Investigation on the plastic work-heat conversion coefficient of 7075-T651 aluminum alloy during an impact process based on infrared temperature measurement technology

The plastic work-heat conversion coefficient is one key parameter for studying the work-heat conversion under dynamic deformation of materials. To explore this coefficient of 7075-T651 aluminum alloy under dynamic compression, dynamic compression experiments using the Hopkinson bar under four groups of strain rates were conducted, and the temperature signals were measured by constructing a transient infrared temperature measurement system. According to stress versus strain data as well as the corresponding temperature data obtained through the experiments, the influences of the strain and the strain rate on the coefficient of plastic work converted to heat were analyzed.The experimental results show that the coefficient of plastic work converted to heat of 7075-T651 aluminum alloy is not a constant at the range of 0.85–1 and is closely related to the strain and the strain rate. The change of internal structure of material under high strain rate reduces its energy storage capacity, and makes almost all plastic work convert into heat.

Residual stress in quenched 7075 aluminum alloy thick plates

The influence of quenching water temperature, pre stretching amount and aging temperature and times on residual stress in 7075 aluminum thick plate was studied by the measurement of residual stress using drilling hole method. The results indicate that residual stress decreases by 30% with increasing quenching water temperature from 40 ℃ to 80 ℃, 20% with increasing aging temperature from 100 ℃ to 180 ℃,and 20% with increasing aging times from 5 h to 25 h. Also, residual stress decreases to zero with increasing pre stretching amount to approximately 2%. Hence, residual stress in 7075 aluminum thick plate is reduced by the control of quenching water temperature at 80 ℃ and with pre stretching amount of about 2%. An optimal aging temperature and time should be systemically investigated to obtain combination of high mechanical performances and lower residual stress for manufacturing of 7075 aluminum alloy thick plates.

Residual Stress Relaxation of Thin‑walled Long Stringer Made of Aluminum Alloy 7050‑T7451 under Transportation Vibration

Thin-walled long stringer made of aluminum alloy 7050-T7451 is prone to deformation during transportation,so a research of residual stress relaxation was launched in this paper.The transport resonance stress of long stringer was analyzed based on the power spectral density of road transport acceleration.The residual stress relaxation experiment of aluminum alloy 7050-T7451 under different equivalent stress levels was designed and carried out.According to the amount of residual stress relaxation in the experiment,an analytical model was established with the equivalent stress level coefficient.The deflection range of long stringer was evaluated under different damping ratios.The results show that when the equivalent stress exceeds 0.8σ0.2,the residual stress relaxation of the thin-walled samples occurs.The residual stress relaxation increases linearly with the equivalent stress,which is logarithmically related to the loading cycle.The deformation caused by residual stress relaxation of the long stringer is proportional to the square of the length and the bending moment caused by stress rebalance,and inversely proportional to the moment of inertia of the structure.As the damping ratio decreases from 0.03 to 0.01,the total deflection of the long stringer increases from 0 to above 1.55 mm.

7075-T6铝合金板材焊接工艺及残余应力试验研究

对7075-T6铝合金板进行MIG焊接工艺试验研究,选择ER5356铝合金焊丝进行低强匹配,发现焊接电流在190 A^210 A时软化区域约4 mm,焊接电流220 A^230 A时软化区域增大至5 mm。为保证焊接接头质量及生产效率,同时结合工程制造实际情况建议焊接电流选择210 A。进一步对焊接电流210 A的试板进行残余应力试验检测,焊缝中心残余应力最大达到378. 1 N/mm2,但高应力区仅存在距中心10 mm区域内,其应力梯度较大,最大值小于7075-T6铝合金板材的屈服强度。采用ANSYS软件进行了焊接残余应力计算,整体应力分布趋势与实测值基本吻合,但计算结果略大,理论计算结果更趋于保守,可供以后的铝合金焊接提供参考。

异速比对龙形轧制7075铝厚板变形的影响研究

针对异速比对龙形轧制7075铝合金50 mm厚板变形程度的影响进行了实验研究,在单道次压下10 mm、轧辊错位量4 mm的条件下,采用异速比1.00、1.06、1.10和1.16进行了龙形轧制实验,分析了异速比对轧板厚度、板厚方向分层晶粒组织和显微硬度的影响。结果表明,异速比对轧板厚度没有明显影响,不同异速比对轧板晶粒组织的影响也不明显;异速比为1.06和1.10时,轧板心部显微硬度高于异速比1.00的轧板,体现了异速比强化心部变形的作用;当异速比达到1.16时,轧板两个边面附近显微硬度明显降低,具体原因还有待进一步实验研究探索。

工艺参数对7075铝合金变截面板时效成形回弹的影响

以典型航空用7075高强铝合金变截面板材为研究对象,通过自行设计的时效成形工装进行时效成形实验,得到工艺参数如时效时间、变截面板宽度、变截面板厚度比对其时效成形后回弹的影响规律。结果表明:在其他工艺参数保持不变的情况下,回弹率随着时效时间、变截面板宽度和变截面厚度比的增加而减小。通过单轴蠕变拉伸实验推导得出本构方程,基于ABAQUS平台建立本实验的有限元模型,对时效成形过程中的等效应力和蠕变应变进行分析,并通过实验验证了建立的有限元模型的可靠性。

均匀化工艺对大尺寸7075铝合金组织和性能的影响

本工作主要研究了不同均匀化工艺对大规格7075铝合金铸锭组织的影响以及对轧制薄板性能的影响。研究结果显示:合金的铸态组织主要由Al基体+Mg(Zn,Cu)2相非平衡共晶相组成。465℃/24 h均热后,合金中枝晶组织部分消失,低熔点相溶解不充分。465℃/24 h+478℃/8 h均热后,共晶组织基本消除,残留相主要是难溶解的含Fe相,均匀化效果优异。通过将不同均热后铸锭轧制成薄板,二级均热后的薄板T6态力学最优,抗拉强度为533.5 MPa,屈服强度为455 MPa,延伸率为16.5%。

预拉伸对7075铝合金中厚板几何精度和力学性能的影响

以厚度为6 mm的7075铝合金中厚板为对象,开展预拉伸对板材几何精度和力学性能的影响研究.试验表明,当预拉伸量相同时,板材宽厚比越大,回弹后的纵向永久变形率越小;预拉伸对板材的宽向尺寸影响很小,其预拉伸过程近似于纵向延伸、厚向减薄的平面应变状态;通过数据拟合,建立了3种宽厚比中厚板的预拉伸量与其纵向和厚向回弹后永久变形率之间的关系方程;随着纵向永久变形率的增加,预拉伸板时效后的屈服强度和抗拉强度均呈先增加后减少的趋势;在纵向永久变形率为2.0%~2.5%时,预拉伸板的强度性能达到最大值.

7075铝合金轧板固溶工艺实验

为优化7075铝合金轧板T6工艺,进行了固溶工艺实验研究,实验参数涉及固溶温度和固溶时间。结合轧板DSC曲线和实验获得的布式硬度数据,选取了4个工艺进行金相组织、拉伸性能、断口形貌的比较与分析。结果表明,固溶温度500℃、固溶1 h、时效温度120℃、时效保温24 h的T6工艺可以获得7075铝合金轧板最优性能,其布式硬度为179 HB,非比例屈服强度493.1 MPa,抗拉强度573.1 MPa,延伸率11.7%。分析认为,轧制中间退火降低了轧板变形储能、提高了再结晶温度,大变形量轧制和中间退火造成轧板中非平衡凝固共晶组织破碎、细化和分离,导致熔化温度升高并且难以出现过烧现象,因此对7075铝合金轧板的T6特别是固溶工艺设置要结合轧板变形情况、轧制过程和轧板DSC曲线。

7075铝合金板材蠕变时效成形试验及数值模拟

采用试验和有限元方法分析了7075铝合金板材蠕变性能,比较了7075铝合金加筋壁板与无加筋壁板在蠕变时效过程中对材料蠕变性能的影响。结果表明,加筋壁板的蠕变性能明显提高。在蠕变成形过程中加筋壁板中心位置的最大应力由无加筋壁板的329 MPa提高到367 MPa,最大应变从0.022提高到0.025。加筋壁板中心位置的位移由2 mm变成为1.7 mm,回弹了0.3 mm,小于无加筋壁板的0.5 mm。

Effect of Temperature on Material Transfer Behavior at Different Stages of Friction Stir Welded 7075-T6 Aluminum Alloy

In this work, the morphologies of weld of 7075-T6 aluminum alloy via friction stir welding （FSW） were analyzed by optical microscopy, the temperature field was attained by numerical simulation, and the effect of temperature on material transfer behavior in the thermal-mechanical affected zone （TMAZ） at different stages was mainly investigated. The FSW process consists of three stages. It is very interesting to find that the maximum transfer displacement of material appears at the final stage of welding process, then at the stable stage and at the initial stage, which results from the difference of peak temperatures at different stages. At any stage, the material in TMAZ near the surface of weld transfers downwards, the material in the middle of weld moves upwards and the material near the bottom of weld hardly moves. In any cross section of weld, the largest transfer displacement of material appears in the middle of weld. The increase of rotational velocity and the decrease of welding speed are both beneficial to the transfer displacement of material in the middle of weld.

Effects of dry/wet ratio and pre-immersion on stress corrosion cracking of 7050-T7451 aluminum alloy under wet-dry cyclic conditions

The stress corrosion cracking(SCC) behavior and mechanism of 7050-T7451 aluminum alloy under wet-dry cyclic conditions were investigated. Slow strain rate tests(SSRTs) and electrochemical tests were used to study the effects of dry/wet ratio(DWR) and pre-immersion on SCC.Fracture and side surface characterizations were observed by scanning electron microscopy(SEM).The results demonstrate that SCC susceptibility decreases with an increase of the DWR. With an increase of the pre-immersion time, both continuous pre-immersion(CP) and wet-dry cyclic preimmersion(WDP) samples are more sensitive to SCC, and the cracking mode in the SCC fracture region is intergranular. Furthermore, the effect of WDP on SCC is greater than that of CP when the total time immersed in solution before an SSRT is the same with each other. In fact, each single wetdry cycle can be divided into three processes with respect to the change of solution on samples’ surface. Volatilization of water on the surface results in an increase in solute concentration, thus accelerating corrosion.

Study on the reaming process of aluminum alloy 7050-T7451 under different cooling conditions

Aluminum alloy 7050 is widely used in the aeronautical industries.However,owing to their highly ductile property,chips created during high-speed machining cannot be naturally broken,and long continuous chips are unavoidably formed,impacting the machining stability and quality of the parts.Because a smaller cutting allowance is required compared with conventional machining operations,the behavior of the chips during reaming operation may be more complex and different from those determined in previous investigations.Therefore,studying the characteristics of chip formation and hole quality during the reaming process is essential to improve the machinability of aluminum alloy 7050.In this study,three different cooling conditions were applied to reaming aluminum alloy 7050-T7451 with polycrystalline diamond(PCD)reamers.The finite element models(FEMs)were established to simulate the chip formation.The macro-and micro-morphologies of chips under the three cooling conditions were compared to analyze the chip behaviors.The diameter,surface roughness,and micro-morphologies of the reamed holes were also analyzed to evaluate the hole quality.The results showed that the chip morphology was strongly influenced by the cutting parameters and cooling strategies.It was found that the desired chip morphologies satisfactory geometrical accuracy and surface quality during the reaming of aluminum alloy 7050-T7451 could be achieved using internal cooling at a spindle speed of 8000 r/min and a feed rate of 0.0l mm/z.This study also demonstrates the feasibility of an internal cooling strategy for breaking chips when reaming aluminum alloy 7050-T7451,which opens new possibilities for improving the chip-snarling that occurs during hole machining.

单级时效工艺对7075铝合金包覆薄板力学性能的影响

为了解决大飞机蒙皮用7075铝合金薄板T6态性能要求。本工作采用室温拉伸试验、金相及扫描电镜研究了工业化生产的7075薄板前铸锭的均热效果,单级时效工艺对7075薄板的力学性能的影响规律。结果表明合金铸锭经均匀化处理后,主要残留含Fe相,共晶组织基本消除。铸锭经热轧、冷轧至2.5 mm,固溶后薄板的晶粒呈拉长状态,再结晶程度达到80%。单级时效结果表明:随着时效时间的延长,7075薄板L和LT向的抗拉强度、屈服强度不断增加,延伸率有所降低,选择121℃/36 h作为7075薄板T6态时效制度,此时L和LT向抗拉强度分别为531 MPa和520.5 MPa,屈服强度分别为448.5 MPa和440.5 MPa,延伸率分别为15.5%和14.8%。

面向7075-T7451铝合金厚板加工变形控制的变向迭代优化方法

依据毛坯分解为去除材料和成形零件两部分,将初始残余应力分为释放应力和有效应力,利用静力平衡条件和弯曲变形理论建立加工变形分析模型及其有限元求解方法。通过现场加工零件后,经与实验测量结果进行对比分析可知,无论是幅值水平还是变形曲线,加工变形的仿真值均有很好的吻合性,两者仅存在10%左右的幅值误差。利用有限元方法求出相邻2个加工位置的零件变形,依据"变形方向相同则步长相等、变形方向相反则步长递减"原则确定下一个加工位置,提出加工位置的变向迭代优化方法。经与企业实际使用的中间位置法相比,变向迭代优化方法能够使得加工变形减小99.79%。

中厚板淬火变形的试验研究

7075铝合金中厚板固溶处理过程中采用不同的支撑方式,利用单面喷淋淬火引起板面整体变形。运用X射线衍射仪与三坐标仪分别测试并讨论各淬火板的表面残余应力分布及变形规律。结果表明:板的淬火应力分布是其外在整体变形的内在表现形式,且板的支撑方式直接影响其后续淬火变形趋势。

7075铝厚板内淬火残余应力的形成机理分析与控制策略

残余应力在加工过程中的释放与再分布是引起飞机结构件加工变形的重要因素。而淬火过程中,铝合金厚板表层和芯层存在较大的温度梯度,由其造成的不均匀塑性变形是形成淬火残余应力的关键所在。为此建立了淬火工艺的有限元分析模型,通过仿真值与实验结果的比较分析表明,无论是残余应力幅值还是分布趋势,仿真值均有很高的吻合度。在此基础上,利用有限元方法分析了淬火残余应力的形成机理,认为芯层在终滑点处塑性变形结束且最终残余应力已经确定,后续降温过程不再影响最终残余应力水平。最后以芯层终滑点为依据提出了热换系数的残余应力控性控形方法。由于控形区对最终残余应力的影响很大,而控性区段基本不影响最终残余应力,因此可以通过合理调整控形区和控性区邻域内对流热换系数的方法,实现冷却速度的增大和残余应力的减小。

面向7075铝厚板加工变形的初始残余应力释放与再分布模型

通过材料的切削去除转化为残余应力的释放,利用静力平衡条件将作用于飞机结构件的残余应力等效为外力后,依据小变形理论创新性地建立加工变形的分析模型。通过全面地考虑拉压、弯曲、以及转角引起的飞机结构件的厚向位置变化,利用叠加原理建立了残余应力再分布的力学模型。本研究建立的解析模型,不仅能够准确地计算飞机结构件的加工变形,还能够分析毛坯残余应力的再分布状态,通过与有限元仿真值、实验测量值进行比较,结果表明:无论是幅值还是变形曲线,解析值都与仿真值具有高度一致性,而与测量值相比,尽管在变形曲线上具有很好的吻合性,但由于残余应力的测量误差使得两者在幅值上亦存在一定误差。

轧制6061/7075铝合金复合板的工艺优化

采用轧制、中间退火和扩散退火的组合工艺,制备了6种不同工艺下的6061/7075铝合金层状金属复合板,分析了不同工艺下复合板的组织特征和形成原因,对比研究了不同工艺下复合板的力学性能。结果表明:冷轧、热轧均能获得沿轧向分布的纤维度良好的晶粒组织,恰当的中间退火和扩散退火加速了两侧基体金属的元素扩散,促进冶金结合。但热轧不存在轧制变形后的加工硬化,力学性能较冷轧复合板差;结合应力-应变曲线可知,冷轧+冷轧+中间退火+冷轧+扩散退火工艺下获得的6061/7075复合板综合性能最高,抗拉强度为214 MPa,伸长率20%,弹性模量8. 026 GPa。

试样尺寸对淬火铝合金厚板残余应力的影响

通过测量从淬火铝合金厚板上取出的一定大小的试样以测量原始铝合金厚板的残余应力值作为一种广泛使用的方法,在层削法、裂纹柔度法、X射线衍射法和中子衍射法中均有应用。以层削法为例,针对由于采用不同尺寸的试样而对7075铝合金厚板残余应力测量结果产生的影响进行了仿真分析和实验研究。结果表明,取样的尺寸对铝合金厚板残余应力的测量结果有重要影响。当试样在长宽方向上的尺寸小于2倍的"特征距离"(等于试样的厚度)时,试样将丧失保持原铝合金厚板真实残余应力的能力,测量结果将严重偏离真实值。基于此,在任何针对淬火铝合金厚板的残余应力测量方法中,当需要使用一定大小的试样对原铝合金厚板残余应力进行测量时,都必须保证试样在长宽方向上的尺寸大于2倍的"特征距离"。