An exact solution for the free vibration analysis of laminated composite cylindrical shells with general elastic boundary conditions

Application of layered finite elements in the numerical analysis of laminated composite and sandwich structures with delaminations

“…Kako bi se preciznije uzelo u obzir krivljenje popre nog preseka, Reddy [14] je razvio smi u u teoriju plo a višeg reda (HSDT), gde je polje pomeranja po visini popre nog preseka aproksimirano kubnom funkcijom koordinate u pravcu debljine plo e. U prethodnim radovima [15], Vuksanovi je koristio kona ne elemente bazirane na jednoslojnom modelu plo a višeg reda za prora un stati kog i dinami kog odgovora neošte enih kompozitnih plo a. Pored primene u analizi laminatnih kompozitnih plo a, kona ni elementi bazirani na HSDT primenjeni su i u analizi kompozitnih sendvi -panela, u radovima [16][17]. Metod diferencijalne kvadrature (DQ) kao i opšti metod diferencijalne kvadrature (GDQ) tako e su primenjeni za prora un sopstvenih frekvencija laminatnih kompozita [18][19][20][21][22], uz neka analiti ka rešenja [23][24][25][26][27].…”

“…Beside the application to the analysis of laminated composite plates, finite elements based on the HigherOrder Shear Deformation Theory were applied in the analysis of composite sandwich plates, in works of Nayak et al [16][17]. The method of differential quadrature as well as Generalized Differential Quadrature Method (GDQ) was also used for the calculation of natural frequencies of laminated composite structures [18][19][20][21][22], along with some analytical solutions [23][24][25][26][27].…”

A New Finite Element Formulation for Nonlinear Vibration Analysis of the Hard-Coating Cylindrical Shell

“…The cylindrical shell has been widely used in the aviation and aerospace fields, especially in the aero engine and aircraft, which have an urgent demand to restrain their excessive vibration [1]. It is well known that the hard-coating treatment has found application in many engineering applications, such as the blades of gas turbines, new turbofans, cylindrical shell structures of the aero engine and other structures.…”

Vibrations of Composite Laminated Circular Panels and Shells of Revolution with General Elastic Boundary Conditions via Fourier-Ritz Method

“…Later, the method fast extended to cope with other structures (i.e. beams, plates, shells and coupled structures) by the Du [27][28][29][30], Jin [31][32][33][34][35][36][37][38][39][40][41][42][43][44][45][46], Wang et al [47][48][49][50][51][52] in the last ten years due to the superiority compared with other methods. The detailed theoretical analyses and mathematical principle can been seen in Refs [24][25][26].…”