Force-displacement characteristics of simply supported beam laminated with shape memory alloys

As a preliminary step in the nonlinear design of shape memory alloy（SMA） composite structures,the force-displacement characteristics of the SMA layer are studied.The bilinear hysteretic model is adopted to describe the constitutive relationship of SMA material.Under the assumption that there is no point of SMA layer finishing martensitic phase transformation during the loading and unloading process,the generalized restoring force generated by SMA layer is deduced for the case that the simply supported beam vibrates in its first mode.The generalized force is expressed as piecewise-nonlinear hysteretic function of the beam transverse displacement.Furthermore the energy dissipated by SMA layer during one period is obtained by integration,then its dependencies are discussed on the vibration amplitude and the SMA＇s strain（Ms-Strain） value at the beginning of martensitic phase transformation.It is shown that SMA＇s energy dissipating capacity is proportional to the stiffness difference of bilinear model and nonlinearly dependent on Ms-Strain.The increasing rate of the dissipating capacity gradually reduces with the amplitude increasing.The condition corresponding to the maximum dissipating capacity is deduced for given value of the vibration amplitude.The obtained results are helpful for designing beams laminated with shape memory alloys.

Oxidation Resistance of Fe-13Cr Alloy with Micro-Laminated (ZrO_2-Y_2O_3)/(Al_2O_3-Y_2O_3) Films

The micro-laminated （ZrO2-Y2O3）/（Al2O3-Y2O3） composite films were prepared on the surface of Fe-13Cr alloy by an electrochemical process and a sintering process alternately. High-resolution field emission scanning electron microscopy （FE-SEM） was used to characterize the laminated films, indicating that the micro-laminated （ZrO2-Y2O3）] （Al2O3-Y2O3） films have nano-structures. SEM, EDS and mass gain measurement were adopted to study the oxidation resistance of films on Fe-13Cr alloy. It is proved that such micro-laminated films are more effective than ZrO2-Y2O3 or Al2O3-Y2O3 films to resist the oxidation of the alloy, and the oxidation resistance is increased with increasing layers in micro-laminated films. These beneficial effects can be contributed to the mechanism, by which such micro-laminated （ZrOE- YEO3）/（Al2O3-Y2O3） composite film combines all the beneficial effects and overcomes all the disadvantages of both ZrOE- Y2O3 film and Al2O3-Y2O3 film during oxidation of alloy.

Internal friction peak and damping mechanism in high damping aluminium alloy laminate

A new aluminium alloy laminate characterized by high damping, corrosion resistance and weldablity was developed. The laminate designed for required aforesaid functions was actually a composite material, which was made of two anti corrosive layers (Al), two damping layers (ZnAl alloy) and one reinforcing layer (AlMg alloy) by hot rolling. The damping characteristics were studied and it was found that there was an internal friction peak at about 50 ℃ on internal fraction vs temperature curve for the laminate. For this reason, the activation energy of the peak was calculated. The origin and damping mechanism for this peak was researched by means of SEM, TEM, X ray and DSC. It is considered that the peak is caused by the interaction between dislocations and point defects in damping layers (AlZn alloy). i.e. by the movement of dislocations dragging point defects under the action of thermal activation. The laminate is remained at room temperature for a long time, it will weaken or even disappear with the restoration of the crystal microstructure and the reduction of the dislocation density in the ZnAl alloy layers. The mechanism of the peak is in conformity with that of the dislocation induced damping. [

Aero-Elastic Flutter Characteristics of Laminated Composite Panel Embedded with Shape Memory Alloy Wires

The effects of shape memory alloy( SMA) wires on the natural frequency,flutter boundary and amplitude of limit cycle oscillation( LCO) of a laminated composite panel are investigated. The classical plate theory as well as von-Karman strain-displacement relation are used to formulate the nonlinear dynamic model of the smart laminated panel. The aerodynamic loadings are simulated by the third order piston theory. The thermomechanical behavior of SMA wires is estimated according to one-dimensional Brinson SMA model. The effects of SMA wires temperature,pre-strain,volume fraction and orientation on flutter boundary and amplitude of LCO of the panel are analyzed in detail.

Bonding interface zone of Mg-Gd-Y/Mg-Zn-Gd laminated composite fabricated by equal channel angular extrusion

In order to improve the mechanical properties and corrosion resistance of Mg alloys,the equal channel angular extrusion (ECAE)was employed to fabricate the Mg-5Gd-5Y/Mg-2Zn-1Gd(GW55/ZG21)laminated composites.After fabrication and annealing treatment,the microstructural evolution,phase constitution,microhardness,and bonding strength were investigated on the bonding interface zone of GW55/ZG21 laminated composites.The bonding interface zone of GW55/ZG21 laminated composites comprises a lot of Mg3(Y,Gd)2Zn3 particles along the bonding interface,some rod Mg24(Y,Gd)5 phases on GW55 side,and a precipitation free zone(PFZ)on ZG21 side.After annealing treatment,Mg3(Y,Gd)2Zn3 particles along the bonding interface increase, rod Mg24(Y,Gd)5 phases on GW55 side decrease,and PFZ is broadened.Meanwhile,the hardness on the bonding interface zone decreases and the bonding strength increases from 126 MPa to 162 MPa.

ANALYSIS AND MEASUREMENT ONRESIDUAL STRESS OF ARAMIDALUMINIUMLAMINATE

Residual stresses of the ordinarily cured and pre-stressed unidirectionallaminate are analyzed quantitatively. In order to examine the analyzing formulations,strain gages were embedded in the uni-directional aramid aluminium laminates (ordi-narily cured and pre-stressed) to determine the residual stresses in the aluminiumlayers. The calculated residual stresses are in good agreement with the experimental val-ues in the longitudinal direction. Therefore, the work in this paper can be used to calcu-late, determine and design the longitudinal residual stresses according to the manufac-ture and application demands.

Electron Beam-Physical Vapor Deposited TiAl-based Laminated Composite Sheet with Nb Layer Toughening

The TiAl-based laminated composite sheet of 150 mm × 100 mm × 0.2 mm, with 24 TiAl layers and 23 Nb layers laid alternately one on another, was successfully fabricated using the electron beam-physical vapor deposition （EB-PVD） method. The microstructure and properties of the sheet were investigated on an atomic force microscope （AFM）, a scanning electron microscope （SEM） and a tensile testing machine. The results indicate that the evenly distributed Nb layers are well joined with the TiAl layers, and the interfaces between layers are transparent, and every interlayer spacing is of about 8μm. The fractures appear to be a mixture of intergranular fractures and somewhat ductile quasi-cleavage ones. Despite its slight influence on ultimate tensile strength, the inserts of Nb layers efficiently increase the room temperature ductility of TiAl-based alloys due to the crack deflection effect.

Mechanical Properties of Laminated Aluminum-Based Plates with Gradient Interface

Two laminated composites, 2024/3003 and 7075/6009 aluminum alloys were prepared by double-stream-pouring continuous casting (DSPCC) followed by plastic deformation and heat treatment. The interface characteristics between the external and internal layers of the composites in the as-cast and plastic deformation conditions were analyzed. The results show that the macrostructure difference between the external and internal layers of both composite ingots in the as-cast condition can be clearly clarified but the gradient interfaces are not distinct. However, the macro-scale gradient layers can be demonstrated from the hardness distribution in the cross sections of the composite ingots. After plastic deformation, the gradient characteristic of the interface in the laminated composites maintains except for the decrease in the interface thickness. After plastic deformation and T6 heat treatment, the ultimate strength, yield strength and elongation of 2024/3003 composite plate are 2.35, 3.10 and 0.9 times of that of 3003 aluminum alloy, respectively. The ultimate strength and yield strength of 7075/6009 composite plate increase 47 % and 82 % of that of 6009 aluminum alloy, respectively and the elongation of the composite is still as high as 15.3 %.

Fabrication, microstructure and properties of electron beam-physical vapor deposited TiAl sheet and TiAl/Nb laminated composites

The TiAl-based alloys sheet with 150 mm×100 mm×0.4 mm and the TiAl/Nb laminated composites with 150 mm×100 mm×0.2 mm were fabricated by using electron beam-physical vapor deposition(EB-PVD) method, respectively. The microstructure and properties of the sheet were investigated by AFM, SEM and EDS. The results show that the TiAl based alloys sheet has a good surface quality, and its microstructure is columnar crystal. The component of the alloys indicates a regular and periodical gradient change which leads to the spontaneous delamination along the normal direction of substrate. In the TiAl/Nb laminated composites alternating overlaid by TiAl of 24 layers and Nb of 23 layers, the interface of each layer evenly distributed throughout the cross-section is transparent, and the interlayer spacing is about 8μm. The component of TiAl layers also changes regularly along the normal direction of substrate, but no delamination phenomenon is found. The TiAl/Nb laminated composites have better ductility than the TiAl-based alloys sheet.

钛合金扩散连接技术及其层合结构疲劳裂纹扩展研究进展

本文主要对钛合金的扩散连接及层合结构疲劳裂纹扩展行为的研究进展进行了综述,总结了扩散连接钛合金界面的微观组织演变和疲劳裂纹扩展特性。首先概述了超塑成形/扩散连接技术的应用背景和优势,以及提高钛合金扩散连接界面质量的辅助技术(如添加中间层、热氢处理、脉冲电流加热和表面改性)。从钛合金扩散连接和钛合金与其他合金扩散连接两方面综述了界面组织和力学性能,指出组织演变严重依赖界面处合金元素种类和元素相互扩散能力。扩散连接技术可用来制备同种和异种合金的层合结构,且可灵活控制界面焊合与未焊合区域的形状与分布。最后,简述了同种或异种钛合金扩散连接层合结构可降低疲劳裂纹扩展速率,从而优化钛合金构件的疲劳损伤容限性能。

热处理对1060/7N01/1060轧制复合板显微组织及力学性能的影响

利用475℃单道次热轧的方式制备界面结合良好的1060/7N01/1060层状复合板。通过扫描电子显微镜、透射电子显微镜及电子背散射衍射结合硬度和拉伸实验研究层厚比对热轧复合板显微组织和力学性能的影响。此外,对比研究冷轧前热处理(固溶处理及峰值时效)对冷轧复合板显微组织和力学性能的影响。结果表明,层厚比对热轧复合板各层显微组织特征影响不大,其力学性能与混合法则理论预测结果一致。相比而言,额外的热处理对冷轧板纯铝层的晶粒尺寸无明显影响,却有助于细化7N01层的晶粒尺寸及弥散、细小析出物的形成,使其具有更显著的细晶强化、析出强化及位错强化效应。

热压工艺参数对TA2/CF/PEEK层板弯曲性能的影响

以TA2箔、碳纤维和PEEK材料体系为基础,探索钛箔-碳纤维布-PEEK薄片直接复合的热压法制备工艺。在对初始材料进行超声清洗除油、砂纸打磨等预处理后,手工铺层并放入自行设计的热压模具,基于不同温度(370和390℃)、压力(0.8、1.6和2.5 MPa)与保压时间(20和40 min)的热压法制备了TA2/CF/PEEK层板。利用三点弯曲实验方法探究了热压工艺参数对层板弯曲性能的影响。结果表明,较佳的热压工艺为:成形温度390℃、热压压力1.6 MPa、保压时间40 min且每侧铺设两片树脂薄膜。在此工艺下制备的TA2/CF/PEEK层板弯曲强度为681.68 MPa,弯曲模量为69.5 GPa。

Progress on the glassy-crystal laminates:From design,microstructure to deformation and future solutions

The development of new design strategies to create innovative structural materials,refine existing ones,and achieves compatible combinations of strength and plasticity remains a worldwide goal.Promising alloys,such as shape memory alloys(SMAs),bulk metallic glasses(BMGs),high entropy alloys(HEAs),and heterogeneous pure metals such as Cu,have excellent mechanical responses,but they still fall short of meeting all the requirements of structural materials due to specific flaws,such as lack of tensile de-formation for BMGs and low yielding strength for HEAs.To address these shortcomings,proposals such as integrating glassy matrices and crystallized alloys,such as HEAs/SMAs,have been suggested.However,these solutions have unresolved issues,such as the challenging control of B2 phase formation in BMG composites.Recently,glass-crystal(A/C)laminated alloys with alternating layers have been reported to exhibit improved mechanical properties and activated work-hardening behaviors,but they still face press-ing issues such as bonding interfaces and unknown deformation mechanisms.This review focuses on design routes such as the selection of alloy components and processing techniques,exploration of micro-structural evolution and deformation modes with an increase in strain,and future solutions to address pressing and unsolved issues.These prominent advantages include diversified deformation mechanisms,such as deformation twinning,martensitic phase transformation,and precipitation hardening,as well as tuned interactive reactions of shear bands(SBs)near the A/C interfaces.Thus,this review provides a promising pathway to design and develop structural materials in the materials field community.

卫星用CFRP/铝合金叠层套钻孔工艺

针对卫星框架产品中CFRP/铝合金叠层结构制孔精度差、缺陷多的问题,优化改进此类叠层结构制孔工艺。通过总结CFRP/金属叠层结构的特点并进行分类,分析传统制孔、螺旋铣孔和套钻制孔的钻削机理,开展对比试验,通过对孔径尺寸、孔壁质量、贴片脱落数的综合评定,确定最优加工工艺方案;通过单因素对比试验研究了加工参数对叠层结构孔加工质量和加工精度的影响规律,并依此优化工艺参数。试验结果显示:采用套钻制孔,可明显提高制孔质量与制孔精度。确定最优加工参数组合为主轴转速3000~4000r/min,进给速度30~40mm/min,该工况下孔径尺寸符合公差要求且加工缺陷少,孔壁表观质量好。

SUS441不锈钢/Al金属间化合物微叠层复合板的界面结构与力学性能

采用“表面预处理—交替层叠—热轧复合—热处理”的工艺流程制备了SUS441不锈钢/Al金属间化合物微叠层复合板。利用光学显微镜、X射线衍射仪、扫描电子显微镜等检测与表征方法研究了热处理温度对复合板界面形貌、微观组织、物相组成、维氏硬度、拉伸性能的影响。结果表明:复合板界面结合良好;热处理后,固–液反应界面氧化严重,易导致界面分层而开裂;固–固、固–半固、固–液热处理后,金属间化合物层由均匀层和两相层组成,均匀层的物相组成为Fe_(2)A_(15),两相层的物相组成为Fe_(4)Al_(13)和Al_(13)Cr_(2),且两相层具有韧性特征,固–半固反应所得到的复合板的综合力学性能最佳。

基于二次摄动法的SMA层合梁非线性自由振动分析

为对SMA(形状记忆合金)层合梁的非线性自由振动进行分析,使用Brison一维本构模型描述SMA的力学特性,基于不同剪切函数和Von Karman大变形理论,建立梁质点位移与应变之间的关系,使用Hamilton变分原理,获得在弹性地基上两端简支SMA层合梁的动力学方程并进行无量纲处理。使用二次摄动法获得SMA层合梁的非线性自由振动方程。研究不同SMA体积分数、预应变、SMA铺设角度、温度变化对非线性振动的影响。

车用碳纤维/铝合金层板弹性模具增塑成形极限及机理研究

为解决车用碳纤维/铝合金层板传统成形工艺存在的异质材料变形协调性差、塑性成形极限低的问题,提出了一种碳纤维金属层板弹性模具增塑成形方法,并结合理论分析、有限元仿真、实验等方法,研究了弹性模具增塑成形过程中碳纤维金属层板的变形行为和成形极限。实验结果表明,所提方法能够显著提升碳纤维金属层板的成形性能,且随着弹性模具硬度的增加,层板的成形极限位移和承载极限均有所提高,当弹性模具硬度达到HS90A时与传统无弹性模具成形相比,层板的成形极限位移可提高30.6%,承载极限可提高21.8%。

复钛叠层结构大孔径制孔热损伤研究

复钛叠层结构制孔所产生的切削热会对复材造成损伤,出现的变色和熔融等热损伤现象在一定程度上影响孔的质量。论文针对复钛叠层结构制孔时的复材孔周变色现象,分析热损伤机理并采用拉伸试验进行热损伤评估,结果表明孔周变色现象对结构强度的影响在可接受范围内。为防止复现该种热损伤现象,优化既定制孔方案,所制连接孔合格率高达100%。除此之外,引进螺旋铣实现低热损伤大孔径制孔,制孔效率和质量大幅提高。

Texture evaluation in AZ31/AZ31 multilayer and AZ31/AA5068 laminar composite during accumulative roll bonding

This article presents the texture development of magnesium AZ31 alloy in the accumulative roll bonded(ARB) AZ31/AZ31 multilayer and AZ31/AA5086 laminate composite.The comparative study demonstrates that the texture evolution in AZ31 in a multilayer system is strongly influenced by the interfaces.A typical basal texture of AZ31 has been observed in AZ31/AZ31 multilayer with texture intensity increased with the rolling deformation.Presence of AZ31/AA5086 interface in the laminate composite leads to a tilted basal texture along the rolling direction(RD) in AZ31 alloy.The texture intensity of composite increased initially with rolling reduction and weakened at the higher rolling strain.Weakening of texture in AZ31 during the laminate processing at higher strain has been attributed to the development of wavy interfaces in AZ31/AA5086 laminate.

CFRP/钛合金叠层结构变参数螺旋铣孔界面加工特性研究

螺旋铣孔是CFRP/钛合金叠层结构件的常用制孔技术,然而两材料切削性能的差异使单一参数下的内孔加工质量难以保证。围绕CFRP/钛合金叠层结构一体化精密制孔的现实需求,设计了变参数螺旋铣孔方案;通过对界面过渡轴向力、界面加工质量和界面处孔径的分析,研究了叠层制孔顺序和变参数位置对界面加工特征的影响规律。结果表明:叠层制孔顺序对界面过渡轴向力、界面加工质量和界面处内孔精度都有显著的影响,而变参数位置的影响主要体现在界面加工质量方面。C/Ti-C方案能获得最佳的界面加工质量,其界面平整度因子仅为Ti/C-Ti的8%;Ti/C制孔顺序能获得较小的两材料界面孔径差值,最小为29μm。基于对界面加工质量和尺寸精度的综合考虑,C/Ti-C变参数方案能够实现最佳的界面加工效果。