite plate is more complicated than that of the laminated plate repair, because not only the laminated damage, but also the honeycomb buckling should be considered. Experimental and numerical investigations are carried out to understand the damage propagation and ultimate strength of both open-hole and repair plates under compressive load. The results of numerical models are verified by experimental data and they are found in good agreement. It is revealed from the results that the strength of open-hole plate is about 34% of the strength of intact plate, while the strength of repair plate could resume to 76% of that of intact plate after the repair process. It is found that the structure strength increases as the scarf repair angle decreases due to the decline of shear stress in the adhesive. We also present the optimum ply sequence and the optimum number of overlays in considering the improvement of structure strength. This research will be useful in improving the design and analysis techniques for scarf patch repair of sandwich structures.     

Tailoring of bonded composite scarf joint interface for impact damage mitigation and stiffness compatibility

A novel composite scarf joint is successfully fabricated with thermoplastic core shell microparticles incorporated into the interlaminar interface regions with a dual objective of mitigating the impact damage and improving the stiffness compatibility of the joint. The impact analysis of the joints revealed that the incorporation of microparticles led to a significant improvement of the impact load bearing capacity of joint and reduced the extent of the damage area. It is also observed from flexural tests that the microparticles reduces the stiffness of the laminate proportional to the weight fraction of the particles and thereby help design a joint adherend with controlled matching stiffness. This engineered scarf joint adherend configuration has the potential to minimise stiffness mismatch between a fatigue worn-out damaged composite part and the new scarf repair patch laminate designed for it. This shall help ensuring an easy restoration of uniform load distribution in the newly bonded composite scarf joints and repairs.     

蜂窝夹层结构面板胶粘剂的研究

介绍了蜂窝夹层结构用面板胶SY -2 4B胶膜的力学性及工艺性能 ,并将其与双组分糊状胶SY -2 1作对比。实验结果表明 ,SY -2 4B胶膜具有更高的综合性能与耐疲劳性能 ,制成的蜂窝夹层结构具有更高的可靠性     

Mechanical properties of honeycomb prepared from aromatic polyimide film

Aromatic polyimides have many advantages such as low thermal expansion coefficient, good electrical insulation, and self-extinguishing properties. We tried to use polyimide film for honeycomb structure. Polymide honeycomb core and sandwich panel were prepared from polyimide film, i.e., UPILEX R, and adhesive by the expansion method. Mechanical properties, i.e., compressive, crushed, shear, and flexural strengths, were evaluated for this core and panel. Compressive and crushed properties increased largely with the density of the honeycomb, whereas shear and midspan flexural properties did not vary so much with the density, because these failures occured in the adhered interface. Strong adhesion is required for improving the latter properties. © 1993 John Wiley & Sons, Inc.