增强型Reddy层合梁理论与热应力分析

为推广Reddy理论准确分析复合材料层合/夹层结构的热变形和应力, 通过使用横法向热变形和自由表面条件, 发展了增强型Reddy层合梁理论。虽然考虑了横法向应变, 增强型Reddy理论位移变量数与Reddy理论相同。用虚功原理推导了复合材料层合梁平衡方程, 并分析了简支复合材料层合/夹层梁热膨胀问题。数值结果表明, 增强型Reddy理论能准确分析复合材料层合/夹层结构热膨胀问题, 而Reddy理论分析热膨胀问题误差较大。     

织物增强复合材料梁结构热校形工艺

本文借鉴金属零件热校形工艺的经验,利用复合材料在高温下的应力松弛现象,通过热校形工艺修正复合材料零件的形状。制造了碳纤维平纹织物/环氧复合材料L形梁、C形梁,通过自制的热校形模具,以实验方法研究热校形时间、热校形载荷对零件形状的影响,分析复合材料热校形工艺的可行性。研究表明,复合材料热校形工艺中零件变形的主要原因是零件在高温下发生应力松弛,其他因素可以忽略;热校形载荷、热校形时间都对热校形工艺的效果有重要影响。针对特定的复合材料结构,采用合理的热校形工艺过程能够有效地控制构件形状,方便零件的装配。     

复合材料梁的几何精确非线性建模及非经典效应

基于Hodges的广义Timoshenko梁理论对具有任意剖面形状、任意材料分布及大变形的复合材料梁进行几何精确非线性建模,采用旋转张量分解法计算梁内任意一点的应变,采用变分渐近法确定梁剖面的任意翘曲,采用平衡方程由二次渐近精确的应变能导出广义Timoshenko应变能,采用广义Hamilton原理建立梁的几何精确非线性运动方程。将所建模型用于复合材料梁的静动力分析,通过与实验数据的对比,验证了建模方法的准确性,并进一步研究了剖面翘曲及横向剪切变形非经典效应对复合材料梁的影响。研究表明,剖面翘曲对复合材料梁的静变形和固有频率有显著影响,横向剪切变形对复合材料梁的静变形和固有频率的影响与梁的长度/剖面高度比有关。     

共固化阻尼薄膜夹嵌复合材料梁的振动分析EI北大核心CSCD

为研究共固化阻尼薄膜夹嵌复合材料固支梁的自由振动特性。将1阶剪切变形理论、变分原理和Hamilton原理相结合,建立了共固化阻尼薄膜复合材料梁自由振动的理论模型,提出使用伽辽金法求解该模型在固支边界条件下的自由振动理论解。通过构建有限元模型、制作阻尼薄膜夹嵌复合材料梁试件与所搭建的试验平台,分别将理论解与模拟结果、试验结果进行对比,验证了理论模型的有效性;最后,进一步探究了阻尼层在复合材料中的分布以及结构几何参数对阻尼薄膜夹嵌复合材料梁动力学性能影响的规律,为阻尼薄膜复合材料梁结构的优化设计提供理论依据。     

基于本征方程求解复合材料梁几何非线性静力平衡

对基于本征梁理论求解复合材料梁的几何非线性大变形屈曲问题进行了研究,根据材料属性利用渐近变分法确定复合材料梁的刚度矩阵,再根据本构方程和平衡方程求得其静力学行为,结果表明：对单层铺层的复合材料梁来说,刚度矩阵的耦合项可以忽略,其变形构型及梁末端的位移及转角的变化趋势与各项同性材料相同;对一个一般的复合材料梁来说,其刚度矩阵的耦合项不可忽略,耦合项对位移和转角的影响与施加在梁上的载荷大小有关,在载荷小于30N,以耦合项50%的变化量为界,当变化量小于50%时,位移和转角的变化趋势与初始时相同,当变化量大于50%时,位移和转角的变化趋势发生很大的改变,但与解耦后的变化趋势相似。     

大变形薄壁复合材料旋转梁静动态特性分析

该文研究了大变形薄壁复合材料旋转梁的静、动态特性以及复合材料旋转梁不同铺层角、转速对固有频率的影响变化规律。在梁截面上设立翘曲节点引入翘曲变形,假设应变沿薄壁厚度呈二次曲线形式变化;由Hamilton原理,推导了复合材料梁的大变形公式;建立了考虑剪切、翘曲薄壁复合材料大变形梁静、动态分析的有限元模型,并编写了相应的计算程序。分析了复合材料薄壁梁大变形状态下的静态变形行为;在旋转状态下,考虑哥氏力影响,不同转速、不同铺层角对复合材料梁动态特性的影响。计算结果表明:能够用该文建立的模型计算复合材料梁的静动态特性,与相关文献计算结果进行比较,说明了模型的优越性。     

热成形钢防撞梁性能研究

目的研究热成形钢防撞梁的性能及其影响因素。方法使用准静态三点弯曲试验和高速落锤试验,对比了热成形钢防撞梁和传统冷冲压防撞梁的静态承载能力及动态抗冲击吸能性能,使用极差分析方法,分析了各个影响因素的显著水平及最优数据。结果热成形防撞梁的最大变形抗力是传统冷冲压防撞梁的2~3倍,吸能效果是其1.5~2.5倍。热成形工艺参数中,变形温度对热成形钢防撞梁性能的影响最大,其次是加热温度,再其次是保温时间。结论热成形钢防撞梁性能优异,在保证驾乘人员安全的同时,可以实现汽车减重、降低油耗、减少二氧化碳排放。为保证热成形钢防撞梁的性能,在热成形工艺过程中最需要注意的是变形温度。     

复合材料机翼结构热校形工艺实验及数值模拟

纤维增强树脂基复合材料机翼结构复杂,往往存在明显的固化变形现象,严重影响机翼的装配和气动特性。本研究目的在于建立大型复合材料复杂结构的热校形工艺方法,解决复合材料机翼制造的变形控制问题。针对复合材料机翼的固化变形特点,设计了新的热校形夹具工装。在评价复合材料应力松弛特性的基础上,建立了大型复合材料机翼结构热校形工艺的有限元模拟方法,实现了对热校形后机翼结构残余变形的有效预报,分析了校形载荷、校形温度等关键工艺参数对校形效果的影响规律,形成优化的热校形工艺方案。模拟及实验结果表明,复合材料热校形工艺可以适用于大型复杂结构,复合材料机翼89.5%的固化变形被热校形工艺的残余变形抵消,达到机翼的装配和气动外形要求。      

穿孔纤维增强阻尼复合材料梁的振动分析

为了研究嵌入式共固化穿孔纤维增强阻尼复合材料梁在简支边界条件下的动力学性能，依据1阶剪切变形理论、Hamilton原理和Navier解形式，建立并求解了共固化穿孔阻尼复合材料梁的自由振动理论模型。制作穿孔阻尼复合材料梁试件并搭建试验平台，运用软件ANSYS数值模拟和软件MATLAB理论仿真分析方法验证了该理论模型和方法的有效性，并用验证的理论模型和方法分别研究了设计参数对嵌入式共固化穿孔纤维增强阻尼复合材料梁动力学性能的影响规律。该模型和方法对嵌入式共固化非连续阻尼复合材料结构的研究提供理论依据，为结构的设计与制造提供了参考。     

热载荷作用下嵌入SMA丝复合材料梁的横向自由振动

基于形状记忆合金Brinson一维热力学本构方程,采用复合材料细观力学分析方法,建立了热载荷作用下嵌入SMA丝复合材料梁的一维热弹性本构关系。其次利用Euler-Bernoulli梁的轴线可伸长几何非线性理论和自由振动理论,建立了嵌入SMA丝复合材料梁在均匀升温场内自由振动的动力学控制方程,导出了热过屈曲构形附近嵌入SMA丝复合材料梁微幅横向自由振动的模型。最后通过打靶法求解了两端固定约束条件下嵌入形状记忆合金丝复合材料梁在加热过程中的振动响应,获得了梁的前四阶固有频率在不同SMA相对体积含量时随温度变化的特征关系曲线。数值结果表明,SMA丝相变过程中的回复应力和弹性模量变化对梁在过屈曲前后的各阶固有频率均有影响,是实现梁自振频率主动控制的一种有效方法。     

Finite element analysis of thermal stresses for laminated composites in terms of a new C0-type Reddy's theory

This article proposed an accurate C⁰-type Reddy's theory including effects of the transverse normal thermal strain to study the thermal behaviors of laminated composite plates. Although transverse normal thermal strain was taken into account, displacement variables are not increased as thermal loads can be included in the generalized force vector. Based on the proposed model, an eight-node quadrilateral isoparametric element is presented, in which the interelement C⁰ continuity conditions are satisfied. Numerical results show that the proposed model can produce accurate responses of laminated composite plates under temperature loads.     

压电作动器对热变形层合板形状修复研究

基于一阶剪切效应Mindlin板理论,建立了在热载下含分布式压电作动器的复合材料层合板有限元分析模型和控制方程,分别研究了该板在内外表面存在温差的情况下的热变形,以及使用压电作动器对热变形区域进行形状修复的问题;在分析中考虑了压电作动器与复合材料层合板间含有胶接层的影响。由典型算例结果讨论,得到如下结论:1)使用压电作动器可以有效地对复合材料层合板的表面热变形形状进行修复;2)压电作动器的分布位置对修复效果影响很大;3)在电压达到一定数值后,继续增加电压值对修复效果贡献很小。     

Interlaminar shear stresses in laminated composite plates under thermal and mechanical loading

The combined effects of thermal and mechanical loadings on the distribution of interlaminar shear stresses in composite laminated thin and moderately thick composite plates are investigated numerically using the commercially available software package MSC NASTRAN/PATRAN. The validity of the present finite element analysis is demonstrated by comparing the interlaminar shear stresses evaluated using the experimental measurement. Various parametric studies are also performed to investigate the effect of stacking sequences, length to thickness ratio, and boundary conditions on the interlaminar shear stresses with identical mechanical and thermal loadings. It is observed that the effect of thermal environment on the interlaminar shear stresses in carbon-epoxy fiber-reinforced composite laminated plates are much higher in asymmetric cross-ply laminate and anti-symmetric laminate compared to symmetric cross-ply laminate and unidirectional laminate under identical loadings and boundary conditions.     

Thermal dynamic stability of parametrically excited laminated composite plates with temperature-dependent properties

Thermal dynamic stability analysis is performed on periodically-loaded laminated composite plates with temperature-dependent properties. The periodic load is taken to be a combination of periodic axial and bending stress. A set of differential equations of Mathieu–Hill type is formed to determine the dynamic instability regions based on Bolotin's method. The thermal dynamic instability of laminate plates with respective temperature-dependent and temperature-independent properties is examined. The effects of various parameters on the instability region and dynamic instability index are also discussed. The results show that the temperature-dependent properties have a significant influence on the thermal dynamic behavior of laminated plates.     

Thermal postbuckling analysis of laminated composite plates by the finite element method

The thermal postbuckling behavior of composite laminated plates subjected to a nonuniform temperature field is investigated by the finite element method. Based on the principle of minimum potential energy, the nonlinear stiffness matrix and geometry matrix are derived. The assumed displacement state over the middle surface of the plate element is expressed as a product of one-dimensional, first-order Hermitian polynomials. An iterative method is employed to determine the thermal postbuckling load. The results of the computations reveal that the thermal postbuckling behavior of composite laminated plates is influenced by lamination angle, plate aspect ratio, modulus ratio and the number of layers.     

受热复合材料层合板的非线性热振动——Part Ι: 理论及数值分析

基于能综合考虑温度效应以及横向线应变和剪切应变的高阶计算模型, 研究受热复合材料层合板的非线性热振动, 推导了非线性有限元方程并给出了相应的数值分析方法, 通过数值算例与已有文献相比较, 证明了本文理论和算法的精确有效性。文中还以大量数值算例研究了温度效应对幅频曲线的影响。     

受热复合材料层合板的非线性热振动——Part:理论及数值分析

基于能综合考虑温度效应以及横向线应变和剪切应变的高阶计算模型 ,研究受热复合材料层合板的非线性热振动 ,推导了非线性有限元方程并给出了相应的数值分析方法 ,通过数值算例与已有文献相比较 ,证明了本文理论和算法的精确有效性。文中还以大量数值算例研究了温度效应对幅频曲线的影响。     

Thermomechanical buckling of hybrid cross-ply laminated rectangular plates

A thermomechanical buckling analysis is presented for simply supported rectangular symmetric cross-ply laminated composite plates that are integrated with surface-mounted piezoelectric actuators and are subjected to the combined action of in-plane compressive edge loads, two types of thermal loads, and constant applied actuator voltage. The formulation of equations is based on the classical laminated plate theory and the von-Karman non-linear kinematic relations. The analysis uses an exact method to obtain closed-form solutions for the buckling load. The effects of applied actuator voltage, thermal and mechanical loads, plate geometry, and lay-up configuration of the laminated plates are investigated. The novelty of the present work is to obtain closed-form solutions for electro-thermomechanical buckling of hybrid composite plates, and to cover non-uniform temperature distribution loading. The results for various states are verified with known data in the literature.     

Material characterization of laminated composite plates via static testing

A minimization method for material characterization of laminated composite plates using static test results is presented. Mechanical responses such as strains and displacements are measured from the static tests of the laminated composite plates. The finite element method is used to analyse the deformation of the laminated composite plates. An error function is established to measure the differences between the experimental and theoretical mechanical responses of the laminated composite plates. The identification of the material elastic constants of the laminated composite plates is formulated as a constrained minimization problem in which the elastic constants are determined by making the error function a global minimum. A number of examples are given to illustrate the feasibility and applications of the proposed method.