纤维增强复合材料风机叶片宏细观一体化有限元分析

为了建立纤维增强复合材料风机叶片宏观性能和细观组分的直接关联,得到一般有限元分析时无法获得的细观参量值,利用FORTRAN程序把细观力学的失效/损伤分析模块,嵌入到有限元软件ABAQUS中的USDFLD用户子程序中,建立了风机叶片宏细观一体化模型。该模型能够实现基于细观组分级损伤/失效判据的宏细观渐进损伤分析和强度预报功能。该模型计算结果与文献中的试验结果有较好的一致性。     

基于多尺度方法的三维编织C/C复合材料弯曲失效特性分析

为了预测三维编织C/C复合材料的弯曲失效行为,基于多尺度渐进展开理论,结合细观渐进损伤模型,建立了三维编织C/C复合材料宏细观多尺度分析模型。通过商业有限元软件ABAQUS用户子程序UMAT的二次开发,在宏观结构有限元分析中实时调用细观单胞模型进行细观渐进损伤分析,实现了宏细观尺度之间交互式信息传递和多尺度损伤模拟。利用上述模型对三点弯曲载荷下三维编织C/C复合材料梁的渐进损伤和失效过程进行了模拟,预测了梁的载荷-挠度曲线和弯曲强度,并与实验结果进行了对比分析,验证了基于多尺度方法的三维编织C/C复合材料弯曲强度预测模型的有效性,为此类材料及结构失效分析提供了一种手段。     

材料强度对层板抗弹性能和损伤特性的影响

根据纤维增强复合材料宏细观结构特征,基于ABAQUS软件平台,建立了层合板高速冲击损伤三维有限元分析模型。该模型在复合材料层间引入界面单元模拟层间分层,采用三维粘弹性本构,结合Hashin失效准则模拟单层板面内损伤.利用该模型,深入研究了复合材料层板的抗弹性能和损伤特性,数值分析结果与实验结果吻合良好,证明了该方法的合理有效性。通过数值分析,详细探讨了材料强度参数对层板抗弹性能和损伤特性的影响规律,获得了一些有价值的结论。     

复合材料-金属毛化接头的失效预测模型

针对复合材料与金属连接的一种新型连接形式－毛化接头,建立了其在拉伸载荷作用下的失效模式与破坏载荷的宏－细观预测模型。首先根据毛刺的分布选择合适的代表体积元,建立毛刺层单胞模型,施加周期性边界条件,通过有限元分析得到毛刺层的平均刚度参数。其次,基于累积损伤理论预测毛刺层的单胞强度,分析毛刺层的失效机理。最后,将毛刺层的等效材料参数赋予接头整体模型,预测接头的抗拉强度及失效模式。预测结果与试验值吻合良好。分析结果表明,毛化接头的承载能力和失效模式与毛刺的密度高度、搭接面积等因素密切相关,通过参数设计可获得较高的承载能力。     

风机叶片包容性分析

应用有限元方法对丢失的失效风机叶片撞击机匣的非线性瞬态响应进行了数值计算研究,模拟了叶片的包容过程,分析了包容过程中叶片、机匣的变形与能量变化。结果表明:有限元方法能较好的模拟风机叶片丢失后撞击机匣的过程,该型风机机匣对叶片具有包容性。研究结果对于进行风机叶片包容性设计具有重要参考价值。     

考虑晶体滑移面分解正应力的细观损伤模型

材料内部的解理、滑移面剥离等细观损伤是引起宏观失效的根源, 从细观尺度研究损伤的发生和发展有助于深入认识材料的变形和失效过程. 本文基于晶体塑性理论, 从滑移系的受力和变形出发研究材料的细观损伤, 建立了考虑滑移面分解正应力的细观损伤模型, 为晶体材料解理断裂的分析提供了新方法. 首先, 在晶体弹塑性变形构型的基础上引入损伤变形梯度张量的概念, 从变形运动学着手建立了考虑损伤能量耗散的本构方程, 并推导了塑性流动方程与损伤演化方程; 然后, 建立了相应的数值计算方法, 给出了应力与状态变量的更新算法, 推导了Jacobian矩阵的表达式; 接着, 以$[100]$取向的单晶铜材料为例, 通过有限元计算与试验结果的对比, 并采用粒子群优化算法标定了11个材料细观参数; 最后, 将所提细观损伤模型应用于RVE单轴拉伸过程的模拟, 得到了考虑损伤影响的应力应变曲线, 并分析了材料的塑性流动与损伤演化过程. 结果表明, 本文所提模型能够计算材料在受载过程中的损伤累积效应, 合理反映晶体材料的细观损伤机理.      

三维编织复合材料渐进损伤的非线性模型及强度分析

建立了考虑周期性位移边界条件的细观体胞模型,对三维编织复合材料的渐进损伤过程进行数值模拟。采用Eshelby-Mori—Tanaka方法计算含损伤裂纹的材料的剐度矩阵,并将有限元网格尺寸和单元裂纹尺寸引入损伤演化方程,有效地降低了模拟结果对有限元网格的依赖程度。通过计算得到了材料应力应变的非线性关系和失效时的极限强度,并分析了材料的破坏机理。结果表明,大编织角材料的破坏模式主要是基体失效与纤维横向拉剪破坏,模拟计算结果与文献中的实验值吻合较好。     

混凝土三维细观模型的建模方法与力学特性分析

根据混凝土材料的细观组成和结构特点,基于三维Voronoi图形提出了一种简单高效的混凝土细观模型生成方法,利用塑性损伤模型对该细观模型进行了单、多轴应力状态下的准静态分析以及SHPB动态有限元分析。结果表明,数值模拟得到的应力应变曲线和破坏模式与实验结果基本吻合,本文中提出的混凝土三维细观模型可较好地模拟混凝土的静、动态力学特性,为进一步从细观力学角度研究混凝土损伤演化规律和破坏机理提供了模型基础。     

基于TCK模型的非贯通节理岩体动态损伤本构模型

提出在岩体动态损伤本构模型中应同时考虑宏、细观缺陷;基于能量原理和断裂力学理论推导得出了同时考虑节理几何及力学特征的宏观损伤变量(张量)的计算公式;基于综合考虑宏、细观缺陷的复合损伤变量(张量)及完整岩石动态损伤Taylor-Chen-Kuszmaul(TCK)模型,建立了相应的单轴压缩下节理岩体动态损伤本构模型;利用该模型讨论了节理内摩擦角及节理长度对岩体动态力学特性的影响规律。研究表明,试件动态峰值强度随着节理内摩擦角的增大而增大,随着节理长度的增加而减小。     

动力损伤后的脆性岩石静力蠕变断裂模型研究

应力波动力扰动下脆性岩石的静力蠕变特性,对深部地下工程围岩变形的评价有重要的实践意义.动力载荷作用导致的局部细观裂纹损伤严重影响脆性岩石蠕变力学行为.基于细观裂纹扩展与应力关系模型、动力扰动损伤演化函数、静动力载荷演化路径函数与黏弹性本构模型,提出一种应力波动力扰动下脆性岩石蠕变断裂特性的宏细观力学模型.其中动力损伤通过控制岩石内部细观裂纹数量变化实现.模型描述了应力波动力扰动下岩石的应变时间演化曲线,解释了岩石动力扰动下蠕变失效特性.研究了不同应力波幅值及周期影响下的脆性岩石应变-时间关系曲线,并通过试验结果验证了模型的合理性.讨论了动力损伤变化形式,突变发生时刻,突变量的大小对岩石蠕变失效特性的影响.分析了应力波幅值、周期对岩石动态动力损伤效应以及蠕变失效特性的影响.主要研究结果:动力损伤的变化值越大,岩石蠕变失效发生时间越短.冲击载荷扰动期间,动力损伤发生的时刻及增加的形式,对动力扰动后的岩石应变及蠕变破坏时间影响很小.动力损伤变化量随应力波幅值增加、周期减小而加速增大.应力波幅值越大、周期越小,岩石发生蠕变失效时间越短.     

Numerical simulation of the flow field in the vicinity of an axial flow fan

The main purpose of the current investigation is the development and evaluation of a numerical model used to simulate the effect of an axial flow fan on the velocity field in the vicinity of the fan blades. The axial flow fan is modeled as an actuator disc, where the actuator disc forces are calculated using blade element theory. The calculated disc forces are expressed as sources/sinks of momentum in the Navier–Stokes equations solved by a commercially available computational fluid dynamic (CFD) code, Flo⁺⁺. The model is used to determine the fan performance characteristics of an axial flow fan as well as the velocity fields directly up‐ and downstream of the fan blades. The results are compared with experimental data. In general, good agreement is obtained between the numerical results and experimental data, although the fan power consumption, as well as radial velocity downstream of the fan blades, is underpredicted by the fan model. Copyright © 2001 John Wiley & Sons, Ltd.     

混凝土细观随机骨料结构与有限元网格剖分

在细观层次上,混凝土被认为是一种由粗骨料、水泥砂浆及二者间的粘结带所组成三相非均质复合材料。本文首先基于蒙特卡罗随机抽样原理,用“取和放”方法在计算机上产生形状、尺寸和骨料颗粒分布与真实混凝土相似的随机骨料结构,再使用有限元分析软件ANSYS对骨料区域及砂浆区域分别划分网格,并编程在骨料和砂浆之间生成三角形三结点可控制厚度粘结单元,从而使三相网格缝合为一个整体,为混凝土非线性有限元分析提供可靠的细观计算模型。最后利用建立的模型进行混凝土轴心受拉和轴心受压的仿真模拟,在细观层次研究的基础上揭示出混凝土的宏观力学性能。     

损伤统计演化方程的性质和数值模拟

通过对一种含成核尺寸效应的损伤统计演化方程性质的分析和数值模拟,揭示了损伤率主要是由微损伤在二维相空间中的前沿的运动所决定的这也就是Kachanov提出的损伤率演化方程的物理基础数值结果进一步显示了含成核尺寸效应模型在损伤发展上与-维模型的区别而且,由几种形式的细观动力学算出的损伤率与损伤的关系简单,可近似拟合为宏观上封闭的形式     

Influence of applied in-plane strain on transverse thermal conductivity of 0°/90° and plain weave ceramic matrix composites

A computationally economic finite-element-based stress analysis model, developed previously by the authors, has been extended to predict the thermal behaviour of ceramic matrix composites with strain-induced damage. The finite element analysis utilises a solid element to represent a homogenised orthotropic medium of a heterogeneous uni-directional tow. The non-linear multi-axial strain dependent thermal behaviour has been discretised by multi-linear curves, which have been implemented by a user defined subroutine, USDFLD, in the commercial finite element package, ABAQUS. The model has been used to study the performance of two CMC composites: a SiC (Nicalon) fibre-calcium aluminosilicate (CAS) matrix, 0°/90° cross-ply laminate Nicalon-CAS; and, carbon fibre-dual carbon-SiC matrix (C/C-SiC), plain weave laminate DLR-XT. The global through-thickness thermal conductivity degradation with composite uni-axial strain has been predicted. Comparisons have been made between the predictions and experimental data for both materials, and good agreement has been achieved. For the Nicalon-CAS 0°/90° cross-ply the dominant mechanism of thermal conductivity degradation is combined fibre failure and associated wake debonding; and, for the DLR-XT plain weave the same mechanisms act in combination with out-of-plane shear failure.     

碳纤维复合材料冲击模型率相关修正方法与试验研究

目前先进航空发动机的风扇叶片均采用复合材料结构,为了研究其在工作过程中可能受到的冲击损伤,即碳纤维增强树脂基复合材料受到高速冲击后的损伤与破坏过程,对其准静态下的正交各向异性本构模型和失效准则进行修正,建立了应变率相关的三维动态本构及损伤模型．该模型考虑了材料模量、强度和断裂韧性与应变率的相关性,并采用基于断裂韧性的渐进损伤模式对刚度进行折减来控制破坏过程．开展了不同应变率下的动态试验,得到基体方向拉伸与剪切的动态响应数据,拟合得到相应的动态修正因子．将该模型结合修正因子植入数值软件进行仿真计算,分析结果表明,所建立的率相关本构及损伤模型能够更准确地模拟层合板受冲击过程的损伤和破坏,与试验吻合较好．     

准脆性材料断裂过程区中的圆饼微裂纹损伤计算

准脆性工程材料及结构在外力作用下,不仅引起内部缺陷变化和微裂纹的出现及发展,且使得其结构承载能力降低或性能劣化．在其材料失效过程中常存在裂缝与断裂损伤过程区．为研究材料细观缺陷或微裂纹与宏观破坏的规律,通过细观力学方法,对于代表性体积单元RVE中的圆饼型微裂纹的尺寸与密度变化,探讨其宏观断裂过程区力学参量与损伤之间的量化关系．借助宏观断裂过程区的黏聚裂纹模型,将损伤单元RVE嵌入到宏观裂缝端部的断裂过程区中,对其进行联接细观损伤到宏观破坏的力学多尺度研究．文中也通过实验数据,对其理论计算结果进行了算例的讨论与分析．     

损伤因素对单层平面索网静力性能影响研究：有限元分析与试验验证

运用通用有限元软件ANSYS建立三维有限元模型,对横索与竖索连接节点失效、索预应力损失和锚固端失效这三种损伤因素的不同损伤工况下,单层平面索网结构的受力性能进行了非线性有限元分析,并与相应的试验结果进行了全面对比分析。结果表明：本文的有限元模型能够准确地分析计算上述三种损伤因素对单层平面索网结构受力性能的影响,包括结构...     

Modeling fracture in large scale shell structures

We consider a problem of modeling fracture and failure preceded by large scale yielding of ductile shells from the point of view of large-scale structural analysis. We place a special emphasis on the computational efficiency of the constitutive formulation. In this context, we seek the formulation embedded in the shell mechanics framework, which is both theoretically sound and easily implementable into a large-scale explicit dynamic finite element code without precluding vectorization or parallelization. This is achieved through the elasto-plastic damage constitutive model for finite-element analysis of plates and shells. The proposed damage model is purely phenomenological with a scalar damage parameter, which has no physical interpretation, except that it represents on a global scale the micromechanical changes the material undergoes during the process of necking and fracture. The localization leading to softening and fracture is represented by the damage calibration function with exponential damage growth after the onset of necking. The proposed phenomenological damage model uses a general plasticity and shell mechanics frameworks which makes it general and easily implementable into existing finite element codes. The proposed formulation has been implemented into the explicit dynamic finite element software code EPSA (Atkatsh et al., 1980, Atkatsh et al., 1983).     

A computationally efficient non-linear beam model

Aerospace structures with large aspect ratio, such as airplane wings, rotorcraft blades, wind turbine blades, and jet engine fan and compressor blades, are particularly susceptible to aeroelastic phenomena. Finite element analysis provides an effective and generalized method to model these structures; however, it is computationally expensive. Fortunately, the large aspect ratio of these structures is exploitable as these potential aeroelastically unstable structures can be modeled as cantilevered beams, drastically reducing computational time.In this paper, the non-linear equations of motion are derived for an inextensional, non-uniform cantilevered beam with a straight elastic axis. Along the elastic axis, the cross-sectional center of mass can be offset in both dimensions, and the principal bending and centroidal axes can each be rotated uniquely. The Galerkin method is used, permitting arbitrary and abrupt variations along the length that require no knowledge of the spatial derivatives of the beam properties. Additionally, these equations consistently retain all third-order non-linearities that account for flexural-flexural-torsional coupling and extend the validity of the equations for large deformations.Furthermore, linearly independent shape functions are substituted into these equations, providing an efficient method to determine the natural frequencies and mode shapes of the beam and to solve for time-varying deformation.This method is validated using finite element analysis and is extended to swept wings. Finally, the importance of retaining cubic terms, in addition to quadratic terms, for non-linear analysis is demonstrated for several examples.     

Crystallographic failure analysis of film near cooling hole under temperature gradient of nickel-based single crystal superalloys

In this paper, a unit cell model with a film cooling hole has been set up to analyze the crystallographic stress characterization and failure behavior under temperature gradient of nickel-base single crystallographic superalloys (SC). The aim of this work is to study the failure behavior of SC blades with film cooling. The distribution of cooling air pressure on the hole side surface and the distribution of the temperature around the hole are obtained from the fluid analysis. The result of the temperature distribution is then transferred to the finite element model (cell model) by the interpolation method. The cell model is analyzed by the crystallographic rate dependent finite element method (FEM). Special attention is put on the influence of temperature gradient. The influence of the loading boundaries, i.e. displacement loading and stress loading, on the stress characterization around hole is also taken into consideration. The results show that temperature gradient hole has much influence on the stress characterization. Different types of loading boundaries result in different types of stress and strain distributions. There is clear stress concentration near the hole under displacement loading, while there is clear strain concentration under stress loading. The failure characterization has been studied by the strain energy density criterion. It is shown that the temperature gradient has influence on the failure behavior.