纤维金属层极疲劳寿命预测的研究进展

简要介绍了纤维金属展板的起源、性能特点、应用现状与前景,对其疲劳损伤机理作了简要分析．对影响层板疲劳寿命的两个关键因素──桥接应力与分层扩展从理论分析与测量技术两方面结合自己的研究成果作了系统评析．详细分析了层板在等幅疲劳下寿命预测的研究现状．介绍了层板在变幅载荷下的疲劳行为（包括裂纹扩展与分层扩展）与寿命预测的研究进展,指出了目前预测模型的有待改进的建议．      

损伤对层合复合材料分层的影响

基于损伤内变量理论,用准三维有限单元法,分析了分层尖端区存在损伤时,Ｊ积分、能量释放率Ｇ以及裂尖附近应力场的变化规律·结果表明,裂尖损伤区的存在对Ⅰ型分层扩展起到屏蔽作用,其屏蔽机理是:损伤的存在消除了裂尖附近应力的奇异性,并在裂尖周围形成一个低层间应力区;损伤导致裂尖附近Ｊ积分不再守恒,但能量释放率降低·     

轴对称脱层圆板的后屈曲分析

基于Von Karrnan板理论,考虑横向剪切变形,建立了轴对称脱层圆板的后屈曲控制方程．应用正交配点法,将轴对称脱层圆板的后屈曲控制方程、边界条件、以及联接条件转化为非线性方程组,然后进行迭代求解．讨论了不同脱层深度和脱层半径对屈曲及后屈曲特性的影响,发现脱层屈曲荷栽随着脱层深度的减小和脱层半径的增大而减小,后屈曲模态也表现出不同的形式．最后与有关文献的结果进行了比较,二者相当吻合．     

Local delamination of InSb IRFPAs in liquid nitrogen shock tests

Both the local delamination and the local fracture, appearing in the InSb infrared focal plane arrays (IRFPAs) detectors in liquid nitrogen shock tests, restrict the final yield of the InSb IRFPAs detectors. To explore the mechanism of the local delamination appearing in the region of the negative electrode of the InSb IRFPAs detectors, basing on the created structural modeling of the InSb IRFPAs detectors, we obtain the distributions of the interfacial stresses in the different interfaces of the InSb IRFPAs detectors. After comparing the distributions of the simulated interfacial stresses with the measured local delamination region in the InSb IRFPAs detectors, we think that the local delamination originates from the interfacial shear stresses, and the crack extension is the typical sliding mode. Besides, the weakened gluing strength between the InSb chip and the underfill in the negative electrode region also causes this region to be prone to the local delamination. All these findings provide the theoretical references for both the structure design and the structure optimization of the InSb IRFPAs detectors assembly in the future.     

Selective role of bainitic lath boundary in influencing slip systems and consequent deformation mechanisms and delamination in high-strength low-alloy steel

We elucidate here the deformation behaviour and delamination phenomenon in a high-strength low-alloy bainitic steel, in terms of microstructure, texture and stress evolution during deformation via in situ electron back-scattered diffraction and electron microscopy. Furthermore, the selective role of bainitic lath boundary on slip systems was studied in terms of dislocation pile-up and grain boundary energy models. During tensile deformation, the texture evolution was concentrated at {1 1 0}<1 1 1> and the laths were turn parallel to loading direction. The determining role of lath on the deformation behaviour is governed by length/thickness (l/t) ratio. When l/t > 28, the strain accommodates along the bainite lath rather than along the normal direction. The delamination crack initiated normal to (0 1 1) plane, and become inclined to (0 1 1) plane with continued strain along (0 1 1) plane and lath plane. This indicated that the delamination is not brittle process but plastic process. The lack of dimples at the delaminated surface is because of lack of strain normal to the direction of lath. The delaminated (0 1 1) planes were associated with cleavage along the (1 0 0) plane.     

超临界环境下印刷线路板回收的分层实验研究

为了研究印刷线路板在超临界环境下分层的理想实验条件和扩大成果应用范围,实验采用无孔的印刷线路板部分为实验样本,简化了样本条件;引入含有不同铜层数的印刷线路板类型,扩大了线路板的研究范围;使用无水乙醇与水的不同比例混合的混合溶剂,增加了溶剂的研究范围;分析了压强对分层的影响。实验结果表明,温度对印刷线路板分层起着主导作用,印刷线路板中的铜层数增加有利于印刷线路板的分层,混合溶剂中无水乙醇与水的比例则对印刷线路板的分层无明显影响,压强对实验后的样本分层有重要影响。     

Application of laser ultrasonic technique for non-contact detection of drilling-induced delamination in aeronautical composite components

The detection of drilling-induced delamination in composite components is a vital and challenging task in aviation industry. Numerous key components of aircrafts are made of composite materials, and drilling is often a final operation during assembly. Drilling-induced delamination is a very serious defect that significantly reduces the structural reliability, but it is rather difficult to be detected effectively due to its special location. A novel application of laser ultrasonic technique for the detection of drilling-induced delamination in composites is presented in this paper. A carbon fiber reinforced plastic laminate with drilling holes was made as specimen. A laser ultrasonic system was constructed and experiments were performed to detect the drilling-induced delamination, based on propagation characteristic of ultrasonic waves generated by pulse laser with a wavelength of 1064 nm and pulse duration of 10 ns. A laser interferometer based on two wave mixing is used to measure ultrasonic wave signals, and the morphology features of the delamination are imaged clearly by laser ultrasonic C-scan testing. The results proved that the laser ultrasonic technique is a feasible and effective method for the detection of drilling-induced delamination in composite components.     

Micron-scale channel formation by the release and bond-back of pre-stressed thin films: A finite element analysis

Buckling of thin films on a rigid substrate during use or fabrication is a well-known but unwanted phenomenon. However, this phenomenon can also be exploited to generate well-controlled patterns at the micro and nano-scale. These patterned surfaces find various technological applications such as optical gratings or micro/nano-fluidic channels. In this article, we present a numerical model that accounts for the buckling-up of pre-strained thin films by a reduction of the interface toughness and the subsequent bond-back. Channels are formed whose dimensions can be controlled by tuning the film dimensions, film thickness and stiffness, the eigenstrain in the film and the cohesive interface energy between the film and the substrate. We will show how the buckling-up and draping back processes can be captured in terms of a limited set of dimensionless parameters, providing quantitative insight on how these parameters should be tuned to generate a specified channel geometry.     

Interlaminar fracture and low-velocity impact of carbon/epoxy composite materials

The interlaminar fracture and the low-velocity impact behavior of carbon/epoxy composite materials have been studied using width-tapered double cantilever beam (WTDCB), end-notched flexure (ENF), and Boeing impact specimens. The objectives of this research are to determine the essential parameters governing interlaminar fracture and damage of realistic laminated composites and to characterize a correlation between the critical strain energy release rates measured by interlaminar fracture and by low-velocity impact tests. The geometry and the lay-up sequence of specimens are designed to probe various conditions such as the skewness parameter, beam volume, and test fixture. The effect of interfacial ply orientations and crack propagation directions on interlaminar fracture toughness and the effect of ply orientations and thickness on impact behavior are examined. The critical strain energy release rate was calculated from the respective tests: in the interlaminar fracture test, the compliance method and linear beam theory are used; the residual energy calculated from the impact test and the total delamination area estimated by ultrasonic inspection are used in the low-velocity impact test. Results show that the critical strain energy release rate is affected mainly by ply orientations. The critical strain energy release rate measured by the low-velocity impact test lies between the mode I and mode II critical strain energy release rates obtained by the interlaminar fracture test. Submitted to the 11th International Conference on Mechanics of Composite Materials (Riga, June 11–15, 2000). Published in Mekhanika Kompozitnykh Materialov, Vol. 36, No. 2, pp. 195–214, March–April, 2000.     

Circular Delaminations - the Effect of Thermal Strains on the Strain Energy Release Rate

The analysis presented focuses on the extent to which the thermal loading resulting from a difference between the curing and service temperatures and from variations in the thermal-expansion coefficients from layer to layer can affect the growth of delaminations. Square laminate plates containing circular delaminations are examined. The reinforcement combinations for the delaminated layer and the core plate considered are [0°]/[90°], [90°]/[0°], [0°]/[±45°] _s , and [±45°] _s /[0°]. The analysis is carried out using the FEM. The strain energy release rate components are calculated using the modified crack-closure integral method. The results obtained show that, for all the reinforcement combinations studied, with the exception of [±45°] _s /[0°], a temperature drop considerably reduces all the strain energy release rate components, but only minor changes in their proportion occur. In the case of the [±45°] _s /[0°] plates, all these components increase, and noticeable changes in their proportion are also observed.