薄壁筒仓的振动实验研究

本文设计并完成了不同地基上筒仓模型的动力试验（包括模型试验和测试方案，数据输入输出及处理）。对模型筒仓及原型筒仓分别进行了系统的有限元动力分析计算，并与试验结果进行了比较。结果表明，本文所设计的试验，试验结果及有限元计算模式是正确的。     

基于静载试验钢桁梁悬索桥承载能力评估分析

早期修建的小跨径钢桁梁悬索桥大部分已接近设计年限,正确评估其承载能力是桥梁维修、加固和技术改造的基本依据.本文首先简单介绍了桥梁承载能力评估的静载试验方法.同时结合城南大桥的实例,分析了现有桥梁结构存在的主要病害及产生的原因.在充分考虑分析现场检测资料和原有设计荷载等级的基础上,建立了考虑结构损伤的有限元模型,制定了静载试验的加载方案.通过试验结果与修正后有限元模型结果的比较,评估了桥梁结构现有承载能力状况,并针对该桥提出了恢复承载能力的加固措施和建议.     

独塔斜拉桥的环境振动试验与分析

桥梁环境振动试验具有简单方便和花费少等优点.本文以吉林市临江门大桥为工程背景,通过动力试验,研究了该桥在天然脉动荷载作用下的固有特性.采用结构分析软件ANSYS建立全桥的空间模型,计算该桥的固有特性.有限元计算结果与动力试验结果比较吻合.结果表明,环境振动响应足以识别出该桥所感兴趣的模态,可作为该桥的有限元模型修正、损伤检测、使用状态评估和健康监测的基础.     

航空发动机模拟机匣动力学模型修正研究

针对有限元建模中由于各种误差(如建模误差等)会给计算结果精度带来影响的问题,提出了一种利用模型修正来提高有限元计算结果精度的方法。首次使用了一阶优化方法,以所测试的模态频率和振型为参考,对有限元模型进行修正。首先,以某航空发动机模拟机匣为研究对象,对其进行模态测试,得到其模态频率和振型。然后,以机匣的前10阶计算模态频率与测试模态频率之间误差最小为优化目标,使用Nastran软件对各部件有限元模型中单元的弹性模量进行了修正,并计算了模型修正前后的机匣模态频率和振型,同时与测试模态频率和振型进行对比。结果表明,修正后的有限元模型计算结果与测试结果吻合良好,二者模态振型一致,模态频率的最大误差不超过1%。由此说明修正弹性模量的模型修正方法合理、可行,适用于工程上大型复杂结构的有限元准确建模。     

大跨斜拉桥结构健康监测实验室模型试验平台

本文基于山东滨州黄河公路大桥,建立面向结构健康监测的实验室模型试验平台.基于相似理论,分析模型相关参数的相似关系,确定模型缩尺比、材料和截面尺寸,并对模型附加质量和斜拉索进行合理地简化.采用ANSYS建立物理模型的三维空间实体有限元数值分析模型,实体建模能较好的体现模型局部特征和模拟损伤.模型制作采用分段整体浇注,分段之间设计连接件连接,模拟斜拉桥施工顺序进行实验室组装,基于影响矩阵法对斜拉索进行张拉成桥.建立了包括传感器系统、静动力加载系统、数据采集系统和数据处理四大部分的完整试验体系,并对隔离出的桥塔和桥面板子结构进行了静动力试验,对全桥模型进行了动力测试.子结构和全桥模型的试验结果与有限元计算结果,以及原桥实测值都吻合较好,验证了斜拉桥模型的准确性和试验平台的有效性.试验系统的建立,为结构健康监测技术提供了一个试验研究平台.     

连续曲线箱梁模型试验研究

建立一两跨连续曲线箱梁有机玻璃试验模型。二跨连续箱梁模型的跨径为45cm 45cm,分别进行了在集中荷载、均布荷载作用下的模型试验研究。垂直集中荷载采用杠杆法加载,均布荷载采用特制条形砝码搁置加载。采用YJ-25静态电阻应变仪、平衡箱,并用半桥测量,温度自补偿方法测定应变值。各种测试值均取分级荷载下读数的平均值,测量得到了沿横截面的应力、应变分布规律。用有限段法和有限元法对该模型进行了应力计算,与试验结果比较吻合较好,实验验证了理论的正确性。     

静应力作用下的层合板接头损伤失效分析

基于单层板理论,结合有限元分析技术即应力分析、Hashin三维失效判定准则、包含4种基本损伤类型相互关联作用的材料性能退化方法及结构最终破坏判据等,建立了含辅助铺层层合板接头静载损伤失效分析方法. 同时,对层合板接头损伤扩展进行了模拟分析,损伤计算结果与试验分级加载试样X光进行了对比. 通过多种类型层合板接头静强度预测结果与试验结果对比及静载累积损伤规律分析表明,建立的静载三维累积损伤分析的强度预测方法可方便模拟不同结构尺寸层合板接头内部各铺层损伤起始、发展及结构最终破坏整个累积过程,同时获得其最终破坏强度及破坏模式. 该方法的预测结果与试验结果吻合较好.      

输电钢管塔环板节点极限承载力的理论研究

以圆环-母线梁模型为基础,运用虚功原理,研究了无环板和四分之一环板节点极限承载力的计算方法,并给出了节点极限承载力的建议公式.通过将其与试验结果、有限元计算结果、日本铁塔协会的送电用钢管铁塔制作基准的计算结果进行对比,证明本文所提出的建议公式得到的结果较日本铁塔协会的送电用钢管铁塔制作基准的计算结果有所提高,并能较好地与试验和有限元计算的结果吻合,与试验结果的误差约为3%.本文可为超高压输电钢管塔节点设计和节点极限承载力确定提供参考.     

某飞机机翼颤振模型模态测试及分析

以某飞机机翼颤振缩比模型为研究对象,通过纯模态测试得到试验件前九阶模态参数。建立机翼梁架有限元模型并进行计算,得到各阶模态振型及频率。将各阶模态的计算结果与试验结果进行对比,频率的计算结果与纯模态试验值的误差均在5%以内,主要模态的振型计算结果与试验结果也基本一致,验证了有限元计算模型的准确性。在此基础上可以进行下一步的颤振分析,且试验结果可以作为机翼颤振模型风洞试验的参考依据。     

CRAS与SAP5P的联接

本文介绍随机信号及振动分析系统CRAS与结构有限元计算程序SAP5P的连接方法.试验数据与计算数据在微机内的拼接,实现了模态试验结果与计算模型的相互校核与修正,给结构的动力分析提供了可靠的依据,是复杂、高技术产品的CAD/CAT一体化的一个重要手段.     

Exact and numerical responses of a plate under a turbulent boundary layer excitation

The aim of this paper is the analysis of the predictive capabilities of the deterministic methodologies when facing the problem of a plate excited by a stochastic pressure distribution due to a turbulent boundary layer (TBL). A full analytical solution has been assembled by considering a simply supported rectangular plate wetted on one side by a TBL. This reference exact solution, developed by using a standard separable variable model, has been used as test case for comparing the approximate solutions coming from the adoption of a numerical scheme by using discrete coordinates. The numerical algorithm has been built by using a standard finite element modal approach. The approximations introduced are thoroughly discussed and analysed; they refer to the meshing condition and the transformation of the distributed stochastic load. The application of a novel numerical procedure named as Asymptotical Scaled Modal Analysis is presented too. This innovative numerical scheme allows the analysis of the structural response of a generic plane operator in the whole frequency range, which is not always amenable by exact solutions; further and equally important, it is associated to a reduction of the computational cost. The work demonstrates that some numerical advances in the prediction of the random structural responses are feasible still using standard finite element modal inputs, without increasing the computational costs.     

多层吸能元件在冲击波作用下大变形问题的模态解

通过实验研究了多层吸能元件在冲击波作用下的大变形模式,基于虚速度原理建立了问题的模态近似解。实例计算表明理论值与实验结果吻合很好,分析了硬化、动态应变率以及元件静态孙载力,层数和惯性对结果的影响。     

Determination of sensor positions for predictive maintenance of revolving machines

The monitoring by measurement and analysis of vibration is largely used to detect the defects in revolving machines. The determination of the best sensor positions is one of the main research goals in the field of predictive maintenance. This paper proposes a numerical methodology based on a finite element model and a spectral analysis in order to find optimum sensor positions. The bearing is a key component for the vibration propagation from the moving parts to static ones. An analytical bearing model and its numerical implementation in a finite element code are presented. The tangent stiffness matrix of the bearing element is obtained by the Newton–Raphson method and then used for the modal and spectral analyses. Several techniques are used to find the most sensitive zones to common defects. The proposed numerical approach correlate well with the experimental results. The numerical modeling of a grinder shows the interests in industrial applications.     

Monitoring structural damage of components using an effective modulus approach

This paper describes a novel nondestructive damage detection method that was developed to study the influence of a crack on the dynamic properties of a cantilever beam subjected to bending. Experimental measurements of transfer functions for the cracked cantilever beam revealed a change in the natural frequency with increasing crack length. A finite element model of a cracked element was created to compute the influence of severity and location of damage on the structural stiffness. The proposed model is based on the response of the cracked beam element under a static load. The change in beam deflection as a result of the crack is used to calculate the reduction in the global component stiffness. The reduction of the beam stiffness is then used to determine its dynamic response employing a modal analysis computational model. Euler–Bernoulli and Timoshenko beam theories are used to quantify the elastic stiffness matrix of a finite element. The transfer functions from both theories compare well with the experimental results. The experimental and computational natural frequencies decreased with increasing crack length. Furthermore the Euler–Bernoulli and Timoshenko beam theories resulted in approximately the same decrease in the natural frequency with increasing crack length as experimentally measured.     

Identification of dynamic properties of plate-like structures by using a continuum model

The common approach currently used in the aircraft structural analysis is the finite element method. NASA's research in computational structures technology (CST) is helping to develop the finite element analysis to a new stage, although the significant limitations still exist. The elements used in the finite element method are usually void of dynamics. The consequence is that hundreds and thousands of elements are needed to represent large flexible aircraft structures in order to acquire analytical accuracy. To avoid the large dimensionality the current practice is to reduce the order of the model for structural system identification and control synthesis. This approximation, however, can lead to system instability due to the dynamics which are ignored.In contrast, distributed parameter modeling seems to offer a viable alternative to the finite element approach for modeling large flexible aerospace structures. Distributed parameter models have the advantage of improved accuracy, reduced number of modal parameters, and the avoidance of modal order reduction. Most of the effort on the continuum modeling so far is contributed to the beam-like structures which are composed of beams, tethers and rigid bodies. For the aircraft structural analysis, however, another important type of structural elements is plate. The principle of the monocoque or semi-monocoque type of aircraft construction is fundamentally the use of a thin-walled tube to carry compression, tension, shear, and bending. It is necessary, therefore, to expand the continuum modeling methodology to the plate-like structures to satisfy the requirement in the aircraft structural analysis, especially for the monocoque structures.This paper has developed a continuum modeling algorithm for the identification of dynamic properties of plate-like structures. A closed-form solution of the Timoshenko plate equation consistent with the maximum likelihood estimator has been derived. The closed-form expressions of the gradient functions have thereby been resulted from the solution of the partial differential equation. The proposed distributed parameter model involves far fewer unknown parameters than independent modal characteristics for finite element models. Illustration of this approach is given by a computer simulation which shows that the estimated results by using continuum model are reasonably accurate compared with the theoretical results.     

基于静力残余力向量的结构损伤评估方法

残余力向量法是一类常用的损伤识别方法,现有的残余力向量法都是基于动力测试的模态参数,和动力测试数据相比,静力测试数据往往精度更高,且无需模态分析等复杂操作.鉴于此,本文提出一种静力残余力向量法用于结构损伤评估.所提方法利用静力测试位移数据,并结合结构有限元模型的刚度矩阵,定义了静力残余力向量,根据该向量中不为零的元素来判断损伤自由度,再根据自由度和单元之间的对应关系来确定发生损伤的位置,并进一步提出一种求解损伤参数的代数解法.另外,针对实践中角位移难以测量的情况,进一步提出了一种静力缩聚残余力向量法,拓宽了所提方法的应用范围.以桁架结构和梁结构模型为例对所提方法进行了验证,数值算例结果说明所提方法合理有效.     

结构动力模型修正方法的比较研究及评估

在实际工程中,由结构动力模型得到的计算值与通过试验获得的测量值间往往存在偏差,为了能够精确预测结构的动力响应,依据测量信息修正存在的动力模型是非常必要的.对现有几种有效的用于结构动力模型修正的理论方法(包括基于敏感性分析的矩阵型法、基于神经网络算法的参数型法和基于遗传优化算法的方法)做了详细的综述;介绍了这些方法的步骤和研究进展;并分析了这些动力模型修正方法在工程运用中存在的一些实际问题,如不完整的模态测量值、模型修正的鲁棒性、模型修正的计算效率和收敛性等.最后,通过对一实际的五层钢框架的动力模型修正,比较了这几种方法的优缺点,提出了今后需要解决的问题.      

基于POD和代理模型的静气动弹性分析方法

静气动弹性问题考虑弹性结构与定常气动力间的相互耦合作用,对飞行器的性能和安全具有显著的影响.在现代飞行器设计阶段,计算流体力学(CFD)/计算结构力学(CSD)直接耦合方法是精确考察静气动弹性影响的重要手段.然而,基于CFD技术的气动力仿真手段在耦合过程中计算量大且耗时长,难以满足设计阶段的需求.因此,为了兼顾计算精度与效率,文章采用本征正交分解(POD)和Kriging代理模型相结合的模型降阶方法,替代CFD求解过程并耦合有限元分析(FEA)方法,建立了高效、准确的静气动弹性分析框架.相较于传统的以模态法为主的静气动弹性分析方法,该方法能够解决更为复杂的静气动弹性问题以及提供静气动弹性变形过程中的气动分布载荷.针对典型三维跨声速HIRENASD机翼模型开展的马赫数、迎角变化的算例验证表明:由建立的静气动弹性分析方法与CFD/CSD直接耦合方法计算得到机翼翼梢处的静变形量间的相对误差在5%以内;同时该方法预测静平衡位置处的气动分布载荷的误差在5%以内,静气动弹性分析的计算效率至少提升了6倍.     

Super element approach to cable passing through multiple pulleys

A parametric super element model for cable passing through multiple pulleys is presented in this study for the static analysis of structures. The amounts of cable passages over pulleys are introduced as additional degrees-of-freedoms in the finite element model and the relationship between cable tensions at the two sides of each pulley is imposed based on the friction law or empirical data. The proposed finite element model is firstly verified by a simple pulley cable system and then applied to the analysis of real complex engineering structures. The verification results satisfy the static equilibrium and deformation compatibility conditions of the structural system and basic engineering principles. With the application of the proposed super element model, the global deformation and stress distribution for structures with multiple-pulley cable systems can be effectively and accurately computed. Numerical results for structural analysis show that the effect of friction of pulleys on the cable tensions is significant and the friction-free and fixed models both give unrealistic and incorrect results in cable tensions in some cases.