四种陶瓷材料与SUS304不锈钢的高温摩擦学特性研究

为了探索陶瓷与金属组合作为高温润滑材料的可能性，利用端面摩擦磨损试验机测定了４种陶瓷ＳｉＣ、Ｓｉ３Ｎ４、Ａｌ２Ｏ３和ＺｒＯ２与ＳＵＳ３０４不锈钢在室温至５００℃下的摩擦学性能．摩擦试验结果表明，ＳｉＣ、Ｓｉ３Ｎ４和Ａｌ２Ｏ３在低于２００℃时的摩擦系数稳定且都低于０．２，但在２００℃以上时的摩擦性能却都不稳定，摩擦系数在０．２－０．４之间；ＺｒＯ２在２００℃以下时的摩擦性能不稳定，而在２００℃以上时的摩擦系数低于６．２且较稳定。磨损试验结果表明，在４种陶瓷中ＺｒＯ２的磨损率最低［－２．６０×１０－９ｍｍ３／（Ｎ·ｍ）］，ＳｉＣ和Ｓｉ３Ｎ４的磨损率居中［分别为１．８０×１０－６ｍｍ３／（Ｎ·ｍ）和４．４０×１０－６ｍｍ３／（Ｎ·ｍ）］，Ａｌ２Ｏ３的磨损率最高［３．６４×１０－５ｍｍ３／（Ｎ·ｍ）］；分别与这４种陶瓷对磨的不锈钢的磨损率都高［１．４０×１０－５－４．５２×１０－５ｍｍ３／（Ｎ·ｍ）］．     

计及界面损伤的复合材料正交(混杂)叠层板的应力集中分析

对正交(混杂)叠层复合材料最终拉伸破坏过程中的细观应力集中问题,提出了一种修正的剪滞分析模型;研究了叠层中由于90°层的基体开裂、层间界面破坏、0°层中部分纤维断裂及纤维/基体界面损伤相互作用所导致的细观应力重新分布,获得了相应的应力集中因子和界面破坏区长度与界面剪切强度的定量关系。本文结果为进一步研究正交叠层复合材料的细观破坏机理、最终拉伸强度及协同效应等提供了重要的理论依据。     

双晶铝晶界驰豫起始温度的滞弹性测量

测量了夹角分别为１０°和５０．５°的［１１０］对称倾侧铝双晶晶界的扭转滞弹性蠕变曲线，得到了晶界的弛豫强度约在０．４２Ｔ＿ｍ温度时变为零（Ｔ＿ｍ为铝的熔点温度），进一步肯定了晶界的内部结构在这个温度的附近发生了显著的变化。同时，采用“晶界附近位错亚结构连续分布与晶界原子的交互工作用模型”，对双晶晶界的驰豫机制做了合理地解释。     

环氧树脂－SiO_2空心微球复合材料的Mie－GrUneisen方程

本文描述了三种不同密度（０．６，０．７６和０．９ｇ／ｃｍ￣３）的环氧树脂－ＳｉＯ＿２空心微球复合材料的Ｈｕｇｏｎｉｏｔ关系。讨论了上述材料以其相应的Ｈｕｇｏｎｉｏｔ关系作为参考方程的Ｍｉｅ－Ｇｒｕｎｅｉｓｅｎ方程，并与Ｐ－α模型进行了比较，结果相当一致。由此得出结论，在本文研究的压力范围内，Ｍｉｅ－Ｇｒｕｎｅｉｓｅｎ方程可应用于上述孔隙材料。     

环氧树脂－SiO_2空心微球复合材料的Mie－GrUneisen方程

本文描述了三种不同密度（０．６，０．７６和０．９ｇ／ｃｍ￣３）的环氧树脂－ＳｉＯ＿２空心微球复合材料的Ｈｕｇｏｎｉｏｔ关系。讨论了上述材料以其相应的Ｈｕｇｏｎｉｏｔ关系作为参考方程的Ｍｉｅ－Ｇｒｕｎｅｉｓｅｎ方程，并与Ｐ－α模型进行了比较，结果相当一致。由此得出结论，在本文研究的压力范围内，Ｍｉｅ－Ｇｒｕｎｅｉｓｅｎ方程可应用于上述孔隙材料。     

固体火药的着火特性研究──激光点火实验

利用１０．６ｍ　ＣＯ＿２激光作热源，在常压下对不同的固体火药［黑火药，１１／７，６／７松樟（５％）（表面经松香障脑处理）及６／７松石（表面经松香石墨处理）］进行了点火试验，研究了发射药，特别是阻燃药的看火性能。实验中采用光电二极管和热电偶测量点火延迟时间及火药表面温度变化，结果令人满意。     

几种等离子喷涂陶瓷涂层之固体粒子冲蚀磨损的特性与数学模型

研究了几种等离子喷涂陶瓷（Ａｌ＿２Ｏ＿３、Ａｌ＿２Ｏ＿３－ＴｉＯ＿２、Ｃｒ＿２Ｏ＿３和ＺｒＯ＿２）涂层的固体粒子冲蚀磨损特性及其冲蚀磨损机理，同时根据冲蚀磨损表面形貌特征的扫描电子显微镜观察，并且从准静态压印断裂分析入手，提出了这类陶瓷涂层在固体粒子于较低速度和较小角度冲击下的冲蚀磨损数学模型（试验选用的粒子冲击速度有３０ｍ／ｓ和７０ｍ／ｓ的两种，冲击角度为３０°）．研究结果表明，固体粒子冲击压印断裂－层状剥落是这类陶瓷涂层的主要冲蚀磨损机理。根据所提出的模型得到涂层的体积冲蚀磨损率Ｅｖ与其硬度ＨＶ呈反比关系（即Ｅｖ∝ＨＶ－１），这与试验结果相符；由该模型推导出涂层的Ｅｖ之速度指数ｎ＝２．１，这与试验结果基本相符。按照这种模型，对于固体粒子以较低速度和较小角度冲击的情况，高硬度的陶瓷涂层具有较高的冲蚀磨损抗力；通过改善陶瓷涂层的断裂韧性，可以有效地提高其在正向冲击时的冲蚀磨损抗力。     

考虑楼板变形的超高层建筑结构计算

应用计算功能与ＡＤＩＮＡ相当的ＭＦＥＰＶ４．０微机程序［５］，在４８６ＰＣ微机上用子结构方法装配了大量的壳元和梁元，建立了目前世界上最高的有八千多个结点组成的线性的钢筋混凝土试验塔（塔高１２０ｍ共３２层）三维有限元计算模型，并进行了相应风载、预应力载荷、自重载荷下的静态应力分析。该模型较全面、真实地反映了该试验塔的几何形状，考虑了内外所有剪力墙和预应力墙及其墙上的门孔和几乎所有窗孔，考虑了每一层楼板的变形，满足相应规范［２］对结构计算的有关规定。风载的计算结果对结构设计有一定的校核作用。最后，讨论了用该模型［１］在微机上完成所有载荷组合计算的可行性。     

割口单向叠层板的拉伸应力集中与强度

基于剪滞理论,建立一种分层剪滞模型,分析了含割口的单向叠层板在拉伸载荷作用下的应力重新分布问题,获得了割口前缘完整纤维的应力集中因子.在此基础上,采用细观统计破坏理论,研究了割口单向叠层板的拉伸破坏强度,得到了与现有实验较吻合的结果.     

开孔复合材料层合板强度不确定性分析

以拉伸载荷作用下AS4/3501-6开孔复合材料层合板为研究对象，采用考虑复合材料层合板就地强度效应的有限断裂力学模型和基于方差的敏感性测度分析模型相结合的方法，研究单层板宏观力学性能不确定性对具有不同孔径和铺层顺序的开孔复合材料层合板破坏强度的影响．研究结果表明：单层板力学性能对开孔板强度影响程度的大小与孔径相关，但敏感性排序与孔径无关．同时，单层板力学性能敏感性测度与层合板铺层顺序有关，层合板各向异性比越大，开孔板拉伸破坏受单层板纤维方向拉伸强度的影响越大，而且开孔板拉伸强度与单层板纤维方向拉伸强度呈正相关，与横向弹性模量呈负相关，与面内剪切模量和纵向弹性模量不具有单调关系．     

Dynamic compressive behavior of thick composite materials

The effect of strain rate on the compressive behavior of thick carbon/epoxy composite materials was investigated. Falling weight impact and split Hopkinson pressure bar systems were developed for dynamic characterization of composite materials in compression at strain rates up to 2000 s^–1. Strain rates below 10 s^–1 were generated using a servohydraulic testing machine. Strain rates between 10 s^–1 and 500 s^–1 were generated using the drop tower apparatus. Strain rates above 500 s^–1 were generated using the split Hopkinson pressure bar. Unidirectional carbon/epoxy laminates (IM6G/3501-6) loaded in the longitudinal and transverse directions, and cross-ply laminates were characterized. The 90-deg properties, which are governed by the matrix, show an increase in modulus and strength over the static values but no significant change in ultimate strain. The 0-deg and cross-ply laminates show higher strength and ultimte strain values as the strain rate increases, whereas the modulus increnases only slightly over the static value. The increase in strength and ultimate strain observed may be related to the shear behavior of the composite and the change in failure modes. In all cases, the dynamic stress-strain curves stiffen as the strain rate increases. The stiffening is lowest in the longitudinal direction and highest in the transverse direction.     

大开口复合材料层合板强度破坏研究

复合材料层合板的各向异性及非均质,使得复合材料层合板内部的破坏形式非常复杂.在复合材料结构的设计中,为满足制造及使用功能上的需求,在复合材料层合板承力结构件上不可避免地需要设计各种开口.然而,含大开口复合材料层合板的强度破坏问题变得更为复杂,使得现有的强度理论面临新的挑战.针对碳纤维增强复合材料大开口层合板受单向拉伸载荷作用下的强度破坏问题进行了数值分析和实验研究.首先,根据Hashin准则和刚度退化模型,对含不同圆形开口尺寸的[0]_(10)单向铺层、[0/90]_5和[±45]_5正交铺层的层合板,进行了单向拉伸载荷作用下渐进失效的数值模拟分析,获得了对应结构的极限载荷和破坏模式.在此基础上,采用数字图像相关方法,进行复合材料大开口层合板强度破坏的实验研究.研究结果表明,大开口复合材料层合板在单向拉伸加载下主要呈现脆性破坏形式,破坏起始位置处于应力集中区.此外,破坏强度和失效模式与复合材料铺层方式和开口尺寸大小密切相关.其中[±45]_5铺层的开口层合板承载能力最弱,分层破坏最严重.开口尺寸越大,结构的极限载荷值越低.同实验测试结果相比,数值模拟对复合材料层合板的损伤失效分析略显不足,往往很难全面分析复合材料层合板破坏失效过程中的各种因素的影响.     

Behavior of Pin-loaded Laminated Composites

In this study, an investigation was carried out to determine the effects of joint geometry and fiber orientation on the failure strength and failure mode in a pinned joint laminated composite plate. Behavior of pin-loaded laminated composites with different stacking sequence and different dimensions has been observed experimentally. E/glass–epoxy composites were manufactured to fabricate the specimens. Mechanical properties of the composites were characterized under tension, compression and in-plane shear in static loading conditions. Laminated composites were loaded through pins. Single-hole pin-loaded specimens were tested for their tensile response and width-to-hole diameter (W/D) and edge distance-to-hole diameter (E/D) ratios evaluated. A series of experiments was performed with six different material configurations ([0/±45]_s–[90/±45]_s, [0/90/0]_s–[90/0/90]_s and [90/0]_2s–[±45]_2s), in all, over 120 specimens. E/D ratios and W/D ratios of plates were changed from 1 to 5 and 2 to 5, respectively. Failure propagation and failure type were observed on the specimens. The influence of the joint geometry on the strength of the pin-loaded composites was assessed. When laminated composite plates were loaded to final failure, three basic failure modes consisting of net-tension, shear out and bearing failure were observed for the different geometric dimensions. All the connections tested showed that the fiber orientations have a definite influence on the position around hole circumference at which failure initiated. Net-tension failure occurred for specimens that had small width and large end distance. When the width was increased, the specimens which had small end distances failed in the shear-out modes. When the end distance was increased, bearing failure developed in addition to shear-out failure. The experimental results showed that the ultimate load capacities of E/glass–epoxy laminate plates with pin connection were increased by increasing W and E. However, increasing the E/D and W/D ratios beyond a critical value has an insignificant effect on the ultimate load capacity of the connection.     

Experimental and analytical comparisons of failure in thermoplastic composite laminates

Failure characteristics of Gr/PEEK were studied, using an experimental investigation and a fully nonlinear ply-by-ply finite-element technique. The stacking sequence of the laminates (with centrally located holes) investigated were: 0, 90, ±45 deg, (0/45/90/−45 deg)_2s and (0±45/90 deg)_2s. The [0 deg] laminate failure was characterized by splitting at the extremities of the hole and along the fibers. The [90 deg] laminates failed in the transverse direction, whereas the [±45 deg] laminates exhibited considerable elongation to failure. In the case of the quasi-isotropic laminates, the failure progression appeared to be due dominantly to matrix cracking followed by fiber failure. Analytical predictions of the failure process showed reasonably good correlation with the experimentally determined data.     

An experimental investigation on the tensile moduli and strengths of graphite/epoxy laminates

The results of a series of tensile tests on graphite/epoxy [0°]_8S and [0°/±30°/0°]_2S laminates at rates varying from 0.002 in/min to 2 in./min are reported. The loads are applied at various angles to the fiber directions in each case. The rate-dependent behavior of the stress-strain response is assessed. Evidence is presented to indicate that failure first occurs on inner plies. Also, evidence is presented to indicate that, in some cases, moduli increase with increased stress or strain level. Lamination theory is used to predict moduli and comparisons with experiment are given. This theory is also used in conjunction with three failure theories to predict ultimate strengths with varying degrees of success. Further, two approaches to ply unloading after first-ply failure are used and discussed. One is a standard method found in the literature while the other is a proposed ‘strength-of-materials’ type of technique which is computationally much simpler.     

Effects of material and stacking sequence on behavior of composite plates with holes

Strain distributions to failure, tensile and compressive strain-concentration factors, and strength-reduction factors were determined for glass-, boron-, and graphite-epoxy plates with holes loaded in tension. Strain gages, photoelastic coatings and moiré techniques were used. Ten variations of layup and stacking sequence were studied. The boron-epoxy composite was found to be the stiffest and strongest of the three. The graphite laminate with the highest stress concentration and the most linear strain response exhibited the highest strength-reduction factor. In all cases, the maximum strain at failure on the hole boundary was higher than the ultimate tensile-coupon strain. In general, it was found that, the higher the stress-concentration factor, the higher the strength-reduction factor. Thus, the [0/90/0/90]_s layup with a stress-concentration factor of 4.82 had a strength-reduction factor of 3.18. At the other extreme, the most flexible layup [±45/±45]_s with the lowest stress-concentration factor of 2.06 had the lowest strength-reduction factor of 1.10. Stacking sequences associated with the tensile interlaminar normal stress or high interlaminar shear stress near the boundary, resulted in laminates 10 to 20 percent weaker than corresponding alternate stacking sequences. Furthermore, it was found that stacking-sequence variations can alter the mode of failure from catastrophic to noncatastrophic.     

Pseudo-molecular dynamics study of grain boundary segregation

The segregation of bismuth atoms on the [101] tilt copper grain boundaries Σ3 ( ) 70.53°, Σ33 ( ) 58.99°, Σ11 ( ) 50.48° and Σ9 ( ) 38.94° has been studied by pseudo-molecular dynamics using the empiricalN-body potentials. The relationship between bismuth segregation and grain boundary structure has been discussed in detail. The subject supported by the Chinese Academy of Sciences and National Natural Science Foundation of China     

碳纤维增强树脂基复合材料压缩失效机理研究

为分析基体性质和纤维铺设方式对碳纤维树脂基复合材料(CFRP)压缩性能的影响,设计两种基体（耐高温环氧树脂基体和PA6 基体） 和两种碳纤维铺设方式[[45/0/-45/90]s和[45/-45]2s],共4 类盒型碳纤维试件．采用轴向压缩实验,研究低应变速率下碳纤维复合材料的极限载荷、压缩量和刚度等力学性能．研究表明试件的失效形式主要由基体性质决定,损伤区域及裂纹方向主要由碳纤维铺设方式决定．利用X射线显微镜(XRM)对试件典型的损伤区域进行三维扫描,并对扫描图像进行重构与渲染,获得破坏区域的内部损伤细节．根据损伤扫描结果,得到材料内部的损伤类型及破坏程度．归纳所获得的损伤测试特征,分析不同类型试件压缩时的损伤规律与失效机理．     

Behavior of graphite/epoxy plates with holes under biaxial loading

An experimental investigation was conducted to study the behavior under biaxial tensile loading of quasiisotropic graphite/epoxy plates with circular holes and to determine the influence of hole diameter on failure. The specimens were 40 cm×40 cm (16 in.×16 in.) laminates of [0/±45/90] _s layup. Four hole diameters, 2.54 cm (1.00 in.), 1.91 cm (0.75 in.), 1.27 cm (0.50 in.) and 0.64 cm (0.25 in.), were investigated. Deformations and strains were measured using strain gages and birefringent coatings. Equal biaxial loading was introduced by means fo four whiffle-tree grip linkages and controlled with a servohyraulic system. Initially, the circumferential strain is uniform around the boundary of the hole. Subsequently, with increasing load, regions of high strain concentration with nonlinear response develop at eight characteristic locations 22.5 deg off the fiber axes. Failure in the form of cracking and delamination initiates at these points. Maximum strains at failure on the hole boundary reach values up to twice the ultimate strain of the unnotched laminate. The effect of hole diameter on strength was described satisfactorily using an average biaxial-stress criterion. Good correlation was also obtained with theoretical predictions based on a tensor-polynomial failure criterion for the lamina and a progressive degradation model.     

TEMPERATURE EFFECT ON LOW-CYCLE FATIGUE BEHAVIOR OF NICKEL-BASED SINGLE CRYSTALLINE SUPERALLOY

The low-cycle fatigue （LCF） behavior of a nickel-based single crystal superalloy with [001] orientation was studied at an intermediate temperature of T0℃ and a higher temperature of To ＋ 250℃ under a constant low strain rate of 10^-3 s^-1 in ambient atmosphere. The superalloy exhibited cyclic tension-compression asymmetry which is dependent on the temperature and applied strain amplitude. Analysis on the fracture surfaces showed that the surface and subsurface casting micropores were the major crack initiation sites. Interior Ta-rich carbides were frequently observed in all specimens. Two distinct types of fracture were suggested by fractogaphy. One type was characterized by Mode-I cracking with a microscopically rough surface at To ＋ 250℃. Whereas the other type at lower temperature T0℃ favored either one or several of the octahedral {111} planes, in contrast to the normal Mode-I growth mode typically observed at low loading frequencies （several Hz）. The failure mechanisms for two cracking modes are shearing of γ＇ precipitates together with the matrix at T0℃ and cracking confined in the matrix and the γ/γ＇interface at To - 250℃.