两参数Birnbaum-Saunders疲劳寿命分布图像特征的拓展分析

研究了两参数BS疲劳寿命分布BS(α,β)密度函数f(t)和失效率函数λ(t)顶峰点的位置以及在中位数β左右侧的图像特征,并给出了判断失效率函数图像特征的更为一般的结论.     

冲角工况下列车车轮损伤机理研究

曲线通过和蛇行运动时将会在轮轨间产生一定的冲角,为探究列车车轮在冲角工况下的损伤机理,利用JD-1轮轨模拟试验机对列车车轮进行滚动接触疲劳试验.结果表明:在冲角工况下车轮试件磨痕的不同区域存在不同的损伤机理,按损伤机理的不同可以将其分为塑性堆积区、疲劳损伤区和磨损区三个区域.在应力发生剧烈变化且应力方向由高应力区指向低应力区的区域将会出现材料的塑性堆积,并且在堆积处产生疲劳裂纹.滚动接触下的疲劳裂纹可以萌生于表面和亚表面,在较强应力作用下,车轮材料的晶粒发生了明显的细化,在横截面上呈现出纤维状组织.     

Great enhancement in remnant polarization of SrBi4Ti4O15 thin films by A-site doping of Fe3+ ions

SrBi4-xFexTi4O15 (SBFT-x) thin films (x = 0.00, 0.05, 0.08, 0.15) have been synthesized on Pt/Ti/SiO2/Si (100) substrates by sol-gel method. This paper finds that Fe-doping does not change the crystal structure of SrBi4Ti4O15 (SBTi). The coercive filed (Ec) and remnant polarisation (Pr) increase at first, then decrease with the increase of Fe doping content. At a maximum applied field of 229 kV/cm, the 2Pr reaches a maximum value of 91.1 μC/cm2 at x = 0.05 and the corresponding Ec is 72 kV/cm. The 2Pr increases by about 260% and the Ec decreases by about 6%, respectively. Obviously, the ferroelectric property of SrBi4Ti4O15 is greatly enhanced by Fe doping. The fatigue-endurance characteristic of the SBFT-0.05 is not improved. After 1.1×109 read/write cycles at a frequency of 50 kHz, the nonvolatile polarisations (Pnv = P*-P∧) decreased about 48% of its initial value.     

FATIGUE GROWTH MODELING OF MIXED-MODE CRACK IN PLANE ELASTIC MEDIA

This paper presents an extension of a displacement discontinuity method with cracktip elements （a boundary element method） proposed by the author for fatigue crack growth analysis in plane elastic media under mixed-mode conditions. The boundary element method consists of the non-singular displacement discontinuity elements presented by Crouch and Starfield and the crack-tip displacement discontinuity elements due to the author. In the boundary element implementation the left or right crack-tip element is placed locally at the corresponding left or right crack tip on top of the non-singular displacement discontinuity elements that cover the entire crack surface and the other boundaries. Crack growth is simulated with an incremental crack extension analysis based on the maximum circumferential stress criterion. In the numerical simulation, for each increment of crack extension, remeshing of existing boundaries is not required because of an intrinsic feature of the numerical approach. Crack growth is modeled by adding new boundary elements on the incremental crack extension to the previous crack boundaries. At the same time, the element characteristics of some related elements are adjusted according to the manner in which the boundary element method is implemented. As an example, the fatigue growth process of cracks emanating from a circular hole in a plane elastic plate is simulated using the numerical simulation approach.     

拉丝环境湿度对高强度光纤动态疲劳的影响

文章研究了高强度石英玻璃光纤的动态疲劳性能与拉丝环境相对湿度的函数关系。光纤是在采用石墨感应加热炉加热,并在控制温度、相对湿度和拉丝环境尘埃粒子数的条件下拉制的。所谓拉丝环境指的是从感应加热拉丝炉至涂覆点之间的空间。通常,人们采用两种不同的加载方式,即拉伸和两点弯曲来测量拉制的光纤的动态疲劳。业已发现,拉丝湿度对用张力法加载方式测得的光纤的动态疲劳起着决定性的影响。     

一种基于耗散能计算的高周疲劳参数预测方法

在热力学框架下,基于薄板假设,建立金属材料薄板试样在高周疲劳载荷作用下的热传导方程,将试样温度场数据和实时载荷信号导入,准确计算与高周疲劳损伤相关的单个循环内耗散能. 基于该方法,以316L不锈钢材料为例,通过实时监测试样不同应力水平下高周疲劳破坏全过程中耗散能的变化,拟合出耗散能-疲劳寿命曲线,呈现与传统的应力-疲劳寿命曲线相同的规律;提出一种新的预测高周疲劳极限的能量法,确定的疲劳极限与实验值相近.     

CrMoV合金钢的微动疲劳实验研究

本文利用一种自行设计的微动疲劳实验装置研究CrMoV合金钢的微动疲劳特性。作者研究了接触压力对材料微动疲劳寿命的影响规律,得到了研究条件下CrMoV合金钢的接触压力阈值。当接触压力较小时,微动桥压块与试件表面间有相对滑动,微动疲劳寿命随接触压力的增加快速下降;当接触压力达到或超过阈值62.5MPa时,微动疲劳寿命达到最低值并不再随接触压力的增加而下降。本文给出了CrMoV合金钢在接触压力为225MPa的微动疲劳曲线和零接触压力(纯)疲劳曲线,并给出微动疲劳强度与常规疲劳强度的关系,分析了微动疲劳破坏的微观机理。     

电镀铜薄膜力学性能的实验研究

电子器件中大量使用铜膜作为电信号通道,而且一般采用电镀工艺制成.铜膜的力学性能参数对于其热疲劳可靠性的研究非常重要.目前有关该材料的力学性能研究尚不充分,而且数据极为不统一.本文借助于纳米压痕法、声发射等实验手段对电镀铜薄膜的静态力学性能(包括弹性模量和屈服强度等)及疲劳性能进行了测试.结果发现,与大块铜材料相比,电镀铜薄膜的弹性模量低很多,但屈服强度与大块铜材料相当,甚至高出200％.同时,本文采用弯曲疲劳实验,以电阻变化为失效判据,对镀铜材料的疲劳性能进行了测试,获取了该材料不同失效判据下的疲劳寿命预测模型的系数.     

The effect of frequency and sample shape on fatigue behaviors of DZ125 superalloy

The effect of frequency and sample shape on fatigue behaviors of DZ125 superalloy are systematically studied. The results show that fatigue fracture still occurs above the cycle of 10⁸ for tests carried out at the frequency of f = 20 kHz and stress ratio R = ?1, so the traditional fatigue limit at cycle of 10⁷ is not appropriate for fatigue design. Fatigue fracture surfaces are perpendicular to stress axis for cylindrical and plate specimens, and the fatigue cracks originate from the extra surface of the specimens. Fatigue crack is apt to propagate from cutting direction to forward direction, which occurs mainly in the second propagation stage at higher stress amplitude. There is an obvious frequency effect for DZ125 superalloy. The higher the test frequency is, the more serious the effect of frequency on fatigue behaviors of the alloy. After the frequency correction, the ultra-high cycle fatigue S-N curve well coincide with the traditional fatigue S-N curve.     

Damage monitor and life prediction of carbon fiber-reinforced ceramic-matrix composites at room and elevated temperatures using hysteresis dissipated energy-based damage parameter

In this paper, the damage monitor and life prediction of carbon fiber-reinforced ceramic-matrix composites (C/SiC CMCs) have been investigated using the hysteresis dissipated energy-based damage parameter. The evolution of the interface shear stress, hysteresis dissipated energy, hysteresis dissipated energy-based damage parameter and the broken fibers fraction vs. cycle number, the fatigue life S?N curves of unidirectional, cross-ply and 2.5D C/SiC composites at room temperature and 800 °C in air atmosphere have been analyzed. For unidirectional C/SiC, the hysteresis dissipated energy and hysteresis dissipated energy-based damage parameter first increase and then decrease with cycle number, and the fatigue limit stress decreases from 88% tensile strength at room temperature to 20% of the tensile strength at 800 °C in air atmosphere; for cross-ply C/SiC, the hysteresis dissipated energy and hysteresis dissipated energy-based damage parameter decrease with increasing applied cycles, and the fatigue limit stress decreases from 85% tensile strength at room temperature to 22% tensile strength at 800 °C in air; and for 2.5D C/SiC, the hysteresis dissipated energy and hysteresis dissipated energy-based damage parameter increases with cycle number, and the fatigue limit stress decreases from 70% tensile strength at room temperature to 25% tensile strength at 800 °C in air.