宏纤维压电层合壳结构非线性屈曲分析

以纤维压电MFC （Micro-Fiber Composite）层合圆柱壳为例,研究了其在准静态屈曲下的非线性振动响应。基于Reissner-Mindlin一阶剪切变形假设,采用大转角几何全非线性理论,建立了带有纤维角度的MFC层合壳结构的非线性屈曲与振动分析模型。采用全拉格朗日方程（Total Lagrange Formulation）对非线性模型进行线性化处理,并结合Riks-Wempner弦长控制迭代法进行准静态求解,然后在每个解点进行自由振动分析。通过与文献数据对比验证了所建模型的准确性。并用该计算模型对MFC-d31层合圆柱壳进行屈曲及自由振动分析,研究了几何参数（曲率、厚度、纤维角度和不同外加电压）对频率的影响。结果表明,厚度、曲率和纤维增强角度对结构的临界载荷有显著的影响,且结构的临界载荷随着上述参数的增大而增大;电场强度可对不同纤维角度壳体的自振频率进行调节,能够提高结构的临界载荷;纤维角度越大,电压对结构自振频率调节的效果越明显。     

智能材料MFC驱动双稳态板的跳变特性研究

智能可变形结构能感知周围环境的变化并做出适当的反应,其主要原理是利用智能材料层产生应变以达到驱动主体结构发生变形。含有智能材料压电纤维MFC的双稳态复合材料层合板可以通过智能驱动实时调整主体结构的形状,实现稳态构型之间的跳变。本文对中心点固支的MFC压电智能驱动双稳态复合材料层合板的稳态构型、跳变规律及其影响因素进行了系统地研究。研究内容主要包括：含MFC的双稳态层合板的稳态构型、分叉行为和驱动跳变分析。利用理论模型分析了层合板的长宽比、厚度尺寸、铺层方式和MFC粘贴位置对双稳态板分叉行为的影响,并预测了双稳态层合板的临界尺寸以及驱动跳变的临界电压。双稳态板的跳变是一个大变形的非线性行为,实现和控制跳变行为的研究是其应用的基础。本文的研究结果为新型压电材料驱动双稳态板的结构设计提供了一定的理论参考。     

智能柔性悬臂梁的动力学建模研究

对带有压电陶瓷作动器和传感器的平面智能柔性梁进行了有限元动力学建模。采用Euler-Bernoulli梁模型,在考虑平面梁压电效应的基础上,考虑了大变形和非线性变形,进行了有限元离散;基于Lagrange方程建立了带压电元件的智能柔性悬臂梁的电-结构耦合动力学有限元精确模型,并将本文模型和一般不考虑压电元件质量和电势能模型的仿真结果进行了对比,结果表明:两种模型得到的一阶固有频率最大相差31.8%,响应振幅也有较大的差异。因此,在工程动力学建模中,不能忽略压电元件的质量和电势能。本文所建立的电-结构耦合动力学模型能更加精确地反映实际应用中智能柔性悬臂梁的动力学特性。     

含间隙铰接的柔性航天器刚柔耦合动力学与控制研究

大型柔性航天器展开锁定后,运动副中仍存在大量无法消除的间隙. 铰链间隙直接影响柔性航天器的姿态 运动和有效载荷的指向精度及稳定度,会对航天器的动力学特性造成较大的影响. 针对这一问题, 提出一种含间隙铰 接的航天器刚柔耦合动力学建模与控制方法. 首先建立含间隙的铰链精确动力学模型,从而构建含间隙铰接的柔性结构 动力学模型. 然后利用哈密顿原理和模态离散方法,建立含间隙铰接柔性航天器离散形式的刚柔耦合非线性动力学 模型,采用 Newmark 算法对非线性动力学方程进行求解. 基于压电纤维复合材料 (macro fiber composite, MFC) 驱动器 构建航天器的刚-柔-电耦合动力学方程,采用最优控制设计控制律. 分析了铰链参数、中心刚体转动惯量、间隙尺寸和间隙数目对航天器动力学特性的影响,着重研究了铰链间隙对航天器姿态运动和结构振动的影响作用. 最后采用 MFC 驱动器对航天器施加主动控制. 结果表明,铰链参数和中心刚体转动惯量影响航天器的固有频率;随着铰链间隙尺寸的增大及间隙数目的增多,航天器的整体刚度逐渐减小,而航天器的姿态角和振动位移响应不断增大;通过基于 MFC 的主动控制,能够实现含间隙铰接航天器姿态运动与结构振动的协同控制,并缓解间隙对系统动态特性造成的影响.      

基于MFC的结构静态形状控制研究

宏纤维复合材料MFC(Macro Fiber Composite)具有体积小、主动控制适用性强、作动效果好等特点。本文开展了宏纤维复合材料MFC对结构静态形状主动控制研究。建立了悬臂梁结构有限元模型,并采用载荷比拟法计算得到了MFC压电作动器的驱动载荷。基于数值分析结果,搭建了悬臂梁结构主动控制实验平台,分析了不同加载电压下的悬臂梁的弯曲变形效果,进而分析MFC结构在静态形状控制中的力学性能。数值仿真和实验结果表明:在不同的静态电压加载下,结构的变形和加载电压近似呈线性关系;仿真和实验结果对比中呈现出较好的一致性,其最大位移误差为12.45%。最后讨论了MFC压电作动器自身时间蠕变特性对静态变形控制实验结果产生的影响,结果表明在大电压作用下MFC材料存在蠕变效应,在实际使用过程中需要关注。本文采用以悬臂梁为载体的实验和仿真研究方法对在其他横观各向同性材料的压电材料力学性能分析具有普遍适用性。     

智能压电结构的新型阻尼修正模型

针对智能压电结构中，结构和压电材料之间的耦合和压电材料的动态输出，对结构阻尼的影响，提出了一种新的分段阻尼模型。由于压电结构和系统之间的耦合效应，整个结构的刚度和阻尼都会发生变化，尤其是阻尼会发生动态的变化。静态阻尼模型的描述已不能满足描述需要，而文中的分段阻尼模型能更精确地描述智能压电结构中的阻尼，以及系统的动态响应。以悬臂梁为例，实验结果验证了原静态阻尼模型的误差较大，而新模型比原模型精确反映了系统的幅频相应，比原模型更加合理和准确。     

层状压电智能梁板结构的形状最优控制研究

基于压电层合结构的有限元方程,采用零阶逼近优化和一阶梯度优化算法,运用ANSYS/APDL语言,编制了力-电耦合有限元优化分析程序.运用该程序,对一单压电片和多压电片埋置的三层梁和一压电片粘贴于结构表面的三层板进行建模,以结构的几何尺寸或驱动电压为设计变量,实现梁板结构的单点和多点形状最优控制设计.对比两种优化方法的计算结果,吻合良好,验证了程序的有效性.本文的计算理论和方法可以为复杂压电层合智能结构的主被动控制设计提供参考.     

旋转功能梯度智能结构的刚-柔耦合动力学分析

基于一次耦合模型理论建立了中心刚体-压电层-功能梯度材料智能梁系统的刚柔耦合动力学模型．研究了开环状态下将压电材料作为传感器的压电效应和质量刚度效应对系统动力学特性的影响．通过仿真算例与另两种不同建模理论（传统零次近似耦合模型、一次近似耦合模型）作了对比．随着中心刚体外驱动力矩的增大,零次近似耦合模型和一次近似耦合模型计算结果逐渐发散,而本文的一次耦合模型的计算结果始终保持收敛,较其他近似耦合模型具有一定优势．对三种不同的结构的计算结果表明,压电材料的压电效应对系统的动力学特性影响显著,压电材料的质量刚度效应也会影响智能梁的动力学行为,前者比后者的影响大得多．此外,功能梯度材料功能梯度指数对系统动力学特性的影响也较大．     

压电智能结构模糊自学习控制(FSLC)

将模糊逻辑与学习控制的基本思想相结合,根据控制系统的动态输出特性,采用模糊控制对学习控制律中的参数进行实时校正,实现系统的动态学习过程,提出了一种适用于压电智能结构振动控制的模糊自学控制方法FSLC（FuzzySelf-LearningContr01）。分别采用三维8节点实体单元（Solid45）和耦合单元模拟主结构和压电致动器／传感器,基于ANSYS参数化语言编写了压电智能结构振动控制分析的有限元程序。通过数值仿真证明了模糊自学习控制方法能有效控制压电结构的振动,并提高了自学习控制的收敛速度和获得了很好的控制效果。     

低速冲击下压电层合板的非线性动力响应与疲劳损伤寿命分析

基于损伤力学,考虑压电效应、几何非线性和损伤演化的影响,建立了集中载荷作用下压电层合板的非线性运动微分方程,考虑撞击物与压电层合板之间的弹性接触效应,确定了层合板所承受的冲击力.对此非线性动力问题,采用有限差分法进行求解,且引入损伤层合板单元模型,采用有限元方法模拟了冲击荷载作用下压电层合板的损伤演化.算例中,讨论了撞击物的冲击速度、压电材料以及损伤对压电层合板非线性动力响应的影响,以及周期冲击荷载下冲击速度和压电材料对压电层合板疲劳损伤寿命的影响.     

扁壳结构弯曲与扭转振动控制试验研究

扁壳结构的弯曲与扭转振动控制对该类结构的应用具有重要意义。本文采用不影响壳体结构的粗压电纤维复合材料(MFC)作动器对其弯曲与扭转振动进行主动控制。建立局部表面粘贴MFC作动器的开口圆柱扁壳的动力学解析模型,得到了作动力和作动力矩的解析表达式,分析了扁壳结构上MFC作动器在弯曲与扭转振动控制中的作动机理。针对一开口碳纤维圆柱扁壳,设计了模糊PD控制器,开展了定频与随机激励下壳体弯曲与扭转振动控制试验,并与传统PD控制试验效果进行了对比。结果表明:MFC作动器在壳体弯曲和扭转振动控制方面作动能力突出;模糊PD控制器的控制效果优于传统PD控制器的控制效果。     

Nonlinear vibration of a rotating laminated composite circular cylindrical shell: traveling wave vibration

In this paper, the large-amplitude (geometrically nonlinear) vibrations of rotating, laminated composite circular cylindrical shells subjected to radial harmonic excitation in the neighborhood of the lowest resonances are investigated. Nonlinearities due to large-amplitude shell motion are considered using the Donnell’s nonlinear shallow-shell theory, with account taken of the effect of viscous structure damping. The dynamic Young’s modulus which varies with vibrational frequency of the laminated composite shell is considered. An improved nonlinear model, which needs not to introduce the Airy stress function, is employed to study the nonlinear forced vibrations of the present shells. The system is discretized by Galerkin’s method while a model involving two degrees of freedom, allowing for the traveling wave response of the shell, is adopted. The method of harmonic balance is applied to study the forced vibration responses of the two-degrees-of-freedom system. The stability of analytical steady-state solutions is analyzed. Results obtained with analytical method are compared with numerical simulation. The agreement between them bespeaks the validity of the method developed in this paper. The effects of rotating speed and some other parameters on the nonlinear dynamic response of the system are also investigated.     

Corotational nonlinear analyses of laminated shell structures using a 4-node quadrilateral flat shell element with drilling stiffness

A new 4-node quadrilateral flat shell element is developed for geometrically nonlinear analyses of thin and moderately thick laminated shell structures. The fiat shell element is constructed by combining a quadrilateral area co- ordinate method （QAC） based membrane element AGQ6- II, and a Timoshenko beam function （TBF） method based shear deformable plate bending element ARS-Q12. In order to model folded plates and connect with beam elements, the drilling stiffness is added to the element stiffness matrix based on the mixed variational principle. The transverse shear rigidity matrix, based on the first-order shear deformation theory （FSDT）, for the laminated composite plate is evaluated using the transverse equilibrium conditions, while the shear correction factors are not needed. The conventional TBF methods are also modified to efficiently calculate the element stiffness for laminate. The new shell element is extended to large deflection and post-buckling analyses of isotropic and laminated composite shells based on the element independent corotational formulation. Numerical re- sults show that the present shell element has an excellent numerical performance for the test examples, and is applicable to stiffened plates.     

Dynamic analysis of a rotating rigid-flexible coupled smart structure with large deformations

Based on Hamilton's principle,a new kind of fully coupled nonlinear dynamic model for a rotating rigid-flexible smart structure with a tip mass is proposed.The geometrically nonlinear effects of the axial,transverse displacement and rotation angle are considered by means of the first-order approximation coupling(FOAC)model theory, in which large deformations and the centrifugal stiffening effects are considered.Three kinds of systems are established respectively,which are a structure without piezoelectric layer,with piezoelectric layer in open circuit and closed circuit.Several simulations based on simplified models are presented to show the differences in characteristics between structures with and without the tip mass,between smart beams in closed and open circuit, and between the centrifugal effects in high speed rotating state or not.The last simulation calculates the dynamic response of the structure subjected to external electrical loading.     

Nonlinear active control of damaged piezoelectric smart laminated plates and damage detection

Considering mass and stiffness of piezoelectric layers and damage effects of composite layers, nonlinear dynamic equations of damaged piezoelectric smart laminated plates are derived. The derivation is based on the Hamilton＇s principle, the higher- order shear deformation plate theory, von Karman type geometrically nonlinear straindisplacement relations, and the strain energy equivalence theory. A negative velocity feedback control algorithm coupling the direct and converse piezoelectric effects is used to realize the active control and damage detection with a closed control loop. Simply supported rectangular laminated plates with immovable edges are used in numerical computation. Influence of the piezoelectric layers＇ location on the vibration control is in- vestigated. In addition, effects of the degree and location of damage on the sensor output voltage are discussed. A method for damage detection is introduced.     

Geometrically nonlinear vibration of laminated composite cylindrical thin shells with non-continuous elastic boundary conditions

The geometrically nonlinear forced vibration response of non-continuous elastic-supported laminated composite thin cylindrical shells is investigated in this paper. Two kinds of non-continuous elastic supports are simulated by using artificial springs, which are point and arc constraints, respectively. By using a set of Chebyshev polynomials as the admissible displacement function, the nonlinear differential equation of motion of the shell subjected to periodic radial point loading is obtained through the Lagrange equations, in which the geometric nonlinearity is considered by using Donnell’s nonlinear shell theory. Then, these equations are solved by using the numerical method to obtain nonlinear amplitude–frequency response curves. The numerical results illustrate the effects of spring stiffness and constraint range on the nonlinear forced vibration of points-supported and arcs-supported laminated composite cylindrical shells. The results reveal that the geometric nonlinearity of the shell can be changed by adjusting the values of support stiffness and distribution areas of support, and the values of circumferential and radial stiffness have a more significant influence on amplitude–frequency response than the axial and torsional stiffness.

     

复合材料层合板壳的非线性热动态响应分析

本文基于高阶剪切变形理论，考虑同天应变和横向剪切应变的影响，对受热复合材料层合板壳的非线性热动态响应进行分析，计及了转动惯量的影响，给出了通用性较好的Ｃ＾０类有限元公式，文中数值算同现有文献和三维有限元计算结果进行了比较，证明了本文方法的精确、有效性，文中还就层合板的边界条件、纵厚比及铺设角度对非线性热动态响应的影响进行了分析。     

Buckling and Postbuckling of Laminated Thin Cylindrical Shells under Hygrothermal Environments

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Nonlinear Dynamics of Shells: Theory,Finite Element Formulation,and Integration Schemes

The paper is concerned with a dynamical formulation of a recently established shell theory capable to catch finite deformations and falls within the class of geometrically exact shell theories. A basic aspect is the design of time integration schemes which preserve specific features of the continuous system such as conservation of momentum, angular momentum, and energy when the applied forces allow to. The integration method differs from the one recently proposed by Simo and Tarnow in being applicable without modifications to shell formulations with linear as well as nonlinear configuration spaces and in being independent of the nonlinearities involved in the strain-displacement relations. A finite element formulation is presented and various examples of nonlinear shell dynamics including large overall and chaotic motions are considered.