碳纤维增强热塑性复合材料/钛合金激光焊接模拟仿真研究

为研究碳纤维增强热塑性复合材料（CFRTP）与钛合金激光高速旋转焊接接头形成机理,探索工艺参数对接头质量的影响规律,建立了CFRTP/钛合金激光高速旋转焊接数学模型,利用有限元方法对焊接接头温度分布进行理论计算,分析了激光功率、焊接速度和光斑半径等工艺参数对接头熔宽和熔深的影响规律,并将理论计算结果与试验结果进行了对比分析。结果表明,利用有限元模拟仿真能够较好地预测CFRTP/钛合金接头的温度场分布;通过对温度场求解结果的数值分析,可以实现CFRTP/钛合金激光焊接过程中接头熔深、熔宽的预测;理论计算结果与试验结果基本吻合,表明模拟仿真能够为CFRTP/钛合金高质量激光焊接提供理论支持。     

电子束焊接气孔的控制

本文介绍了焊接气孔产生的原因，根据电子束非穿透焊缝根部气孔及穿透焊缝内部气孔的形成机理，提出了减少气孔的焊接工艺措施。     

扫描振镜激光TC4钛合金焊接性能及熔池流动行为

钛合金广泛应用于飞行器及航空航天发动机，激光焊是连接钛合金的优异焊接方法，目前主要问题是气孔导致的接头性能降低。扫描激光能显著改善激光焊接过程中的匙孔行为及熔池流动状态，从而降低气孔率、细化晶粒，最终提高接头性能。采用光纤激光器对4 mm厚TC4钛合金进行扫描振镜激光焊接，对比分析了以0.4 mm为步长、0.4～1.6 mm扫描幅度扫描前后的焊缝成形、力学性能、晶粒细化程度、熔池流动与匙孔行为。结果表明圆形扫描路径下，激光功率为4 kW、焊接速度为1.2 m/min、离焦量为0、扫描频率为100 Hz、扫描幅度为0.8 mm时，匙孔型气孔受显著抑制，且对应的接头抗拉强度最高，为1 025.03 MPa,达到了母材的96%。与无扫描光束相比较，扫描幅度为0.8 mm的接头上部平均晶粒面积减小了65%;圆形扫描的加入使熔池流动具有方向性，同时扫描激光能扩大并稳定匙孔，减少飞溅与气孔。     

钛合金激光焊接残余应力试验与数值模拟

采用小孔释放法对钛合金薄板激光焊接残余应力进行了试验研究,并基于ANSYS分析软件,针对钛合金薄板的焊接残余应力进行了数值模拟,分析了不同焊接工艺参数对激光焊接残余应力分布的影响.     

TiNi记忆合金激光焊接缺陷分析

针对TiNi形状记忆合金薄板采用NdYAG连续激光进行自熔焊接和预填稀土薄片的工艺研究。试验表明,合理的焊接工艺参数可以获得良好的焊缝成形,然而,同常规的钛合金激光焊接一样,Ti Ni形状记忆合金主要焊接缺陷是气孔和裂纹。基于X射线图像、扫描电镜等手段对焊缝缺陷的位置、形状、大小和周边组织变化进行了进一步观察,并对缺陷形成的原因和控制进行了分析。     

双光束激光焊接技术研究现状及应用

阐述了双光束激光焊接技术特点及研究现状,对钛合金双光束激光焊接工艺进行研究,采用双光束激光焊能增强激光焊接的工艺适应性,减少焊接缺陷,焊接过程更加稳定。试验研究表明,钛合金双光束激光焊焊缝成形良好,钛合金双光束激光焊接头强度与母材相当。采用双光束激光焊接某钛合金薄壁结构件,满足设计要求的焊缝质量标准要求。     

钛合金激光焊接研究现状

随着航空工业的发展,钛合金在航空结构中有着越来越广泛的应用。焊接作为重要的连接手段,其制造接头的力学性能决定了构件的使用性能。激光焊接具有高能束焊接方法热输入小、残余应力及变形小的特点,焊接质量高,并且能在开放环境中开展工作,已成为真空电子束焊接外另一种优秀的钛合金焊接方法,是近年研究的热点。总结了近期钛合金激光焊接的一些研究工作,重点介绍了关于激光焊接钛合金组织性能调控方面的成果,并讨论了钛合金激光焊所存在的问题,具体内容包括：激光类型和扫描方式对接头质量的影响、三种典型(α型、α+β型和β型)钛合金激光焊接头组织性能特点、焊后热处理对钛合金激光焊接头组织性能调控方法。为采用激光焊接方法制造高质量钛合金接头研究工作提供参考。     

TC4钛合金激光焊中工艺参数对气孔生成量的影响

文摘研究了TC4钛合金激光焊接在平焊、横焊两种位置下工艺参数对气孔生成量的影响。结果表明:平焊时,气孔生成量随激光功率、离焦量的增大先减小后增大,随焊接速度的增大先增大后减小;横焊时,气孔生成量随激光功率的增大而增大,随焊接速度的增大而减小,随离焦量的增大先减小后增大。利用正交试验方法得到的优化工艺参数进行焊接,气孔生成量大幅减少,在两种位置下均可得到内部质量良好的焊缝。     

基于Gauss热源模型的BT20钛合金管口激光焊接数值模拟

基于热弹塑性有限元方法,建立激光焊接的热力学计算模型,利用三维有限元分析软件AN-SYS,使用其APDL语言,对BT20钛合金管接头激光焊接过程中的温度场和应力场有限元模拟问题进行了研究.结合数值计算,讨论了激光焊接过程中采用瞬间空冷后,试件内应力的分布情况.     

TC4钛合金激光窄间隙焊接工艺与组织特征研究

使用IPG YLS-5000多模光纤激光器实现了12mm厚TC4钛合金光纤激光窄间隙焊接,优化了焊接工艺,并对焊缝组织和显微硬度进行了分析.结果表明:激光窄间隙焊接容易产生气孔和侧壁未熔合缺陷,优化后的焊接工艺能显著减少气孔并消除未融合缺陷.母材显微组织为典型的等轴组织,焊缝区显微组织由粗大的β柱状晶和网篮状马氏体α'组成.热影响区晶粒尺寸明显细化.热影响区组织由细小的针状马氏体α'、转变α组织和β转变组织构成.焊缝区和热影响区的显微硬度高于母材,近焊缝热影响区显微硬度达到最大值.     

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.