Theory of Laminated Composite Doubly-Curved Shell Structures
01 Jan 2017-
About: The article was published on 2017-01-01. It has received 5 citations till now. The article focuses on the topics: Shell (structure).
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TL;DR: In this article, the free flexural vibration behavior of doubly curved complete and incomplete sandwich shells with functionally graded (FG) porous core, FG carbon nanotube reinforced composite (FG-CNTRC) face sheets and integrated piezoelectric layers is investigated.
Abstract: As a first endeavor, the free flexural vibration behavior of doubly curved complete and incomplete sandwich shells with functionally graded (FG) porous core, FG carbon nanotube reinforced composite (FG-CNTRC) face sheets and integrated piezoelectric layers is investigated. The variable radii shells with the three most common types of geometries, i.e., elliptical, cycloid and parabolic, are considered. The system equations are derived based on the general higher-order shear deformation theory and Maxwell's equation. The generalized differential quadrature (GDQ) method is employed to discretize the governing partial differential equations subjected to different boundary conditions. The accuracy and reliability of the approach are verified by comparing the results with the existing solutions in open literature. The effects of porosity parameter and porosity distribution through the thickness direction, carbon nanotube (CNT) volume fraction, different boundary conditions and various shell geometrical parameters on the flexural vibrational behavior of the smart sandwich shell structures are investigated and useful results are presented.
82 citations
TL;DR: In this paper, the authors investigated the response behavior of moderately thick hyperbolic paraboloidal laminated shells using C0 finite element formulations based on Higher order Shear Deformation Theory (HSDT).
5 citations
TL;DR: In this paper, a C0 finite element formulation using eight noded isoparametric shell element with seven degrees of freedom per node is applied to evaluate the dynamic response of shells.
Abstract: Transient response behavior of laminated doubly curved shells with varying geometry and boundary conditions subjected to various time-dependent pulse loads is investigated using Higher order Shear Deformation Theory (HSDT) in the present study. The ratio of thickness co-ordinate to radius of shell (z/R) is incorporated in the mathematical formulation based on HSDT. The condition of zero transverse shear stresses at free surfaces of laminated shell is also included in the displacement function. A C0 finite element formulation using eight noded isoparametric shell element with seven degrees of freedom per node is applied to evaluate the dynamic response of shells. Three types of pulse loading such as sine, triangular and rectangular pulses are considered for the present investigation. Newmark's β method is applied to solve the dynamic equilibrium equation of the shells. The accuracy of the present analysis is examined by comparing the results obtained with those available in the published literature. Several numerical examples are illustrated to show the effects of pulse loading and boundary condition on the central displacement and stresses of laminated composite shells.
2 citations
TL;DR: In this article, the authors focused on the deflection of the electrode, consisting of a current collector and an electrode film on the current collector, to confirm the durability and reliability of lithium-ion batteries.
TL;DR: In this paper , an analytical solution was developed in order to obtain the critical buckling load for a doubly-curved composite laminate under compression, shear, moment or any combination of the three loads.
Abstract: Curved panels are structural elements that form the skin of wings, fuselages and tail booms in aircraft. Buckling of these structures would adversely affect aircraft performance. Due to this, the problem of buckling has been extensively researched in the past. Most of the research has been restricted to the analysis of flat composite panels and analysis of curved panels through simplifications involving geometry, material properties and boundary conditions. The present study aims to develop an analytical solution that can predict the critical buckling load for a wider range of problems. An analytical solution was developed in order to obtain the critical buckling load for a doubly-curved composite laminate under compression, shear, moment or any combination of the three loads. The assumptions of the classical laminate plate theory were used in order to obtain the displacement fields as well as strains of the laminate. The energy method was employed in order to obtain the critical buckling load for various load cases. The values obtained through the analytical solution are compared to the critical buckling loads obtained through finite element analysis (FEA). The highest deviation of critical buckling load from FEA was calculated to be 16.55%. Variation of the critical buckling load with respect to the radius of curvature, boundary conditions and stacking sequence was analyzed. The developed solution was also found to be valid for cases when radii of curvatures are unequal as well as when the length and breadth of laminate are unequal.