水下爆炸载荷作用下环肋加筋圆柱壳结构的弹塑性动力屈曲

为研究水下爆炸载荷作用下潜艇结构的动力屈曲现象,以潜艇耐压结构的简化模型环肋加筋圆 柱壳结构为研究对象,建立流固耦合有限元分析模型,应用瞬态有限元分析程序MSC.Dytran对该结构在水 下爆炸冲击载荷作用下的弹塑性动力屈曲行为进行研究,基于Budiansky-Roth准则和Southwell方法确定环 肋加筋圆柱壳结构的临界屈曲载荷,讨论结构动力屈曲的影响因素如载荷强度、网格密度、径厚比、长径比、加 筋截面间距、加筋尺寸等对环肋加筋圆柱壳结构动屈曲模态和临界屈曲载荷的影响。结果表明:采用建立的 流固耦合有限元分析模型,应用动力瞬态有限元软件MSC.Dytran可以对加筋圆柱壳结构的动力屈曲行为进 行模拟,模型网格尺寸大小、结构几何参数对结构的动力屈曲临界载荷都有一定的影响,其中加筋圆柱壳结构 的径厚比对结构的动力屈曲临界载荷影响最为显著。     

中厚夹层圆柱扁壳的屈曲分析

基于一阶剪切变形中厚圆柱壳理论,考虑夹心层的面内刚度,根据中厚夹层圆柱扁壳的几何方程、本构关系、平衡方程,建立了中厚夹层圆柱扁壳小挠度屈曲的微分方程;应用广义傅里叶级数解法,得到了四边简支条件下中厚夹层圆柱扁壳屈曲的临界荷载表达式。该表达式可以退化为硬夹心夹层板的表达式,表明本文推导过程的正确性。本文还讨论了夹心层的弹性模量和泊松比以及中厚夹心圆柱扁壳的长宽比和厚度对扁壳屈曲荷载的影响。结果表明:临界荷载与夹心层的弹性模量和泊松比成正比,与扁壳的长宽比和厚度成反比。     

TiNi合金圆柱薄壳静压屈曲失稳特性的实验研究

对马氏体相变支配的伪弹性TiNi合金圆柱薄壳进行了准静态屈曲实验研究和分析,结果表明,TiNi柱壳的屈曲模态以非轴对称钻石型为主,卸载时可恢复,与马氏体相变和相变铰的行为相关,明显不同于传统弹塑性柱壳。还讨论了长径比和边界条件对屈曲模态、比能、临界失稳阈值等的影响。研究发现：随着长径比和边界条件的变化,TiNi圆柱薄壳呈现出多样化的屈曲模态发展。相同长径比下,两端简支的TiNi圆柱薄壳比能Se较大;随着长径比增大,边界条件的影响有逐步弱化趋势。相同边界条件下,长径比较小的TiNi圆柱薄壳比能较大。     

复合材料夹层扁壳的有限挠度方程和线性稳定问题

本文对表板采用Kirchhoff假设,考虑夹心沿厚度方向的剪切变形,用最小势能原理导了复合材料夹层扁壳的有限挠度方程和边界条件。作为一个特例,求解了矩形夹层圆柱壳在轴压(或侧压)作用下的线性稳定问题。     

水中爆炸载荷下夹芯圆柱壳的结构优化

采用ANSYS/LS-DYNA有限元软件,研究了由三种不同相对密度的泡沫铝组合成的密度非均匀芯层泡沫金属夹芯圆柱壳的水下抗爆性能及均匀型泡沫金属夹芯结构的结构优化.结果表明:泡沫铝芯层相对密度配置顺序对夹芯圆柱壳的抗爆性能影响明显,可以通过调整芯层配置获得最佳吸能性能泡沫金属夹芯圆柱壳;采用Kriging多目标优化分析方法,获得了以夹芯壳单位面积重量最小、中心位移最小和能量吸收最大为目标,上、下面板的厚度的最优解.     

金属圆柱壳受大质量低速冲击的屈曲变形

对钢质和铜质金属圆柱壳的轴向冲击动力响应进行了实验研究,记录了两种不同材料圆柱壳在大质量低速冲击下的冲击力时程曲线,得到其屈曲模态。采用高速摄像及模拟技术给出了钢质圆柱壳渐进屈曲的全过程,为理解钢质圆柱壳的屈曲机理提供了直观的结果。黄铜质圆柱壳在大质量低速冲击下, 出现整个壳面滿布屈曲波纹的塑性动力屈曲现象,说明高速冲击不是产生塑性动力屈曲的充要条件。像铜这样具有高密度的韧性材料,在大质量低速冲击下,会在轴向产生持续的压缩塑性流作用而出现塑性动力屈曲现象。     

负泊松比蜂窝夹层板的振动特性研究

研究了负泊松比蜂窝夹层板几何参数变化对板振动频率的影响,并得到了频率随泊松比的变化规律。在Reddy高阶剪切变形理论的基础上,利用Hamilton原理,推导出四边简支边界条件下的负泊松比蜂窝夹层板的偏微分运动方程。根据修正后的Gibson公式,考虑了蜂窝胞元壁板的弯曲和伸缩变形,重新计算了蜂窝芯层胞元的等效弹性参数。利用Navier法,选择合适四边简支边界条件的模态函数,得出板的长厚比分别为0.01、0.05、0.10,芯厚比分别为0.80、0.85、0.90、0.95和蜂窝芯胞元倾角分别为-30°、-60°、0°、30°、60°等情况下系统的前五阶固有频率。研究结果表明,系统的固有频率随板的芯厚比、蜂窝芯胞元倾角、蜂窝芯壁厚与斜壁之比的增加都在减小,而随着板长厚比的增加而增加。分析了泊松比的变化对系统固有频率的影响,发现负泊松比蜂窝夹层板的固有频率要明显小于传统正泊松比蜂窝夹层板。本文所得结果对进一步研究系统的多模态共振具有指导意义,为负泊松比蜂窝夹层结构的工程应用在减振设计方面提供一定的理论依据。     

弹性支撑功能梯度微圆柱壳模态频率的研究

在建立弹性支撑功能梯度薄壁微圆柱壳模型的基础上,基于修正的偶应力理论和一阶剪切变形理论,推导了微圆柱壳的模态频率方程,讨论了弹性支撑、尺寸效应、温度梯度、材料组分指数、孔隙以及几何尺寸等参数对微圆柱壳模态频率的影响。结果表明：微尺度下,弹性刚度系数在0～10⁵ N/m³范围内对微圆柱壳的模态频率基本无影响,剪切刚度系数在0～5×10⁴ N/m范围内对模态频率的影响较大,且增大剪切刚度系数有益于提高微圆柱壳的模态频率;由修正的偶应力理论得到的模态频率大于由经典连续体理论得到的模态频率;在弹性支撑和尺寸效应有无考虑的4种组合下,模态频率随温度梯度和微圆柱壳长度的增大而减小,随陶瓷体积分数指数的增大而增大,随孔隙体积分数和微圆柱壳厚度的变化规律不同;温度梯度对考虑尺寸效应或弹性基础的微圆柱壳模态频率影响较大,而孔隙调节具弹性支撑微圆柱壳的模态频率尤其显著。     

受轴向冲击圆柱壳的塑性动力屈曲研究

令屈曲模态同时包含轴向坐标x和环向坐标 ,通过最优模态的分析 ,直接得到各向同性线性强化刚塑性圆柱壳受轴向冲击时发生轴对称屈曲或非轴对称屈曲时的临界速度 ,在此基础上讨论了临界速度与径厚比的关系。     

恒磁场作用下压磁/压电半导体复合圆柱壳的耦合响应分析

本文针对由压磁材料和压电半导体材料组成的无限长复合圆柱壳结构，理论研究了其在径向恒磁场作用下结构内的多场耦合力学响应问题。为解析求解方便，文中分别采用单向耦合法和线性全耦合法，导出复合圆柱壳内位移场、电场、载流子等物理量的解析表达式。利用导出的解析表达式，数值分析了磁场大小和半导体层厚度比对结构内电势、电场和载流子的影响。计算结果表明：磁场和厚度比均可用来有效调控半导体层内的电学量，复合圆柱壳结构的厚度比有一个最优区间。     

金属蜂窝夹层结构抗水下爆炸特性

金属蜂窝夹层结构是一种新型的舰船防护结构,在舰船防护领域具有广阔的应用前景,但目前缺乏对其在实际水下爆炸载荷作用下动态响应的研究。为研究金属蜂窝夹层结构在水下爆炸载荷作用下的动态响应及防护性能,设计并制备了背板加筋蜂窝夹层结构样件以及相应的浮箱,在大型露天水池中进行了水下实爆 实验;通过声固耦合算法对结构响应进行模拟,实验结果与模拟结果吻合良好,随后分析了蜂窝夹层板的变形过程及能量吸收特性,量化了载荷参数（冲击因子）及结构参数（前后面板厚度比和芯体相对密度）对结构动态响应的影响;最后,以蜂窝夹层板的面密度和后面板中心点最大变形的无量纲量为目标函数,使用NSGA-Ⅱ遗传算法对结构进行了多目标优化,得到对应的Pareto前沿。结果表明,随着冲击因子的增大,蜂窝夹层板整体变形显著增大,蜂窝芯体始终是主要的吸能构件,但其吸能占比逐渐降低;随着前后面板厚度比或芯体相对密度的增加,蜂窝夹层结构的最大变形呈现先降低后升高的趋势,同时呈现不同的变形模式,芯体相对密度对结构变形的影响更为显著;对蜂窝夹层结构开展多目标优化可有效降低结构的面密度及最大变形,优化结果可为蜂窝夹层结构的设计选型提供参考。     

Parametric study of an elliptical fuselage made of a sandwich composite structure

We size the shell thickness of a pressurised elliptical fuselage and analyse the weight gains or savings compared to a circular fuselage. Three fuselage construction cases are analysed: a monolithic construction, a symmetric sandwich with two facesheets of equal thicknesses separated by a lightweight core, and an unsymmetric sandwich with two facesheets of different thicknesses. We develop a proper dimensionless analysis comparing the proposed elliptical fuselage with a circular one for two different scenarios: equivalent cross-section areas and enclosing a similar rectangular box. We apply a semi-analytical thin shell theory to compute the loading due to pressurisation around the circumference of the fuselage cross-section. We select the facesheet thicknesses above and below the sandwich core at every location to minimise weight. The goal is to compute the structural weight gain or penalty that is incurred by replacing a circular fuselage with an elliptical one to resist internal pressurisation in function of the scenario, eccentricity, fuselage diameter, and sandwich core thickness. We find that an elliptical cross-section incurs a significant penalty in terms of necessary facesheet thickness even with an optimised unsymmetric sandwich construction. This penalty can be minimised by keeping the eccentricity low, the loading intensity low and the core thick.     

Optimization of cylindrical shells with compliant cores

Thin-walled, cylindrical structures are found extensively in both engineering components and in nature. The weight to load bearing ratio is a critical element of design of such structures in a variety of engineering applications, including space shuttle fuel tanks, aircraft fuselages, and offshore oil platforms. In nature, thin-walled cylindrical structures are often supported by a honeycomb- or foam-like cellular core, as for example, in plant stems, porcupine quills, or hedgehog spines. Previous studies have suggested that a compliant core increases the buckling resistance of a cylindrical shell over that of a hollow cylinder of the same weight. In this paper, we extend the linear-elastic buckling theory by coupling it with basic plasticity theory to provide a more comprehensive analysis of isotropic, cylindrical shells with compliant cores. We examine the optimal design of a thin-walled cylinder with a compliant core, of given radius and specified materials, for a prescribed load bearing capacity in axial compression. The analysis gives the values of the shell thickness, the core thickness, and the core density that maximize the load bearing capacity of the shell with a compliant core over an equivalent weight hollow shell. The analysis also identifies the optimum ratio of the core modulus to the shell modulus and is supported by a Lagrangian optimization technique. The analysis further discusses the selection of materials in the design of a cylinder with a compliant core, identifying the most suitable material combinations. The performance of a cylinder with a compliant core is compared with competing designs (optimized hat-stiffened shell and optimized sandwich-wall shell). Finally, the challenges associated with achieving the optimal design in practice are discussed, and the potential for practical implementation is explored.     

Nonlinear vibration of functionally graded graphene platelet-reinforced composite truncated conical shell using first-order shear deformation theory

In this study, the first-order shear deformation theory(FSDT) is used to establish a nonlinear dynamic model for a conical shell truncated by a functionally graded graphene platelet-reinforced composite(FG-GPLRC). The vibration analyses of the FG-GPLRC truncated conical shell are presented. Considering the graphene platelets(GPLs) of the FG-GPLRC truncated conical shell with three different distribution patterns, the modified Halpin-Tsai model is used to calculate the effective Young's modulus. Hamilton's principle, the FSDT, and the von-Karman type nonlinear geometric relationships are used to derive a system of partial differential governing equations of the FG-GPLRC truncated conical shell. The Galerkin method is used to obtain the ordinary differential equations of the truncated conical shell. Then, the analytical nonlinear frequencies of the FG-GPLRC truncated conical shell are solved by the harmonic balance method. The effects of the weight fraction and distribution pattern of the GPLs, the ratio of the length to the radius as well as the ratio of the radius to the thickness of the FG-GPLRC truncated conical shell on the nonlinear natural frequency characteristics are discussed. This study culminates in the discovery of the periodic motion and chaotic motion of the FG-GPLRC truncated conical shell.     

热环境下功能梯度夹层双曲壳三维自由振动分析

功能梯度夹层双曲壳结构广泛应用在航空航天、海洋工程等领域中,对于该类结构的动力学特性研究非常重要。本文以热环境下功能梯度夹层双曲壳为研究对象,在三阶剪切变形理论的基础上,考虑横向拉伸作用的影响提出了一种新的位移场,假设材料的物性参数与温度有关,且沿厚度方向表示为幂律函数。利用Hamilton原理得到简支边界条件下功能梯度夹层双曲壳三维振动系统动力学方程,利用Navier法求得两种不同夹层类型的系统固有频率。研究了几何物理参数和温度场对功能梯度夹层双曲壳自由振动固有频率的影响。     

Three-point bending of honeycomb sandwich beams with facesheet perforations

A novel square honeycomb-cored sandwich beam with perforated bottom facesheet is investigated under threepoint bending,both analytically and numerically.Perforated square holes in the bottom facesheet are characterized by the area ratio of the hole to intact facesheet(perforation ratio).While for large-scale engineering applications like the decks of cargo vehicles and transportation ships,the perforations are needed to facilitate the fabrication process(e.g.,laser welding)as well as service maintenance,it is demonstrated that these perforations,when properly designed,can also enhance the resistance of the sandwich to bending.For illustration,fair comparisons among competing sandwich designs having different perforation ratios but equal mass is achieved by systematically thickening the core webs.Further,the perforated sandwich beam is designed with a relatively thick facesheet to avoid local indention failure so that it mainly fails in two competing modes:(1)bending failure,i.e.,yielding of beam cross-section and buckling of top facesheet caused by bending moment;(2)shear failure,i.e.,yielding and buckling of core webs due to shear forcing.The sensitivity of the failure loads to the ratio of core height to beam span is also discussed for varying perforation ratios.As the perfo-ration ratio is increased,the load of shear failure increases due to thickening core webs,while that of bending failure decreases due to the weakening bottom facesheet.Design of a sandwich beam with optimal perforation ratio is realized when the two failure loads are equal,leading to significantly enhanced failure load(up to 60%increase)relative to that of a non-perforated sandwich beam with equal mass.     

冲击载荷作用下柱壳链中的弹性波传播简化模型及其解析解

柱壳链能引起波形的弥散,具备操控波形的潜力。建立了柱壳链结构的等效连续介质模型和细观有限元模型,研究了质量块冲击作用下柱壳链中的弹性应力波传播过程及其几何弥散特性。基于考虑横向惯性修正的Rayleigh-Love波动方程,建立了柱壳链在质量块冲击下的控制方程,采用Laplace变换及其逆变换获得了位移场、速度场和应变场的解析解,所得结果与细观有限元模拟结果较好吻合。结果表明,在冲击过程中应变和速度峰值均逐渐减小,应变峰值、振荡幅度和波形前沿宽度与泊松比和惯性半径相关,泊松比和惯性半径越大,应变峰值越小,应变分布振荡越剧烈,波形前沿宽度越宽。     

撞击载荷下Nomex蜂窝夹芯梁的变形模式研究

本文研究了Nomex蜂窝夹芯结构在不同冲量下的变形模式和失效模式.实验采用子弹撞击的加载方式,对Nomex蜂窝夹芯梁施加大小不同的冲量,使用激光位移传感器测量每个试件后蒙皮的变形位移.分析了同芯层厚度,不同蒙皮厚度的Nomex蜂窝夹芯梁在不同冲量作用下抵抗变形的能力,以及冲量大小与蒙皮厚度对夹芯梁抵抗撞击能力的影响,计算分析了蒙皮与芯层的吸能性.实验结果表明:增加蒙皮的厚度能够改善夹芯梁在撞击荷载下抵抗变形的能力,在撞击过程中芯层吸收了50％左右的能量,且冲量越大,芯层吸收的能量越多.     

基于弧长法的受压球壳稳定性分析

对受压球壳进行特征值屈曲分析,得到了前6阶屈曲模态及线性屈曲临界载荷;采用弧长法进行非线性有限元分析,对理想球壳施加初始扰动,通过2次扰动值折半的方法求得引起结构屈曲的最小扰动值,追踪到了屈曲分支点和全过程载荷-位移路线。基于前6阶屈曲模态位移,在受压球壳中分别引入2.5mm和1mm两种缺陷值,分析缺陷对球壳屈曲特性的影响。结果表明:取壳厚的0.5%即0.05mm时,得最小扰动值,近似模型与完善结构极值载荷的差值为0.93%;球壳是缺陷敏感性结构,缺陷的幅值和分布都对其极限载荷有影响,缺陷幅值与厚度比为0.1时,缺陷球壳承载力相对理想结构下降了约11%,缺陷幅值与厚度比为0.25时,承载力相对下降了约30%,说明提高球壳稳定性需要提高球壳加工精度。     

Response and Damage Tolerance of Composite Sandwich Structures under Low Velocity Impact

The deformation and failure response of composite sandwich beams and panels under low velocity impact was reviewed and discussed. Sandwich facesheet materials discussed are unidirectional and woven carbon/epoxy, and woven glass/vinylester composite laminates; sandwich core materials investigated include four types of closed cell PVC foams of various densities, and balsa wood. Sandwich beams were tested in an instrumented drop tower system under various energy levels, where load and strain histories and failure modes were recorded for the various types of beams. Peak loads predicted by spring-mass and energy balance models were in satisfactory agreement with experimental measurements. Failure patterns depend strongly on the impact energy levels and core properties. Failure modes observed include core indentation/cracking, facesheet buckling, delamination within the facesheet, and debonding between the facesheet and core. In the case of sandwich panels, it was shown that static and impact loads of the same magnitude produce very similar far-field deformations. The induced damage is localized and is lower for impact loading than for an equivalent static loading. The load history, predicted by a model based on the sinusoidal shape of the impact load pulse, was in agreement with experimental results. A finite element model was implemented to capture the full response of the panel indentation. The investigation of post impact behavior of sandwich structures shows that, although impact damage may not be readily visible, its effects on the residual mechanical properties of the structure can be quite detrimental.