【摘 要】
:
The effects of solution temperature and holding time on the microstructure,mechanical properties and surface morphology of 2A12 aluminum alloy sheets were discussed in this paper.The universal tensile tester was used to test the tensile strength and yield
【机 构】
:
GRIMAT Engineering Institute Co.,LtD.,Beijing 101407,China;General Research Institute for Nonferrous
论文部分内容阅读
The effects of solution temperature and holding time on the microstructure,mechanical properties and surface morphology of 2A12 aluminum alloy sheets were discussed in this paper.The universal tensile tester was used to test the tensile strength and yield strength of alu-minum alloy sheets with different treatment systems.The surface morphology of the alloy sheets was characterized by a white light interference profile scanner,and the microstructure of the sheets was characterized by optical microscope(OM),scanning electron microscope(SEM)and electron backscattered diffraction(EBSD).The results showed that the mechanical properties of the sheets could not satisfy GBT228.1-2010 national standard when the holding time was 10 min and the holding temperature was 475℃.However,under the other heat treatment systems,the alloy could reach the GBT228.1-2010 national stan-dard.Moreover,with the extension of the holding time,the part of the matrix gradually diffused into the aluminum-clad layer.When the holding time was shorter than 25 min,the boundary between the matrix and the aluminum-clad layer was relatively obvious.And the diffusion gradually became obvious when the holding time was over 25 min.Thereby,the boundary became blurry.The further investigation suggested that the solution temperature of 495℃and the holding time of 35 min showed better mechanical properties and better surface morphology.
其他文献
The microstructure,room temperature and 650℃tensile properties of an(α+β)titanium alloy were investigated after aging over a temperature range of 600-750℃following solution treatment.The results exhibit that both aging temperature and aging time influ-enc
通过氯硅烷与中间体多面体笼型聚倍半硅氧烷(POSS)铵盐发生取代反应或含氢POSS的硅氢加成反应制备了多种MQ型功能化POSS,并对其结构进行了表征.初步将环氧基POSS(OG-POSS)经物理共混改性环氧树脂E51,将甲基丙烯酰氧丙基POSS(MA-POSS)经化学共聚改性聚甲基丙烯酸甲酯(PMMA),结果表明,OG-POSS有助于提高环氧树脂的介电性能,MA-POSS对PMMA力学性能的提升有很大的帮助.
In order to strengthen pure tin and improve its dry sliding resistance,Sn/SiC and Sn/Zn composites were fab-ricated via a powder metallurgy route.Microstructure,hardness and pin-on-disk wear resistance of pure tin and the fabricated composites were compar
Controlling the corrosion rate is critical for practical applications of Mg-based alloys.In this work,we constructed a protective coating of hybrid polycaprolactone(H-PCL)/indocyanine green(ICG)on AZ31 Mg alloy,whose degradation rate was controlled by 808
The tradeoff between the strength and the frac-ture elongation in the high-strength Cu-Ni-Si alloy became a hot research topic recently.Cu-Ni-Si-(Ti)alloys were fabricated in a vacuum induction melting furnace to study the effects of titanium on the micro
论述了航天器径向肋式、缠绕肋式、构架式和环形桁架式四种抛物面可展SAR天线结构的研究现状,分析了四种抛物面可展SAR天线结构的特点,分别对航天器翼式、桁架式和薄膜式三种平面可展SAR天线结构进行了综述,指出了航天器可展SAR天线结构轻质、大收纳比和高精度的发展趋势,提出了航天器可展SAR天线实现展开高精度需攻克的关键技术,旨在为航天器可展SAR天线结构的创新发展提供参考.
This research presents the influence of copper(Cu)concentration on the properties of copper zinc tin sulfide(CZTS)nanoparticles(NPs)synthesized by a col-loidal method,employing oleylamine as an organic sol-vent.From the structural analysis,a pure phase of
为了提高运载火箭上升段飞行中推力故障下轨迹重规划的计算效率,提出了一种基于智能决策的在线轨迹重规划方法,将原问题转化为最优救援轨道的在线智能决策和成熟的燃料最优轨迹规划问题进行求解.通过离线求解不同故障状态对应的轨迹重规划问题,建立“故障状态-救援轨道”样本集,基于径向基神经网络建立最优救援轨道的决策模型,并将决策模型装订箭上.在实际飞行中以当前故障状态作为输入,利用决策模型可在线快速决策出最优救援轨道根数,进而求解以救援轨道为目标轨道的燃料最优轨迹规划问题,从而完成推力故障下的在线轨迹重规划.数值仿真表
Inconel 600 alloy is widely utilized for high temperature environment application due to the corre-sponding good oxidation and corrosion resistance proper-ties.In order to estimate the high temperature oxidation resistance of Inconel 600 alloy at various
针对火星飞行器探测需求,提出了一种共轴双旋翼式火星飞行器,基于计算流体力学方法优选了桨叶翼型、平面形状和扭转角等结构参数,基于叶素动量理论建立了旋翼气动力学模型,利用数值模拟方法选择了旋翼转速、旋翼间距和桨叶安装角等飞行参数,设计了原理样机“火星飞鸟-I”的结构与控制系统.构建了火星大气环境模拟器和重力补偿与运动约束装置,开展了模拟火星环境下旋翼式飞行器地面飞行试验,验证了共轴双旋翼式火星飞行器的推进性能,展望了旋翼式火星飞行器技术的发展方向.研究成果对我国开展的火星探测工程具有重要借鉴价值.