A refined theory for laminated beams: Part I—A new high order approach

This paper presents a new displacement-based one-dimensional model for the analysis of multilayered composite beams. The kinematic restriction of cross sections rigid in their own planes is introduced. The axial displacements over the cross sections are represented in terms of explicitly defined piecewise polynomial warping functions with discontinuous derivatives at the interlaminae, whereas the amplitude of the displacements along the beam axis is established by means of a variational formulation. It is proved that the proposed representation of the axial displacements yields the exact solution of the interior domain problem for a beam subjected to a transverse load varying according to a polynomial law. It is shown that two or three coordinate functions are sufficient to yield continuous distributions of equilibrated stresses except for small neighborhoods of the constrained cross sections, where a higher number of warping functions could be used in order to obtain a better accuracy. The numerical results show excellent agreement with plane stress finite element and plane strain exact solutions.

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Sommario In questo lavoro viene presentato un nuovo modello monodimensionale per l'analisi di travi composite multistrato. Viene introdotta l'ipotesi di indeformabilita delle sezioni nel proprio piano mentre gli spostamenti assiali nella sezione sono rappresentati facendo uso di funzioni ingobbamento definite sull'intera altezza e con derivata discontinua all'in erlamina. Infine, l'ampiezza degli spostamenti lungo l'asse della trave è determinata facendo uso di una formulazione variazionale. Si mostra come la rappresentazione degli spostamenti assiali proposta sia in grado di fornire la soluzione esatta, all'interno del dominio, per una trave soggetta ad un carico trasversale variabile con legge nolinomiale. Due o tre funzioni coordinate sono sufficienti a fornire distribuzioni di sforzi che verificano l'equilibrio anche all'interlamina, a meno di zone rislrette in vicinanza di sezioni vincolate. I risultati numerici mostrano un eccellente accordo con soluzioni agli elementi finiti in stato piano di tensione e con soluzioni esatte in stato piano di deformazione.

     

Sound transmission through laminated composite cylindrical shells using analytical model

Composite structures are often used in aircraft because of advantages offered by a high strength to weight ratio. Sound transmission through an infinite laminated composite cylindrical shell is studied in the context of the transmission of airborne sound into aircraft interior. The shell is immersed in an external fluid medium and contains an internal fluid, and airflow in an external fluid medium moves with a constant velocity. The different parameters were used to see how laminate specification affected noise transmission. An exact solution is obtained by solving the vibration equation of laminated composite shell and acoustic wave equations simultaneously. Transmission losses (TLs) obtained from numerical solution are compared with those of other authors. The effects of different source condition, structural properties and flight conditions on TL are studied for a range of values, especially, incident angle of the plane wave, Mach number and flight altitude of aircraft, stack sequences, angle of warp and damping.     

Behavior of Pin-loaded Laminated Composites

In this study, an investigation was carried out to determine the effects of joint geometry and fiber orientation on the failure strength and failure mode in a pinned joint laminated composite plate. Behavior of pin-loaded laminated composites with different stacking sequence and different dimensions has been observed experimentally. E/glass–epoxy composites were manufactured to fabricate the specimens. Mechanical properties of the composites were characterized under tension, compression and in-plane shear in static loading conditions. Laminated composites were loaded through pins. Single-hole pin-loaded specimens were tested for their tensile response and width-to-hole diameter (W/D) and edge distance-to-hole diameter (E/D) ratios evaluated. A series of experiments was performed with six different material configurations ([0/±45]_s–[90/±45]_s, [0/90/0]_s–[90/0/90]_s and [90/0]_2s–[±45]_2s), in all, over 120 specimens. E/D ratios and W/D ratios of plates were changed from 1 to 5 and 2 to 5, respectively. Failure propagation and failure type were observed on the specimens. The influence of the joint geometry on the strength of the pin-loaded composites was assessed. When laminated composite plates were loaded to final failure, three basic failure modes consisting of net-tension, shear out and bearing failure were observed for the different geometric dimensions. All the connections tested showed that the fiber orientations have a definite influence on the position around hole circumference at which failure initiated. Net-tension failure occurred for specimens that had small width and large end distance. When the width was increased, the specimens which had small end distances failed in the shear-out modes. When the end distance was increased, bearing failure developed in addition to shear-out failure. The experimental results showed that the ultimate load capacities of E/glass–epoxy laminate plates with pin connection were increased by increasing W and E. However, increasing the E/D and W/D ratios beyond a critical value has an insignificant effect on the ultimate load capacity of the connection.     

Analytical elasto-creep model of interfacial thermal stresses and strains in trilayer assemblies

A two-dimensional model has been developed for thermal stresses, elastic strains, creep strains, and creep energy density at the interfaces of short and long trilayer assemblies under both plane stress and plane strain conditions. Both linear (viscous) and non-linear creep constitutive behavior under static and cyclic thermal loading can be modeled for all layers. Interfacial stresses and strains are approximated using a combination of exact elasticity solutions and elementary strength of materials theories. Partial differential equations are linearized through a simple finite difference discretization procedure. The approach is mathematically straightforward and can be extended to include plastic behavior and problems involving external loads and a variety of geometries. The model can provide input data for thermal fatigue life prediction in solder or adhesive joints. For a typical solder joint, it is demonstrated that the predicted cyclic stress–strain hysteresis shows shakedown and a rapid stabilization of the creep energy dissipation per cycle in agreement with the predictions of finite element analysis.     

Numerical simulation of nonlinear magnetic-mechanical-electric coupling effect in laminated magnetoelectric composites

Considering the significant nonlinear magnetoelectric (ME) characteristics in laminated ME composites, we build a numerical model of magnetic-mechanical-electric coupling effect based on the nonlinear magnetostrictive constitutive relation. The change of the ME field coefficients with bias magnetic field predicted by this model shows good agreement with the experimental result, both qualitatively and quantitatively. Furthermore, this paper considers and predicts the magnetoelectric conversion charateristics of laminated ME composites, calculates and analyzes the influence of the thickness ratio of magnetostrictive layer, the geometrical size of laminated composites, the saturation magnetization, and the types of piezoelectric materials on the ME conversion coefficient of ME laminated composites. We believe that this research provides a theoretical basis for the production of magnetoelectric devices with good magnetoelectric conversion characteristics.     

Free vibration analysis of piezoelectric coupled annular plates with variable thickness

This paper presents the free vibration analysis of piezoelectric coupled annular plates with variable thickness on the basis of the Mindlin plate theory. No work has yet been done on piezoelectric laminated plates while the thickness is variable. Two piezoelectric layers are embedded on the upper and lower surfaces of the host plate. The host plate thickness is linearly increased in the radial direction while the piezoelectric layers thicknesses remain constant along the radial direction. Different combinations of three types of boundary conditions i.e. clamped, simply supported, and free end conditions are considered at the inner and outer edges of plate. The Maxwell static electricity equation in piezoelectric layers is satisfied using a quadratic distribution of electric potential along the thickness. The natural frequencies are obtained utilizing a Rayleigh–Ritz energy approach and are validated by comparing with those obtained by finite element analysis. A good compliance is observed between numerical solution and finite element analysis. Convergence study is performed in order to verify the numerical stability of the present method. The effects of different geometrical parameters such as the thickness of piezoelectric layers and the angle of host plate on the natural frequencies of the assembly are investigated.     

Magnetic and structural properties of laminated Co65Fe35 films

We report on coercivity mechanisms in Co₆₅Fe₃₅ films. Using a unique High Target Utilisation Sputtering System (HiTUS) sputtering system we have produced a range of samples with controlled grain size in the range 6-30 nm. This has enabled an evaluation of the effects of different seed layers (Ru, Cu, Ta and Mg) and the effects of lamination of the films. We found that in 100 Å single-layer films the coercivity rises abruptly from 29 to 90 Oe with grain size. We found that samples with Cu or Ru seed layers show the largest reduction in coercivity. The effects of lamination are more complex since it leads to a reduction in grain size whereas coercivity increases. We believe this is due to RKKY coupling through the metallic interlayers.     

多色显示电致变色聚合物叠层复合薄膜的可控制备

在氧化铟锡透明导电玻璃(ITO)电极上电化学聚合依次得到聚4,4',4″-三[4-(2-联噻吩基)苯基]胺(PTBTPA)和聚3,4-乙烯二氧噻吩(PEDOT)薄膜, 从而可控制备出叠层复合薄膜. 由红外光谱(FTIR)和场发射扫描电镜(SEM)表征了复合薄膜. 紫外-可见吸收光谱和电化学测试结果表明, 相对于PTBTPA薄膜(中性态橙色到氧化态深灰色)与PEDOT薄膜(中性态深蓝色到氧化态浅蓝色)的颜色变化, 叠层复合薄膜在不同的电压下能够展现出从橙色→蓝色→墨绿色的颜色变化, 并保持了较好的电化学活性和光学对比度. 这主要源于中性态吸收光谱和颜色显示互补的电致变色材料的选择. 本文提供了一种简单有效的制备多色乃至全色显示的电致变色材料的方法, 该方法同样适用于其它聚合物电致变色材料体系.     

Analysis of nonlinear dynamic response and dynamic buckling for laminated shallow spherical thick shells with damage

Based on the nonlinear theory of shallow spherical thick shells and the damage mechanics, a set of nonlinear equations of motion for the laminated shallow spherical thick shells with damage subjected to a normal concentrated load on the top are established. According to Hertz law, the contact force acted upon the shells is determined due to the impact of a mass, and it is related to the mass and initial velocity of the striking object, the geometrical and physical character of the shell. By using the finite difference method and the time increment procedure, the nonlinear equations are resolved. In the numerical examples, the effects of the damage, the initial velocity, and mass of the striking object, the shells’ geometrical parameters on the dynamic responses and dynamic buckling of the laminated shallow spherical thick shells are discussed. Research of Y. Fu, Z. Gao and F. Zhu was supported by National Natural Science Foundation of China (No. 10572049).