压电智能结构荷载识别方法的研究

采用压电智能结构实测荷载的输出响应,基于BP神经网络与有限元逆分析提出一种识别荷载位置及大小的方法. 首先在结构的不同位置施加单位荷载由有限元方法计算得到网络的学习样本,经网络作逆分析识别荷载位置,继而通过有限元逆逼近方法确定荷载大小的最小二乘解. 数值算例表明,该方法计算速度快、精度高,不受结构几何形状和边界条件的限制,用于识别实际压电智能结构不确定荷载的位置及大小是可行的.     

A coupled Timoshenko model for smart slender structures

In this paper, a generalized Timoshenko model has been developed for prismatic, beam-like slender structures with embedded or surface mounted piezoelectric type smart materials. Starting from a geometrically exact formulation of the original, three-dimensional electromechanical problem, we apply the variational asymptotic method to carry out a systematic dimensional reduction. In the process, the three-dimensional electromechanical enthalpy functional is approximated asymptotically using the slenderness as the small parameter to find out an equivalent one-dimensional electromechanical enthalpy functional. For Timoshenko-like refinement over the Euler–Bernoulli beam model, terms up to the second order of the slenderness are kept in the enthalpy expression. As an unified analysis tool, the present model can analyze embedded or surface mounted active layer with arbitrary cross-sectional geometry as two cases of a general one, no special assumptions or modifications need to be made for these two separate types of active inclusions.     

Higher order zig-zag theory for smart composite shells under mechanical-thermo-electric loading

A higher order zig-zag shell theory based on general tensor formulation is developed to refine the predictions of the mechanical, thermal, and electric behaviors. All the complicated curvatures of surface including twisting curvatures can be described in a geometrically exact manner in the present shell theory because the present theory is based on the geometrically exact surface representation. The in-surface displacement fields are constructed by superimposing the linear zig-zag field to the smooth globally cubic varying field through the thickness. Smooth parabolic distribution through the thickness is assumed in the out-of-plane displacement in order to consider transverse normal deformation and stress. The layer-dependent degrees of freedom of displacement fields are expressed in terms of reference primary degrees of freedom by applying interface continuity conditions as well as bounding surface free conditions of transverse shear stresses. Thus the proposed theory has only seven primary displacement unknowns and they do not depend upon the number of layers. To assess the validity of present theory, the developed theory is evaluated under the thermal and electric load as well as under the mechanical load of composite cylindrical shells. Through the numerical examples, it is demonstrated that the proposed smart shell theory is efficient because it has the minimal degrees of freedom. The present theory is suitable in the predictions of deformation and stresses of thick smart composite shells under the mechanical, thermal, and electric loads combined.     

A fuzzy model for the failure of composite structures

In this paper, the fuzzy theory is used to describe the uncertainty in failure definition of composite structures. The concept of structural failure level (SFL) is suggested and a method of evaluation is presented.     

Thermally induced fracture of a smart functionally graded composite structure

Discussed is the fracture behavior of a cracked smart actuator on a substrate under thermal load. The actuator is made of piezoelectric material with functionally graded material (FGM) properties. Integral transform method is used to reduce the problem to the solution of a set of singular integral equations and is solved numerically. This paper is completed by including graphical plots of the thermal flow, stress and electric displacement intensity factors around the crack for different crack positions and material gradients. Directions of crack initiation are also predicted by using the energy density criterion.     

Stress analyses of a smart composite pipe joint integrated with piezoelectric composite layers under torsion loading

In order to improve the joint failure strength, an adhesively bonded smart composite pipe joint system has been developed by integrating electromechanical coupling piezoelectric layers with the connection coupler. It has been validated that the integrated piezoelectric ceramic layers can smartly reduce stress concentration in the adhesive layer bond-line under bending or axial tension loads. In this study, piezoelectric particle/fiber reinforced polymer composite was utilized to construct adhesively bonded smart composite pipe joint systems, in order to overcome the brittle characteristic of the piezoelectric ceramic layers and to facilitate joint construction. Since torsion is one of the dominating loading conditions in practice, the behavior of the newly developed smart pipe joint system subjected to torsion loading was investigated in-detail to evaluate the effect of the integrated piezoelectric reinforced polymer composite layer on the joint performance. Firstly, based on the first-order shear deformation theory, the fundamental equations with relevant boundary and continuity conditions were developed to theoretically model the smart pipe joint system subjected to torsion loading. Further, the analytical solutions for the mid-plane displacements and the shear and peel stresses in the adhesive layer were obtained by using the Levy solution and the state-space method. Finally, some numerical examples were presented to evaluate the detailed effect of the stacking sequence and thickness of the integrated composite piezoelectric layers in the connection coupler on reducing the stress concentration in the adhesive layer; the effect of the applied electric fields on shear and peel stresses in the adhesive layer was also illustrated.     

橡胶复合材料结构大变形有限元分析

建立了一个橡胶复合材料结构有限元分析模型。在该模型中 ,考虑了轮胎变形的几何非线性、轮胎与地面和轮胎与轮辋的大变形非线性接触、轮胎材料的非均匀性和物理非线性及橡胶基复合材料的各向异性。此外 ,本文还利用该模型研制的有限元分析软件对全钢丝子午胎的变形轮廓进行了详细的分析。     

Modal theory of elastic-viscoelastic composite structures

The present paper investigates the vibration modal theory of composite structures constructed with elastic and viscoelastic materials. The equation of motion that comes in the form of integrodifferential equations is transformed into the first order differential equation in state space. Then modal analysis is carried out. The concepts of vibrating modal set and creeping modal set are proposed. And impulsive response matrix and transfer function matrix are defined and discussed in detail. Finally sample problems are given to support the theory developed in this paper.     

Indentation failure in composite sandwich structures

A combined analytical and experimental investigation of the indentation failure of a composite sandwich panel has been undertaken. Two cases have been studied: a sandwich panel with carbon/epoxy facing and a PVC foam layer supported on a rigid base and indented at the center with a cylindrical indentor; and a sandwich beam with symmetrical facing and core materials as in the sandwich panels. The load-deflection behavior of the loaded facing was monitored during the test. Strains were also measured near the load on both surfaces of the facing using embedded strain gages. A full-field analysis of the in-plane displacements in the foam was conducted using the moiré method. The problem was modeled as an elastic beam resting on an elastic-plastic foundation. Initiation of indentation failure occurs when the foundation yields, while catastrophic failure takes place when the compression facing fractures. The experimental results are in good agreement with the results of the analytical modeling based on the Winkler foundation.     

Passive damping of prestressed composite structures

This paper presents some analysis techniques to estimate the passive damping ability of viscoelastically damped, fiber-reinforced, polymer composite materials. The potential use of passive damping treatments to further enhance the damping ability of composite structural elements is discussed. Experimental comparisons are provided wherever possible.     

A dropped-weight apparatus for low-speed impact testing of composite structures

A dropped-weight test apparatus has been developed that can be used to perform low-speed impact tests on composite aircraft structures. This vertical drop-weight test apparatus is simple, compact, inexpensive and has precision impact and self-arresting design features similar to the more sophisticated, expensive test machines. The test apparatus has been used to perform low-speed impact response studies on laminated composite plates to understand the influence of impactor and target parameters on structural response and to develop a validated analysis method. Some of the experimental results generated by using this test apparatus for composite laminated plates are presented in the present paper and compared with the corresponding analytical results.     

STAGS computational procedure for progressive failure analysis of laminated composite structures

Non-linear analyses are difficult simulations to perform and place increased demands not only on the computational systems but also on the analyst. The number of possible problems and/or difficulties increases significantly compared to those for linear elastic analyses. Combined material and geometric non-linearities challenge the analyst and the solution algorithms. Progressive failure and damage propagation for composite structures result in even more complexities due to the discrete, abrupt changes in local material stiffness. Analysts need to interrogate the computed solutions carefully based on their understanding of structural mechanics, material behavior, computational procedures and non-linear phenomena to distill correct physics from such simulations. This paper describes the computational strategy incorporated into the STAGS non-linear finite element analysis code with special emphasis on progressive failure analysis of laminated composite structures. Results for selected laminated composite structures are used to demonstrate the PFA capability.     

Micromechanics-based elastic-damage analysis of laminated composite structures

Based on the micromechanics-based constitutive model, derived in our preceding work [Lee, H.K., Pyo, S.H., 2009. A 3D-damage model for fiber-reinforced brittle composites with microcracks and imperfect interfaces. Journal of Engineering Mechanics-ASCE, in press, doi:10.1061/(ASCE)EM.1943.7889.0000039.], incorporating a multi-level damage model and a continuum damage model, the overall elastic behavior and damage evolution of laminated composite structures are studied in detail. The constitutive model is implemented into the finite element program ABAQUS using a user-subroutine UMAT to solve boundary value problems of the composite structures. The validity of the implemented constitutive model is assured by comparing the predicted stress–strain curves with experimental data available in literature under uniaxial tension with various fiber orientations. The results show that the proposed micromechanics-based constitutive model accurately predict the overall elastic-damage behavior of laminated composite structures having different material compositions, thicknesses and boundary conditions.     

Multicriteria optimization of laminated composite material structures

The search for the optimum design of a given structure is a basic aspect of structural analysis. In recent years there has been a renewed interest in structural optimization, particularly in the field of composite material structures. The aim is often to obtain the best solution that is able to respect both the technical and the economic requirements. In this paper, the optimization process is pursued as the determination of the Pareto-optimal curves for composite material structures. The problem has been tackled by means of an analytical optimization methodology (trade-off method) appropriately transformed into a design procedure. A sensitivity analysis is also performed, in order to try out the measure in which the optimal solutions are affected by the variation of the design variables. Two examples are presented, concerning a hemispherical shell and a cylindrical shell.

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Sommario Molti problemi della ricerca dell'ottimo progettuale presentano la difficoltà di coinvolgere nella soluzione più obiettivi da considerare simultaneamente. Il problema risulta piuttosto complesso (in particolare nel caso di strutture in materiale composito) quando gli obiettivi, spesso contrastanti, hanno natura diversa e quindi risultano non facilmente combinabili fra loro. Tale problema si pone spesso quando si vuole da un lato aumentare l'affidabilità strutturale e dall'altro diminuire i costi della struttura. Nel presente articolo, vengono affrontati alcuni aspetti dell'ottimizzazione di strutture in materiale composito: a tale scopo viene presentata una procedura di ottimizzazione per problemi multi-obiettivo che, avvalendosi del Trade-off method, è in grado di determinare la curva degli ottimi di Pareto. Successivamente viene effettuata un analisi di sensitività allo scopo di valutare la sensibilità delle soluzioni ottimali nei confronti della aleatorietà delle variabili di progetto. Vengono presentati in tal senso due esempi relativi a strutture in materiale composito.

     

Progressive fracture of adhesively bonded composite structures

Progressive damage and fracture of adhesively bonded graphite/epoxy composite structures are evaluated via computational simulation. Load induced damage in both the adhesive bond and the adjoining laminate is considered. An integrated computer code is used for the simulation of structural degradation under loading. Damage initiation, growth, accumulation, and propagation to fracture are included in the simulations. Results show in detail the damage progression sequence and structural fracture resistance during different degradation stages. Design implications with regard to damage tolerance of adhesively bonded joints are examined. Influence of the type of loading as well as adhesive thickness on damage initiation and progression for an adhesively bonded composite structure are investigated.