用本模型可以计算复杂谱载荷作用下的疲劳裂纹扩展寿命。
We can predict the fatigue life of structures under complex spectrum loading by the present model.
机械零（构）件的寿命由裂纹形成时间（即疲劳寿命）和裂纹扩展寿命两部分组成。
The whole life of an equipment part consists of the crack forming life (i. e. , the fatigue life or the damage accumulation life) and the crack extension life.
采用虚拟裂纹闭合技术计算裂纹扩展的应变能释放率，并对裂纹扩展寿命进行计算。
The strain energy release rate of the crack propagation was calculated by using virtual crack closure technique, and fatigue life was forecasted.
计算了飞机机翼加劲板和飞机起落架旋转臂在复杂谱载荷作用下的疲劳裂纹扩展寿命。
The fatigue lives of the stiffened panel of a wing and the landing gear of an aircraft under spectrum loadings also have been predicted.
最后，给出了概率断裂力学方法预测焊接钢梁在给定可靠度下疲劳裂纹扩展寿命的算例。
At last, adopting PFM to estimate fatigue crack growth life for welded steel beams under given reliability.
要准确预测结构在变幅载荷谱下的疲劳裂纹扩展寿命，必须研究超载对裂纹扩展的影响。
Therefore, it is necessary to evaluate the influence of overloads on crack growth rates for the fatigue life prediction of structures subject to variable amplitude loadings.
为了预测焊接构件在中温环境下的疲劳裂纹扩展寿命，提出了一组新的疲劳裂纹扩展方程。
To predict the fatigue crack growth life of welded equipments at elevated temperature, a group of novel fatigue crack growth equations was proposed.
针对疲劳裂纹扩展寿命失效概率计算的复杂性，提出基于神经网络响应面的可靠性分析方法。
In response to the complexity of calculation for failure probability regarding fatigue crack growth life, a method for reliability analysis based on neural network response surface was presented.
通过对结构疲劳裂纹形成寿命和裂纹扩展寿命的研究，提出了连接件疲劳全寿命的计算方法。
A calculating method of the total fatigue life of structural joints is proposed based on a study on both the fatigue crack initiation life and crack growth life of joints.
进一步，预估了管路连接件裂纹萌生寿命，预测了裂纹扩展路径并预估了疲劳裂纹扩展寿命。
The fatigue crack initiation life for pipeline connection assemblies is also predicted. The fatigue crack propagation path is analyzed and the fatigue crack propagation life is predicted.
通过分析影响裂纹扩展寿命的多个随机因素，使用疲劳寿命模型，讨论了裂纹尺寸的计算方法。
By analyzing stochastic factors to influence the fatigue crack expandable life, fatigue life model was used and a calculation method for crack size was discussed.
此模型首先给出了多个失效模式系统失效概率敏度与单夹杂裂纹扩展寿命失效概率敏度之间的关系；
The relationship of sensitivity for the system failure probability was firstly constructed between multiple failure modes and single failure mode.
应用概率断裂力学方法，对含初始裂纹体的金属材料(铝合金)构件的疲劳裂纹扩展寿命进行可靠性分析。
Applying probabilistic fracture mechanics approach (PFMA), the reliability analysis is carried out for helicopter metal material (aluminum alloy) structure having initial cracks.
将该方法加以拓展，建立了含有不同尺寸缺陷的粉末盘断裂力学有限元模型，并对其裂纹扩展寿命进行了评估。
The finite element model could be developed to predict the propagation life of PM turbine disk containing defects with different sizes.
通过算例，将疲劳裂纹扩展速率公式中的各个参量全部随机化，并预测构件在给定可靠度下的疲劳裂纹扩展寿命。
By an example, each parameters are randomized in the Paris formula, and the propagation life of fatigue of the structure is prognosticated on the presented reliability.
结合裂纹扩展率单一曲线模型对肘板裂纹扩展寿命进行了预报，预报结果与实验结果符合得较好，说明所采用的方法可行。
The fatigue life for bracket was predicted by way of the unique crack growth rate model incorporating the above SIF functions and the predicted results were in good agreement with the experiment data.
最后，应用概率断裂力学方法(PFMA)，对含初始裂纹体的直升机金属材料(铝合金)构件的疲劳裂纹扩展寿命进行可靠性分析。
Finally, applying Probabilistic Fracture Mechanics Approach (PFMA), the reliability analysis is carried out for helicopter metal material (aluminum alloy) structure having initial cracks.
总结了机械寿命预测方法(包括疲劳损伤寿命计算和裂纹扩展寿命计算)，重点在于用理论分析的方法来代替大量的实物试验这一类方法。
Methods of predicting machine life has systematically summarized with the emphasis on those which use theoretical analysis to substitute large scale prototype experiments.
结合粉末冶金材料含有非金属夹杂裂纹的特点，以裂纹扩展寿命可靠性分析的剩余强度模型与寿命干涉模型为基础，建立了多夹杂裂纹扩展的可靠性敏度分析模型。
Based on residual strength interference model and life interference model, a sensitivity analysis method on reliability was proposed for the fatigue crack growth life of powder metallurgy materials.
研究表明，大量规则分布、互不重叠的合金化区及其周围的相变硬化区从总体上降低了疲劳裂纹扩展速率，提高了材料的疲劳寿命。
It is shown that a regular pattern distribution of scattered alloying zones which surrounded by phase transformation zone can retard the fatigue crack growth rate and improve the fatigue life.
本文采用断裂力学方法来估算结构构件的疲劳寿命，这其中主要围绕裂纹扩展速率表达式展开研究。
Fracture mechanics is adopted to estimate the fatigue life of structural members, and among the rest, crack growth rate formula is studied.
晶粒尺寸对形成寿命、扩展寿命和裂纹长度的分布特性都有影响。
The initiation life, growth life and crack length distributions are affected by the grain size.
疲劳寿命的计算采用断裂力学方法，建立疲劳裂纹扩展模型和失效模式的极限状态方程。
Fatigue damage estimation of the tendons was made using fracture mechanics approach, establishing the fracture crack growth rate model and limit state equations for failure modes.
因此，计算筒体尤其是其危险部位的应力，预测其裂纹扩展速度或其使用寿命，具有非常重要的实际意义。
Accordingly, it is very important and significant to calculate the stress of the cylinder especially in the dangerous position, and to predict its crackle expanding speed and its surplus life.
结果表明：与纯低周载荷作用相比，高低周复合载荷下球墨铸铁的裂纹扩展速率明显加快，极大地降低材料的疲劳寿命。
The results show that the crack growth rate under high-low cycle complex fatigue load is greater than that under low cycle fatigue load, and so the fatigue life is obviously reduced.
发现裂纹剖面宏观形貌特征与制动盘疲劳裂纹扩展规律之间存在一定的关联，为制动盘寿命评估提供了新的思路。
The relation of law of the fatigue crack extending and feature of macro-profile is discovered, which provides a new method for the life estimation of the brake disc.
研究裂纹在谱载荷作用下的扩展规律对可靠预报平台等结构物的疲劳寿命具有十分重要的意义。
Studying of fatigue crack growth under different spectrum loadings is very important for the reliable life prediction of ship structures.
试样寿命主要由裂纹萌生寿命和断裂寿命组成，扩展寿命所占比例较少。
The crack initiation life and the crack fracture life are the main life of the specimen.
预测和实测寿命对比表明，基于短裂纹扩展特性的预测能力有显著改善。
As compared with the experimental life it shows that the predicting ability based on the growth characteristics of short fatigue crack was improved obviously.
预测和实测寿命对比表明，基于短裂纹扩展特性的预测能力有显著改善。
As compared with the experimental life it shows that the predicting ability based on the growth characteristics of short fatigue crack was improved obviously.
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