共查询到20条相似文献,搜索用时 468 毫秒
1.
Approximate analytical solutions and experimental analysis for transient response of constrained damping cantilever beam 总被引:2,自引:0,他引:2
Vibration mode of the constrained damping cantilever is built up according to the mode superposition of the elastic cantilever beam. The control equation of the constrained damping cantilever beam is then derived using Lagrange's equation. Dynamic response of the constrained damping cantilever beam is obtained according to the principle of virtual work, when the concentrated force is suddenly unloaded. Frequencies and transient response of a series of constrained damping cantilever beams are calculated and tested. Influence of parameters of the damping layer on the response time is analyzed. Analyitcal and experimental approaches are used for verification. The results show that the method is reliable. 相似文献
2.
3.
To predict the vibration response of viscoelastic composite structure, two key issues need to be conducted, one is introducing the constitutive model of viscoelastic material into the analysis model and the other is describing the real damping behavior of viscoelastic composite structure. The emphasis of this study is to obtain the effects of frequency dependence on the vibration response of viscoelastic composite structure and the method of introducing two kinds of damping (viscoelastic material damping and remaining equivalent viscous damping). Vibration response analysis in frequency domain was investigated for viscoelastically damped plate. A cantilever plate attached with the ZN_1 viscoelastic free layer damping (FLD) was chosen to demonstrate the developed method. Frequency-domain response of the composite plate were solved and the obtained results were compared with the experimental values for the purpose of assessing the rationality of the proposed method. In addition, in order to obtain the effects of viscoelastic material parameters on vibration response of viscoelastic composite structure, a detailed parametric analysis was performed. This study shows that the frequency dependent characteristic of viscoelastic material has significant influence on the vibration response in the resonant region and acceptable results can be achieved in the non-resonant region if frequency dependent parameters are substituted by average values of the viscoelastic parameters reasonably in the analysis process. 相似文献
4.
5.
《Wave Motion》2020
Vibrations and the damping behaviour of thin constrained composite plates with double piezoelectric layers are analytically explored by using Fourier transformation and classical laminated plate theory. Electric potential equations in the double piezoelectric layers are solved with respect to closed and open circuit boundary conditions, an exterior dielectric slab and active control. The natural frequencies and loss factors of the constrained smart composite plates with passive control methods are not notably changed in comparison with those of the constrained composite plates without piezoelectric effects since vibrational energy does not efficiently convert to electrical energy. The loss factors of the composite plates with active constrained damping increase and the natural frequencies have significant variations as the proportional derivative gains increase. Transverse displacement power spectra of the piezoelectric composite plates with active control are compared with those of the piezoelectric composite plates with passive control showing that active control has the best suppression performance of vibrations for the constrained laminated plates with double piezoelectric layers. Radial power spectral density, phase angles and cylindrical-wave power spectral density are calculated. Interesting patterns of wave propagation are explained when plane wave expansion is used to obtain Bessel cylindrical waves. 相似文献
6.
Li Zelin Li Hui Wang Dongsheng Ren Chaohui Zu Xudong Zhou Jin Guan Zhongwei Wang Xiangping 《力学学报》1957,52(6):1690
本文首次从解析角度建立了低速冲击激励下嵌入黏弹性阻尼芯层的纤维金属混杂层合板动态响应预测模型. 首先,结合经典层合板理论和冯$\cdot$卡门假设,建立了嵌入黏弹性芯层的纤维金属混杂层合板弹性损伤本构关系. 然后,将层合板受冲击时的变形分成接触和拉伸两个区域,在接触区域内,对金属层采用 Von Mises 失效准则,纤维层采用 Tsai-Hill 失效准则和对黏弹性层采用指数 Drucker-Prager 失效准则判断层合板损伤情况. 考虑不同材料层对冲击动态响应的贡献来修正两个变形区域的位移公式,进而计算结构因弹性变形产生的应变能,以及接触区域因塑性变形消耗的能量,实现每次失效事件发生后各层材料的能量、位移和冲击接触力的理论求解,并给出了结构动态响应分析的具体流程图. 最后,以嵌入 Zn33 黏弹性芯层的 TA2 钛合金混杂 T300 碳纤维/树脂层合板为研究对象,开展落锤冲击实验. 验证结果表明,理论预测与测试获得的冲击接触力、位移响应以及冲击载荷-位移曲线吻合较好,且关注的峰值点计算误差最大不超过 9%,进而验证了所提出的理论模型的有效性. 相似文献
7.
减振阻尼材料可以改变结构的阻尼特性从而降低振动响应和声辐射水平,因而被广泛应用于飞机结构的减振降噪。本文针对减振阻尼材料的设计和应用开展了一系列试验研究,首先通过材料改性得到了不同主基料下材料的配方对阻尼性能的影响;其次配制了三种不同的约束阻尼结构,通过DMA测试对比了三种约束阻尼结构的最佳使用温度和频率范围;最后对约束阻尼结构的减振效果和粘贴布局应用进行了试验,试验结果表明,约束阻尼结构具有良好的减振效果。通过研究掌握了减振阻尼材料在材料改性、约束阻尼结构设计、粘贴布局应用等方面的一些设计方法,可为后续的进一步研究提供技术支持和参考。 相似文献
8.
Based on Reddy's layerwise theory, the governing equations for dynamic response of viscoelastic laminated plate are derived by using the quadratic interpolation function for displacement in the direction of plate thickness. Vibration frequencies and loss factors are calculated for free vibration of simply supported viscoelastic sandwich plate, showing good agreement with the results in the literature. Harmonious transverse stresses can be obtained. The results show that the transverse shear stresses are the main factor to the delamination of viscoelastic laminated plate in lower-frequency free vibration, and the transverse normal stress is the main one in higher-frequency free vibration. Relationship between the modulus of viscoelastic materials and transverse stress is analyzed. Ratio between the transverse stress's maximum value and the in-plane stress's maximum-value is obtained. The results show that the proposed method, and the adopted equations and programs are reliable. 相似文献
9.
约束层阻尼板动力学问题的半解析解 总被引:1,自引:0,他引:1
利用条形传递函数方法(SDTFM)得到了约束层阻尼(CLD)板动力学问题的半解析解.首先对CLD板沿纵向离散成多个条形单元,基于Hamilton原理推导出条形单元的刚度矩阵和质量矩阵,仿照有限元法组集得到系统的总刚度矩阵和总质量矩阵.经Laplace变换后引入状态向量,采用分布参数传递函数方法在状态空间内建立CLD板的控制方程并进行求解.最后以对边固支和悬臂CLD板为例,得到了板的动力学特性和频响曲线,并与NASTRAN或相关文献结果进行了比较,吻合良好,验证了该方法的有效性.从推导过程和算例可以看出,该方法所需的单元数目少,获得的是半解析解,计算效率高且准确可靠. 相似文献
10.
可控约束阻尼层板的杂交控制 总被引:5,自引:0,他引:5
用局部压电层控制约束阻尼约束层产生一种新的主、被动杂交控制形式,称为可控制 约束层。本文根据弹性材料、粘弹性材料、压电材料的本构关系和变形连续条件,建立了可控约束阻尼层板的控制微方程;从理论上证明了用离散小压电片组合来代替整体压电层而不影响作动效果,改善了结构的工艺性;利用Galerkin方法和GHM方法建立了系统的近似低阶方程对一试验模型进行了控制数值模拟和试验实现,结果表明这种杂交控制对控制 相似文献
11.
Deployable/retractable damped cantilever beams are a class of time-varying parametric structures which have attracted considerable research interest due to their many potential applications in the intelligent robot field and aerospace. In the present work, the dynamic characteristics of a deployable/retractable damped cantilever beam are investigated experimentally and theoretically. The time-varying damping, as a function of the beam length, is obtained by both the enveloped fitting method and the period decrement method. Furthermore, the governing equation of the deployable/retractable damped cantilever beam is derived by introducing the time-varying damping parameter,and the corresponding closed-form solution and vibration principles are investigated based on the averaged method. The theoretical predictions for transient dynamic responses are in good agreement with the experimental results. The dynamic mechanism analysis on time-varying damping offers flexible technology in mechanical and aerospace fields. 相似文献
12.
13.
基于LCF-Kriging模型的结构多失效模式可靠度计算 总被引:1,自引:0,他引:1
针对多失效模式下结构体系可靠度计算中的代理模型构建成本与计算精度如何权衡的问题,本文以减小体系失效概率预测方差为出发点,推导出最大贡献函数(LCF-Largest Contribution Function)来识别对体系失效概率方差影响较大的样本。LCF函数可减少对体系失效概率方差影响较小区域内样本数量,进而提高代理模型的计算效率;通过置信水平和允许相对误差建立LCF函数的学习停止条件,能够保证已有样本信息不浪费。本文选取能够对多个功能函数联合构建的多输出Kriging模型作为代理模型,基于LCF-Kriging模型并结合MCS对体系可靠度进行计算,功能函数的相关性可通过各失效模式的逻辑关系予以考虑。数值算例表明,在适当的学习停止条件下,对于串联、并联和串并混联的结构体系可靠度评估,本文方法均能在计算精度和计算效率之间达到满意平衡。 相似文献
14.
15.
This paper presents the analysis on the nonlinear dynamics of a deploying orthotropic composite laminated cantilever rectangular plate subjected to the aerodynamic pressures and the in-plane harmonic excitation. The third-order nonlinear piston theory is employed to model the transverse air pressures. Based on Reddy’s third-order shear deformation plate theory and Hamilton’s principle, the nonlinear governing equations of motion are derived for the deploying composite laminated cantilever rectangular plate. The Galerkin method is utilized to discretize the partial differential governing equations to a two-degree-of-freedom nonlinear system. The two-degree-of-freedom nonlinear system is numerically studied to analyze the stability and nonlinear vibrations of the deploying composite laminated cantilever rectangular plate with the change of the realistic parameters. The influences of different parameters on the stability of the deploying composite laminated cantilever rectangular plate are analyzed. The numerical results show that the deploying velocity and damping coefficient have great effects on the amplitudes of the nonlinear vibrations, which may lead to the jumping phenomenon of the amplitudes for first-order and second-order modes. The increase of the damping coefficient can suppress the increase of the amplitudes of the nonlinear vibration. 相似文献
16.
Owing to the advantages of noncontact and fullfield measurement, an optical system called the amplitude fluctuation electronic
speckle pattern interferometry (AFESPI) method with an out-of-plane setup is employed to investigate the vibration of a cantilever
square plate with a crack emanating from one edge. Based on the fact that clear fringe patterns will be shown by the AFESPI
method only at resonant frequencies, both the resonant frequencies and the vibration mode shapes can be obtained experimentally
at the same time. Three different crack locations will be discussed in detail in this study. One is parallel to the clamped
edge, and the other two are perpendicular to the clamped edge. The numerical finite element calculations are compared with
the experimental results, and good agreement is obtained for resonant frequencies and mode shapes. The influences of crack
locations and lengths on the vibration behavior of the clamped cantilever plate are studied in terms of the dimensionless
frequency parameter (λ
2) versus crack length ratio (a/L). The authors find that if the crack face displacements are out of phase, a large value of stress intensity factor may be
induced, and the cracked plate will be dangerous from the fracture mechanics point of view. However, there are some resonant
frequencies for which the crack face displacements are completely in phase, causing a zero stress intensity factor, and the
cracked plate will be safe. 相似文献
17.
首次给出了四边简支的 Mindlin 矩形微板热弹性阻尼的解析解. 基于考虑一阶剪切变形的 Mindlin 板理论和单向耦合热传导理论建立了微板热弹性耦合自由振动控制微分方程. 忽略温度梯度在面内的变化,在上下表面绝热边界条件下求得了用变形几何量表示的温度场的解析解. 进一步将包含热弯曲内力的结构振动方程转化为只包含挠度振幅的四阶偏微分方程. 利用特征值问题之间在数学上的相似性,在四边简支条件下给出了用无阻尼 Kirchhoff 微板的固有频率表示的 Mindlin 矩形微板的复频率解析解,从而利用复频率法求得了反映热弹性阻尼水平的逆品质因子. 最后,通过数值结果定量地分析了剪切变形、材料以及几何参数对热弹性阻尼的影响 规律. 结果表明,Mindlin 板理论预测的热弹性阻尼小于 Kirchhoff 板理论预测的热弹性阻尼. 两种理论预测的热弹性阻尼之间的差值在临界厚度附近十分显著. 另外,随着微板的边/厚比增大,Mindlin 微板的热弹性阻尼最大值单调增大,而 Kirchhoff 微板的热弹性阻尼最大值却保持不变. 相似文献
18.
低速冲击激励下嵌入黏弹性阻尼芯层的纤维金属混杂层合板动态响应预测模型 总被引:1,自引:0,他引:1
本文首次从解析角度建立了低速冲击激励下嵌入黏弹性阻尼芯层的纤维金属混杂层合板动态响应预测模型. 首先,结合经典层合板理论和冯$\cdot$卡门假设,建立了嵌入黏弹性芯层的纤维金属混杂层合板弹性损伤本构关系. 然后,将层合板受冲击时的变形分成接触和拉伸两个区域,在接触区域内,对金属层采用 Von Mises 失效准则,纤维层采用 Tsai-Hill 失效准则和对黏弹性层采用指数 Drucker-Prager 失效准则判断层合板损伤情况. 考虑不同材料层对冲击动态响应的贡献来修正两个变形区域的位移公式,进而计算结构因弹性变形产生的应变能,以及接触区域因塑性变形消耗的能量,实现每次失效事件发生后各层材料的能量、位移和冲击接触力的理论求解,并给出了结构动态响应分析的具体流程图. 最后,以嵌入 Zn33 黏弹性芯层的 TA2 钛合金混杂 T300 碳纤维/树脂层合板为研究对象,开展落锤冲击实验. 验证结果表明,理论预测与测试获得的冲击接触力、位移响应以及冲击载荷-位移曲线吻合较好,且关注的峰值点计算误差最大不超过 9%,进而验证了所提出的理论模型的有效性. 相似文献
19.
20.
The damping property of materials can be defined as the ratio of dissipated energy over the total strain energy during the
loading–unloading process, called the specific damping capacity (SDC). In this study, in order to characterize the damping
properties of materials, a test plan in designed to extract the SDC of a single layer composite from hysteresis data. The
theory of linear viscoelasticity incorporates a varying Young’s Modulus by using a complex stiffness modulus. Considering
different lay-ups, the modified classical lamination plate theory is modified to represent both stiffness and SDC of laminates.
The results are compared with experimental results for symmetric laminated specimen. This evaluation shows a very good agreement
between theoretical and experimental results in the range of low frequency loading from 0.2 to 4 Hz. The complex compliance
matrix changes the governing equation in to a complex form which contains both stiffness and damping properties. 相似文献