估算低温下金属材料应变疲劳寿命和疲劳极限的新方法

本文建立了估算低温下金属材料应变疲劳寿命的新方法,并首次提出了金属疲劳极限的热激活模型。该模型可定量地解释温度和频率对疲劳极限的影响。研究结果表明,提出的应变疲劳公式可很好地拟合低温下金属材料应变疲劳寿命的实验结果;疲劳极限可表示成非热激活分量σ_(ai)(ε_(apc))和热激活分量σ_a~*(T,ε_p)之和;σ_(ai)(ε_(apc))是与温度和频率(或应变速率)无关的材料常数;σ_a~*(T,ε_p)与流变应力的热激活分量近似相等。最后用文献中的实验数据对本文提出的低温下就应变疲劳寿命和疲劳极限的估算方法进行了验证。     

微量预应变对15MnVN钢初始屈服抗力和疲劳极限的影响

研究了微量拉伸预应变对１５ＭｎＶＮ钢初始屈服抗力和疲劳性能的影响。结果表明,微量预应变可使材料的疲劳强度下降,同时也使初始屈服抗力下降。加载方向对预应变后的比例极限影响很小。在供应状态和预应变状态下,材料的理论疲劳极限与比例极限近似相等。     

Cocontraction changes in muscular fatigue at different levels of isometric contraction

Ten normal subjects participated in a study designed to contrast results obtained in pre- and post-fatigue states. The measures contrasted were the IEMG ratios of agonist/antagonist pairs of muscles. The experimental task was an 8 s ramp isometric elbow flexion ranging from 0 to 100% of a maximal voluntary contraction (MVC). IEMG ratios were obtained at levels of 20, 40, 60 and 80% MVC. Records from the following muscles were obtained with surface electrodes: biceps brachii (BB), brachioradialis (BR), triceps brachii (TB) and anconeus (SU). The torque at the elbow joint was measured by a Cybex II dynamometer. Fatigue was induced using a 60% MVC of elbow flexion maintained during 5 minutes. The data were collected on-line at a sampling rate of 1 kHz. The results indicated that the IEMG ratios (BB/TB and BR/SU) presented a tendency, across subjects, toward a decrease at the levels of 40%, 60% and 80% MVC at the post- relative to the pre-fatigue state. The BB/BR ratios remained stable. These changes in the post-fatigue ratios disclose a tendency toward a saturation of the agonist occurring concomitantly with an increased level of contraction of the antagonists.     

多功能聚乙烯母粒及棚膜的研制

本文报道了不同浓度的赤霉素及其栽培密度对芹菜产量的影响。结果表明，赤霉素３０×１０＾＿６和１０×１０ｃｍ的密度为最佳组合，增产达２０％，叶绿素含量提高０．１５ｍｇ／ｄｍ＾２，并有抑制叶片徒长现象，从而增加了经济产量。     

LIFE PREDICTION OF CROSS-PLY METAL MATRIX COMPOSITES UNDERGOING THERMOMECHANICAL FATIGUE

A life prediction model that was originally developed for the axial loading of unidirectional metal matrix composites (MMCs) undergoing combined thermal and mechanical loading is extended to the axial loading of cross-ply MMCs by adding an internally initiated matrix fatigue damage term. This new term accounts for the growth of cracks that initiate at the location where fibre–matrix separation occurs in the transversely-oriented plies. A comparison of the model predictions to experimental data on SCS-6/Timetal 21S shows that the model reasonably accounts for the dependence of applied stress, temperature and environment, as well as cyclic frequency. The dominant damage accumulation process for cross-ply MMCs with weak fibre–matrix bonds is described by this internally initiated matrix fatigue damage process for most stress–temperature cycle combinations. However, the fibre-dominated damage accumulation process operates under in-phase TMF when both stress and temperature are high. Environment-enhanced matrix fatigue is the dominant damage accumulation process under isothermal fatigue when stress is low and temperature is high.     

SMALL CRACK GROWTH AND FATIGUE LIFE PREDICTIONS FOR HIGH-STRENGTH ALUMINIUM ALLOYS: PART I—EXPERIMENTAL AND FRACTURE MECHANICS ANALYSIS

The small crack effect was investigated in two high-strength aluminium alloys: 7075-T6 bare and LC9cs clad alloy. Both experimental and analytical investigations were conducted to study crack initiation and growth of small cracks. In the experimental program, fatigue tests, small crack and large crack tests were conducted under constant amplitude and Mini-TWIST spectrum loading conditions. A pronounced small crack effect was observed in both materials, especially for the negative stress ratios. For all loading conditions, most of the fatigue life of the SENT specimens was shown to be crack propagation from initial material defects or from the cladding layer. In the analysis program, three-dimensional finite element and weight function methods were used to determine stress intensity factors and to develop SIF equations for surface and corner cracks at the notch in the SENT specimens. A plasticity-induced crack-closure model was used to correlate small and large crack data, and to make fatigue life predictions. Predicted crack-growth rates and fatigue lives agreed well with experiments. A total fatigue life prediction method for the aluminium alloys was developed and demonstrated using the crack-closure model.     

SHORT FATIGUE CRACK GROWTH BEHAVIOUR IN WASPALOY AT ROOM AND ELEVATED TEMPERATURES

Short fatigue crack growth tests have been carried out at room and elevated temperatures using the nickel-based superalloy known as Waspaloy. A fully automated computer controlled system has been developed and employed for controlling the testing and monitoring of the growth of freely initiated surface short cracks on smooth specimens. Surface cracks as small as 10 um in length have been detected and recorded at temperatures up to 700°C. Anomalous short crack propagation behaviour was observed when comparisons were made with the corresponding long crack behaviour. Some aspects of mechanical, microstructural and environmental effects on the short fatigue crack growth behaviour of the material are discussed.     

应变疲劳循环软化机制的观察,确证及定量估测

通过透射电镜观察和循环应变加时效的试验方法，对淬火回火态地低碳合金钢的循环软件机制进行了研究。     

A survey of serious aircraft accidents involving fatigue fracture

A world-wide survey of serious aircraft accidents involving fatigue fracture has been carried out. The study includes not only fatal accidents, but also those in which the damage to the airframe was substantial or greater. The accidents cover civil and, to a limited extent, military aircraft. A total of 1885 accidents since 1927 were identified as having fatigue fracture as a related cause, and these accidents resulted in 2240 deaths. Engine/transmission failure and landing-gear failure were the most common cause of recent fixed-wing accidents, while the most prevalent rotary-wing problems were failure of the engine/transmission and of the tail-rotor. Currently there is a yearly average of about 100 serious fatigue accidents (69 fixed-wing and 31 rotary-wing).     

仿生非光滑表面45#钢模具的热疲劳性能

利用动物体表仿生学原理制备45#钢模具非光滑表面试样,通过自约束冷热疲劳试验方法,对比研究了光滑与非光滑试样的热疲劳特性,观察分析了热疲劳裂纹在仿生非光滑表面上扩展的形貌和内部机理.结果表明,非光滑单元体对热疲劳裂纹有阻断作用,仿生非光滑表面使模具的热疲劳抗力显著提高,模具表面的热疲劳性能在非光滑单元体的某一密度范围内达到最佳状态.在细晶强化、合金强化等强化机制下,由仿生非光滑单元体构筑的"桩钉"效应是导致模具抗热疲劳性提高的主要原因.