Free vibration response of composite sandwich cylindrical shell with flexible core

Rahmani, O.; Khalili, S.M.R.; Malekzadeh, K.

doi:10.1016/j.compstruct.2009.10.021

Cited by 81 publications

(44 citation statements)

References 18 publications

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“…The comparison was made with the analytical solutions based on LW approach (Jam et al 2010, Rahmani et al 2010, the 3D-finite element models also based on LW approach (FEM-3D-LW) (Malekzadeh and Sayyidmousavi 2009, Burlayenko et al 2015), the FEM-Q9 and Q4 solution based on HSDT (Nayak et al 2002) and other analytical solution based on HSDT (Meunier and Shenoi 1999 In this problem, a simply supported square sandwich plate having two laminated stiff layers is investigated. The thickness of each laminate layer is 0.05h, whereas the thickness of the core is 0.8h.…”

Section: Convergence Studymentioning

confidence: 99%

On the Free Vibration Analysis of Laminated Composite and Sandwich Plates: A Layerwise Finite Element Formulation

Belarbi

Tati

Ounis

et al. 2017

Lat. Am. j. solids struct.

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Section: Convergence Studymentioning

confidence: 99%

On the Free Vibration Analysis of Laminated Composite and Sandwich Plates: A Layerwise Finite Element Formulation

Belarbi

Tati

Ounis

et al. 2017

Lat. Am. j. solids struct.

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“…Frostig's 1st model (Rahmani et al, 2009) Error difference(%) ANSYS (Rahmani et al, 2009) Error difference(%)…”

Section: Present Modelmentioning

confidence: 99%

“…Experimental and analytical investigations of bending and free vibration response of layered FG beams were carried out by Kapuria et al (2008), who demonstrated capability of the zigzag theory in modeling mechanics of such beams. Rahmani et al (2009) studied free vibration analysis of open single curved composite sandwich panel with a flexible core using a higher order sandwich panel theory. Their formulation used classical shell theory for the face sheets and an elasticity theory for the core layer.…”

Section: Introductionmentioning

confidence: 99%

Improved high order free vibration analysis of thick double curved sandwich panels with transversely flexible cores

Fard

Livani

Ghasemi

2014

Lat. Am. j. solids struct.

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This paper dealt with free vibration analysis of thick double curved composite sandwich panels with simply supported or fully clamped boundary conditions based on a new improved higher order sandwich panel theory. The formulation used the first order shear deformation theory for composite face sheets and polynomial description for the displacement field in the core layer which was based on the displacement field of Frostig's second model. The fully dynamic effects of the core layer and face sheets were also considered in this study. Using the Hamilton's principle, the governing equations were derived. Moreover, effects of some important parameters like that of boundary conditions, thickness ratio of the core to panel, radii curvatures and composite lay-up sequences were investigated on free vibration response of the panel. The results were validated by those published in the literature and with the FE results obtained by ABAQUS software. It was shown that thicker panels with a thicker core provided greater resistance to resonant vibrations. Also, effect of increasing the core thickness in general was significant decreased fundamental natural frequency values. KeywordsFree vibration, Double curved sandwich panel, Boundary conditions, Improved higher order sandwich panel theory.Improved high order free vibration analysis of thick double curved sandwich panels with transversely flexible cores INTRODUCTIONStructural efficiency is an important attribute for aircraft structures. A higher order theory approach, used by Kant and Patil (1991), replaced sandwich structure with an equivalent higher order shear deformable structure, which lacked the ability to determine local buckling modes and imperfection effects on the overall behavior. Using the three-dimensional elasticity equations, Bhimaraddi (1993) studied the static response of orthotropic doubly curved shallow shells. He assumed that the ratio of the shell thickness to its middle surface radius is negligible as compared to unity. The high- er order sandwich panel theory was developed by Frostig et al. (1994Frostig et al. ( , 2004, who considered two types of computational models in order to express governing equations of the core layer. The second model assumed a polynomial description of the displacement fields in the core that was based on displacement fields of the first model. Their theory did not impose any restrictions on distribution of the deformation through thickness of the core. Singh (1999) studied free vibration of the open deep sandwich shells made of thin layers and a moderately thick core. Rayleigh-Ritz method was also used to obtain natural frequencies. The improved higher order sandwich plate theory (IHSAPT), applying the first-order shear deformation theory for the face sheets, was introduced by Malekzadeh et al. (2005Malekzadeh et al. ( , 2006.

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“…The main aim of this review article is to collate the research performed in the area of dynamic analysis of composite shells during the last 10 years, thereby giving a broad perspective of the state of art in this field. The paper [12] deals with the free vibration analysis of composite sandwich cylindrical shell with a flexible core using a higher order sandwich panel theory. The formulation uses the classical shell theory for the face sheets and an elasticity theory for the core and includes derivation of the governing equations along with the appropriate boundary conditions.…”

Section: Introductionmentioning

confidence: 99%

Effect of external excitation on dynamic characteristics of vibration isolating table

Jurevičius¹,

Turla²,

Бурейка³

et al. 2015

Eksploatacja i Niezawodnosc - Maintenance and Reliability

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Article citation info: IntroductionMost of metrological instruments are sensitive to low-frequency mechanical vibrations and higher frequency -acoustic noise. These oscillations can occur from both outside and inside of the building, i.e. from passing automobiles, wind, heating, ventilation and air-conditioning equipment, and these building vibrations effect on laboratory equipment operation as well. The possibility and method of time varying vibration decomposition are discussed in the scientific workof professor Radkowski [11].Honeycomb sandwich structures are currently being used in various engineering solutions, both within and outside of aerospace engineering. Lightweight honeycomb materials can be used in the construction of composite panels, shells, and tubes with high structural efficiency. The dynamic characteristics of Multilayer Polyurethane foam glass/fiber composite sandwich panels have been determined through Experimental Investigations by Havaldar and others [4].Sandwich shell structures including metal alloys and composites are being increasingly applied to many aircraft, automobile and construction industries due to their lightweight and highly load carrying capacities. Furthermore, the use of cellular cores for panels and shells not only can further reduce the structural weight, but also potentially possess superior heat dissipation, vibration control and energy dissipation characteristics. Filament winding and twice co-curing processes were proposed to make a carbon fiber reinforced composite (CFRC) sandwich cylinder with Kagome cores. Axial compression was carried out to reveal the stiffness and load capacity of the fabricated sandwich cylinder. Compared with the stiffened cylinder with similar dimensions and mass, the sandwich cylinder is shown to be stiffer and stronger by several times [3]. Linear and nonlinear analysis using the ABAQUS finite element is described in paper [15]. Some mechanical properties such as compression, bending, impacting and vibration have been reported by many scientists worldwide. Analytical calculation methods have a clear advantage when designing multi-layered composite cylindrical shells. Compared to Finite Element Methods (FEM) they enable more precise physical interpretations and weighting of the different design variables to be made and, hence, significantly facilitate problem-specified parameter studies and sensitivity analysis [5]. Sandwich cylindrical shells are the major components of aerospace apparatus structures [17]. Nevertheless, an analytical investigation was carried out to examine the response of CFRC sandwich cylinders with lattice cores.Researchers Xiong et al [20] manufactured sandwich-walled cylindrical shells with aluminium pyramidal truss core of constant curva-JUREVICIUS M, TURLA V, BUREIKA G, KILIKEVICIUS A. Effect of external excitation on dynamic characteristics of vibration isolating table. Eksploatacja i Niezawodnosc -Maintenance and Reliability 2015; 17 (2): 260-265, http://dx

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Free vibration response of composite sandwich cylindrical shell with flexible core

Cited by 81 publications

References 18 publications

On the Free Vibration Analysis of Laminated Composite and Sandwich Plates: A Layerwise Finite Element Formulation

On the Free Vibration Analysis of Laminated Composite and Sandwich Plates: A Layerwise Finite Element Formulation

Improved high order free vibration analysis of thick double curved sandwich panels with transversely flexible cores

Effect of external excitation on dynamic characteristics of vibration isolating table

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