四边简支双曲率蜂窝夹层薄壳自由振动分析

基于Reddy三阶剪切理论,研究了四边简支双曲率蜂窝夹层薄壳的自由振动,以及结构参数对蜂窝夹层薄壳固有频率的影响.将由六边形胞元组成的蜂窝芯层等效为一正交异性层,其等效弹性参数由修正后的Gibson公式得到,应用Reddy三阶剪切理论和Hamilton变分原理推导出四边简支条件下双曲率蜂窝夹层薄壳的频率方程.具体算例表明,采用Reddy三阶剪切理论计算的固有频率精度较高;双曲率蜂窝夹层薄壳的曲率、厚度比及胞元角度对蜂窝夹层壳固有频率有不同程度的影响,其中蜂窝夹层薄壳的固有频率随曲率的增大而增大,随厚度比的增大呈波动变化,随胞元角度的增大而减小.     

四边固支铝基蜂窝夹层板弯曲自由振动分析

基于经典叠层板理论, 将铝基蜂窝芯层等效为一正交异性层, 等效弹性参数由修正后的Gibson公式得出, 对四边固支薄蜂窝夹层板弯曲振动的固有频率进行了理论推导, 研究了蜂窝夹层板厚度、 芯层板厚度对蜂窝夹层板固有频率的影响。同时利用有限元软件计算了相应参数下的固有频率。计算结果表明, 经典叠层板理论可以较准确的计算四边固支蜂窝夹层板的固有频率。      

对边简支负泊松比蜂窝夹层板的弯曲自由振动

负泊松比蜂窝夹层板作为一种特殊的复合材料结构,目前对其动态行为尚缺乏认识。应用Reddy剪切板理论分析了对边简支负泊松比蜂窝夹层板的弯曲振动。将内凹六边形胞元的蜂窝芯层等效为一正交异性层,芯层的等效弹性参数由修正后的Gibson公式得出。由具体算例可知经典叠层板理论和一阶剪切板理论不适合用于蜂窝夹层板的振动分析。应用Reddy剪切板理论研究了蜂窝夹层板板厚比、芯层板厚及胞元角度对弯曲振动频率的影响,并绘出相应的曲线图。结果表明:对于对边简支负泊松比蜂窝夹层板,当板厚比小于某一值时,固有频率参数随板厚比的增加而增加;但当板厚比大于该值时,固有频率参数随板厚比的增加呈现复杂的变化形式。本文得到的结果为蜂窝夹层板的设计和实际应用提供了理论依据和数值参考。      

基于高阶剪切理论的复合材料格栅夹层板弯曲特性

基于高阶剪切弯曲理论,对含有软质芯材的复合材料格栅夹层板的弯曲特性进行了理论研究。基于能量法,推导了含有软质芯材的复合材料格栅的等效弹性参数计算式;基于高阶剪切弯曲理论,推导了夹层板的弯曲平衡微分方程,并采用Navier方法,给出了分布载荷作用下四边简支、上下表层为对称正交铺层的夹层板弯曲问题的理论解;用算例对典型格栅夹层板的理论解和有限元仿真解进行了对比,两者误差为7.1%,验证了本文理论方法的正确性;并分析了夹层板跨厚比、格栅厚度、格栅复合材料铺层角度、格栅间距等参量对含有软质芯材的典型复合材料格栅夹层板弯曲挠度的影响规律。      

简支边界条件下超椭圆蜂窝夹芯板的自由振动

基于Reddy三阶剪切板理论,将铝基蜂窝芯层等效为一正交异性层,等效弹性参数由修正后的Gibson公式得出,对简支边界条件下超椭圆蜂窝夹芯板弯曲振动的固有频率进行了理论推导,应用具体算例与实验值和有限元计算结果进行了验证,结果表明本文方法具有较高的计算精度。研究了板宽、板厚和芯层胞元结构参数对简支边界条件下超椭圆蜂窝夹芯板固有频率的影响,并绘出相应的曲线图,该曲线图对超椭圆蜂窝夹芯板的工程应用具有指导意义。     

随从力作用下功能梯度矩形板的非线性振动

本文研究了切向均布随从力作用下简支FGM矩形板的非线性振动问题。按照材料组份体积分数的简单幂率分布规律,FGM板的材料常数仅沿厚度连续变化。由大挠度的von Karman理论建立了以应力函数和挠度函数表示的运动偏微分方程组,再由Galerkin法转化成非线性常微分方程。对随从力作用下的四边简支陶瓷/金属矩形板,讨论了随从力、梯度指标和边长比对板的动力特性的影响,得到了各种条件下板中心振幅与非线性基频的关系。     

四边固支对称蜂窝夹层板主共振非线性动力学计算

应用同伦分析方法(HAM)研究了四边固支对称蜂窝夹层板主共振情况下的非线性动力学特性。将铝基蜂窝芯层等效为一正交异性层, 等效弹性参数由修正后的Gibson方程得出。基于经典叠层板理论(CPT)和几何大变形理论建立了四边固支蜂窝夹层板受横向激振力作用下的受迫振动微分方程, 通过振型正交化将蜂窝夹层板受迫振动微分方程简化成双模态下的动力学控制方程, 得到了主共振情况下的平均方程, 研究了不同结构参数对动力学特性的影响。计算结果表明, 蜂窝夹层板的幅频特性曲线类似单自由度Duffing方程响应曲线, 随着结构参数的增大, 硬特性明显加大并且振幅的峰值明显减小, 所得结论可为蜂窝夹层板的设计和实际应用提供理论依据。     

热环境下混凝土矩形薄板在弹性地基上的振动

基于刚性板的小挠度理论，考虑混凝土的材料非线性，推导了双参数弹性地基上混凝土矩形薄板热弹性问题的动力方程。采用级数法，导出了热环境下双参数弹性地基上四边简支混凝土矩形薄板的固有频率计算公式和强迫振动下的挠度函数。为便于工程应用，给出了双参数弹性地基上四边简支混凝土矩形薄板在恒向变温和温度均匀变化时的固有频率和均布荷载作用下的挠度函数。针对Winlder弹性地基的情况，讨论了板的材料弹性常数、几何尺寸（长宽比）、相对厚度、刚度系数k和温度对薄板固有频率和挠度函数的影响，从而为工程结构中热环境下弹性地基上混凝土矩形薄板的振动计算提供了理论依据。     

不同边界条件下波纹夹芯板的自由振动特性

波纹夹芯板作为一种特殊的复合材料结构,边界条件对其振动特性有重要影响。根据不同剪切方式下的剪切变形理论和基尔霍夫经典板理论(CLPT),利用Hamilton原理建立波纹夹芯板的动力学方程。其中,波纹芯层等效成各向异性均质体。根据四边简支、四边固支、对边简支和固支、一边固支三边简支的边界条件,推导出位移形式的偏微分动力学方程。求解得到波纹夹芯板在不同边界条件下自由振动的固有频率,与有限元仿真结果进行对比,验证了理论结果的正确性。在此基础上,基于指数剪切变形理论(ESDT),分析了不同边界条件下波纹夹芯板的基频随材料参数和结构几何参数的变化规律。结果表明,材料和几何参数对不同边界条件下波纹夹芯板的振动特性有重要影响。相关研究结果将对波纹夹芯板在工程应用中的减振设计及优化分析提供一定的理论依据。      

四边固支功能梯度矩形板的主共振分析

针对四边固支约束的陶瓷-金属材料功能梯度矩形板,在给出非均匀材料的应力应变关系及非线性几何方程基础上,应用虚功原理导出了横向简谐激励力作用下功能梯度板的非线性振动偏微分方程。通过位移函数的设定,利用伽辽金积分法推得了相应的达芬型非线性振动方程。应用多尺度法对非线性系统的主共振问题进行解析求解,得到了稳态运动下的幅频响应方程。基于李雅普诺夫稳定性理论,得到了共振下解的稳定性判别条件。作为算例,给出了不同参数下功能梯度矩形板共振的幅频曲线图和动相平面相轨迹图,讨论了不同参数对系统非线性振动特性的影响     

Geometrically nonlinear free vibrations of the symmetric rectangular honeycomb sandwich panels with simply supported boundaries

Geometrically nonlinear free vibrations of symmetric rectangular honeycomb sandwich panels with simply supported boundaries at the four edges are investigated using the homotopy analysis method (HAM). The honeycomb core of hexagonal cells is modeled as a thick layer of orthotropic material whose parameters of physical and mechanical properties are calculated by the corrected Gibson’s formula. The basic formulation of nonlinear free vibrations has been developed based on the third-order shear deformation plate theory and the nonlinear strain–displacement relation. The equilibrium equations have been obtained using Hamilton’s principle. Effects of axial half-waves, height and height ratio on the nonlinear free vibration response have been investigated for honeycomb sandwich panels.     

Geometrically nonlinear forced vibrations of the symmetric honeycomb sandwich panels affected by the water

Geometrically nonlinear forced vibrations of the symmetric rectangular honeycomb sandwich panels with the four edges simply supported and one surface affected by the water are investigated in this paper using the homotopy analysis method (HAM). The honeycomb core of hexagonal cells is modeled as a thick layer of orthotropic material whose physical and mechanical properties are determined using the Gibson correlations. The effect of water acting on honeycomb panels can be described as added mass, additional damping and additional stiffness coefficients which are obtained by the semi-analytical fluid pressures. The basic formulation of nonlinear forced vibrations has been developed base on the third-order shear deformation plate theory and Green Lagrange nonlinear strain–displacement relation. The equilibrium equations have been obtained using the Hamilton’s principle. Effects of water velocity, height and height ratio on the nonlinear forced vibration response have been studied for the honeycomb sandwich panels.     

Geometrically nonlinear forced vibrations of the symmetric rectangular honeycomb sandwich panels with completed clamped supported boundaries

Geometrically nonlinear forced vibrations of symmetric rectangular honeycomb sandwich panels with clamped supported boundaries at the four edges are investigated using the homotopy analysis method (HAM). The honeycomb core of hexagonal cells is modeled as a thick layer of orthotropic material whose parameters of physical and mechanical properties are calculated by the corrected Gibson’s formula. The basic formulation of nonlinear forced vibrations has been developed based on the classical plate theory (CPT) and the nonlinear strain–displacement relation. The equilibrium equations have been obtained using Hamilton’s principle. Effects of axial half-waves, height and height ratio on the nonlinear free vibration response have been investigated for honeycomb sandwich panels.     

四边简支新型类方形蜂窝夹层结构振动特性研究

新型类方形蜂窝是六边形蜂窝的一种过渡形式,对其等效弹性参数和振动特性的研究具有重要意义。采用改进的Gibson公式对比分析了双壁厚与等壁厚类方形蜂窝夹芯的面内等效弹性参数的差异,并应用经典层合板理论分析了不同等效弹性参数下2种壁厚类型的四边简支类方形蜂窝夹层结构的振动特性,基于有限元仿真技术分析了不同壁厚类方形蜂窝夹层结构的振动特性,并与理论分析结果进行对比。结果表明等效弹性参数的数值模拟结果与理论值基本吻合。在蜂窝基本结构参数相同的条件下,双壁厚类方形蜂窝夹芯的面内等效剪切模量、面外刚度和等效密度均比等壁厚类方形蜂窝夹芯大;在低阶振动模态下,双壁厚类方形蜂窝夹层结构的固有频率比等壁厚类方形蜂窝夹层结构的低,在高阶振动模态下,双壁厚类方形蜂窝夹层结构的固有频率比等壁厚类方形蜂窝夹层结构的高;影响夹层结构固有频率的3个主要因素所占权重由大到小依次为蜂窝夹芯yoz面等效剪切模量、蜂窝夹芯等效密度,蜂窝夹芯壁厚。研究结果表明采用经典层结构理论计算得到类方形蜂窝夹层结构的固有频率与数值仿真结果的一致性较好,这进一步证明了采用改进Gibson公式得到的类方形蜂窝夹芯等效弹性参数的正确性,同时证明了将该振动理论运用到一般蜂窝夹层结构研究的可行性,为扩展研究其他类型蜂窝夹层结构振动特性奠定了基础。     

Sound transmission loss characteristics of unbounded orthotropic sandwich panels in bending vibration considering transverse shear deformation

A theoretical study on the sound transmission loss (STL) characteristics of unbounded orthotropic sandwich panels considering the transverse shear deformation is presented. With the transverse shear deformation taken into account, the governing equation of bending vibration for unbounded orthotropic sandwich panels is derived and implemented to the sound transmission problem. The expressions for impedance and transmission coefficient are also derived. The accuracy of the theoretical predictions is checked against available experimental data. The influence of several key parameters on the sound insulation properties of the orthotropic sandwich panel is then systematically studied, including shear rigidity of the core, face sheet thickness, and core thickness. Numerical analysis shows that shear rigidity has evident effect on coincidence critical frequency and STL property, and should not be neglected when predicting STL. Increasing face sheet thickness can move coincidence critical frequency to lower frequency region and improve STL, which is much more effective than increasing the core thickness.     

Compressive and shear buckling analysis of metal matrix composite sandwich panels under different thermal environments

Combined inplane compressive and shear buckling analysis was conducted on flat rectangular sandwich panels using the Rayleigh-Ritz minium energy method with a consideration of transverse shear effect of the sandwich core. The sandwich panels were fabricated with titanium honeycomb core and laminated metal matrix composite face sheets. The results show that slightly slender (along the unidirectional compressive loading axis) rectangular sandwich panels have the most desirable stiffness-to-weight ratios for aerospace structural applications; the degradation of buckling strength sandwich panels with rising temperature is faster in shear than in compression; and the fiber orientation of the face sheets for optimum combined-load buckling strength of sandwich panels is a strong function of both loading condition and panel aspect ratio. Under the same specific weight and panel aspect ratio, a sandwich panel with metal matrix composite face sheets has a much higher buckling strength than one having monolithic face sheets.