AZ31B镁合金电子束焊接接头疲劳裂纹扩展速率分析

对AZ31B镁合金母材及其电子束焊接接头疲劳裂纹扩展速率进行研究,测试缺口位于母材、焊缝、热影响区(HAZ)时3组试验的裂纹扩展门槛值及扩展速率,并对3种试样疲劳裂纹扩展断口进行SEM分析.结果表明:缺口位于焊缝的裂纹扩展门槛值高于母材及HAZ,且疲劳裂纹扩展速率小于母材及HAZ.AZ31B镁合金母材及HAZ疲劳裂纹扩展断口都呈现河流状花样,为准解理脆性断口;焊缝的疲劳裂纹扩展断口中有许多撕裂棱、韧窝,表现出一定韧性,断口为以脆性为主的韧-脆混合断裂;随着裂纹扩展速率增大,三者断口中的解理台阶变粗大,疲劳条带变宽.     

30CrMnSiNi2A钢电子束焊接头的疲劳裂纹扩展特性研究

比较了26mm厚30CrMnSiNi2A超高强度钢电子束焊接头的母材、热影响区和焊缝区的疲劳裂纹扩展速率.试验结果表明,母材的抗疲劳裂纹扩展性能最好;热影响区抗疲劳裂纹扩展性能相对较弱;焊缝区的抗疲劳裂纹扩展性能接近母材.分别观察了母材、热影响区和焊缝区3个区域疲劳试样的断口形貌,发现接头各区域均呈现多源启裂特征,在稳...     

A7N01铝合金焊接接头组织和疲劳性能研究

研究了A7N01高强铝合金焊接接头的组织性能和疲劳性能。结果表明:焊缝中心为铸造组织,近缝热影响区为晶粒粗大的变形晶粒,远离焊缝的母材区为轧制态组织;焊接接头各微区显微硬度分布不均匀,热影响区存在"软化现象";预置缺口的焊接试样在相同应力幅下,母材区疲劳寿命最长,热影响区次之,焊缝区最短;A7N01铝合金的TIG焊结构多数在焊缝区发生疲劳断裂,焊缝区的表面气孔、夹杂等缺陷和热裂纹是引起疲劳失效启裂的主要原因,焊缝区屈服强度低可能是导致该微区疲劳扩展寿命低的直接原因。     

锻造TC4钛合金电子束焊接接头的疲劳破坏机制

对锻造TC4钛合金电子束焊接(EBW)接头进行了应力控制的高周疲劳试验和应变控制的低周疲劳试验,利用扫描电子显微镜对疲劳断口进行观察与分析,研究了疲劳裂纹的起裂机制.研究结果表明:所有的高周疲劳试样裂纹起裂位置和最后断裂位置均发生在母材区,而低周疲劳试验试样断裂位置表现出不确定性,在焊缝区和母材区均可导致裂纹起裂.高周疲劳载荷下,裂纹起源于表面滑移;低周疲劳时,裂纹可能在接头母材区的表面起裂,也可能在接头焊缝的内部缺陷处起裂,裂纹起裂模式取决于载荷大小.      

铝合金T型接头双激光束焊接断裂行为研究

为推动双光束激光焊接在国产大型客机机身壁板上的应用,系统研究了6000系列铝合金T型接头CO2激光焊接试验件的断裂行为。试验表明:在横向拉伸、纵向拉伸和剪切这3种检测方式下,T型接头的起裂位置均为焊趾处,裂纹沿着下熔合线扩展,下熔合线区为T型焊接接头的薄弱区。     

薄壁结构焊接接头CTOD试验分析

设计测试薄壁结构平面应力断裂韧性的三点弯曲测试试样,应用于GH4169焊接接头CTOD测试试验。采用光学金相显微镜和扫描电镜观察分析各试样的裂纹扩展形貌和断口形貌。依据BS7448标准的规定分析CTOD测试过程有效性。结果表明,采用设计三点弯曲试样进行的GH4169焊接接头CTOD测试过程是有效的;GH4169母材的断裂韧性较好,裂纹为延性起裂特性;GH4169焊缝和熔合区的断裂韧性较差,裂纹为脆性起裂特性。     

2219铝合金厚板TIG焊接头组织与力学性能研究

采用氦弧打底+氩弧填充、盖面的焊接工艺对2219-T87铝合金15 mm厚板进行TIG焊接试验，研究其焊缝成形和组织力学性能。结果表明，此工艺焊缝成形美观，无可见焊接缺陷，气孔抑制效果好，接头平均抗拉强度为278.22 MPa，平均断后延伸率为3.89%，接头平均强度系数达到58.94%。接头硬度整体表现为焊缝中心最低，从焊缝中心到母材呈现先增大后局部降低再增大的趋势；且焊缝中心填充层硬度高于打底层和盖面层。熔合区的微观组织为柱状树枝晶和胞状树枝晶，且垂直于熔合线生长，在靠近熔合区两侧出现了等轴细晶带。焊接接头断面有较多撕裂棱和韧窝，局部发现第二相粒子和微孔，其断裂机制为典型的韧性断裂。     

激光焊接螺栓组件焊缝开裂失效分析

GH6159合金/GH4169合金激光焊接螺栓组件,在试验后发现螺栓顶端焊缝处存在裂纹。为分析螺栓组件裂纹产生原因,对裂纹螺栓进行断口和金相分析,确定裂纹的性质为过载断裂,裂纹从焊合区和未焊合区的界线起始,沿焊接深度方向扩展。为分析裂纹产生规律,采用金相法测量焊接深度,发现裂纹处焊接深度大多比非裂纹处焊接深度小,且焊接深度不满足设计要求。对螺栓组件使用情况和强度进行分析确定,弹簧片优先受力,使得焊接结构承受较大载荷,焊接薄弱处因焊接有效承载面积小而过载破坏,是开裂的主要原因。提出了结构和焊接优化措施,在试车过程中螺栓组件开裂问题未复现,说明采取的优化措施有效。     

铝锂合金8090+Ce的疲劳断裂特征

研究了铝锂合金8090+Ce的疲劳寿命和断裂特征,并与2024铝合金相对比。结果表明,铝锂合金8090+Ce各应力水平的疲劳寿命均低于2024铝合金;其早期沿晶萌生的微小裂纹一般沿晶纵向扩展,而发展成为非扩展短裂纹,不构成对疲劳寿命的危害;其主断裂面上的短裂纹沿粗滑移带扩展,显示宽而平直的典型脆性疲劳条带;其瞬断方式为穿晶粗滑移带开裂+穿晶和沿晶撕裂的混合型,对应于较小的失稳扩展临界尺寸。     

焊接速度对7050-T7451铝合金搅拌摩擦焊接头疲劳性能的影响

针对5 mm厚航空用铝合金7050-T7451进行了不同焊速时搅拌摩擦焊接头的微观结构和低周疲劳性能的研究.结果表明:接头焊核区面积与焊核区晶粒度都随着焊接速度的增加而减小;转速为400 r/min、焊速为40 mm/min时,接头具有最好的疲劳性能;搅拌摩擦焊接头的低周疲劳裂纹均在接头底部启裂,沿前进侧热机械影响区与焊核区的过渡区域扩展至断裂.     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.