Abstract The discretization of the boundary value problem for laminated composite shells is based on the finite difference approach using the regular mesh with the constant grid step and the difference operators of the second order of accuracy. The dynamic relaxation method is proposed for the solution of the nonlinear problem. The evolutionary equations of the dynamic relaxation are constructed, and the optimum parameters of the converging linear iterative process are estimated.
Nonlinear deforming of laminated composite shells of revolution under finite deflections and normal’s rotation angles
Russian Aeronautics ; 60 , 2 ; 169-176
2017-04-01
8 pages
Article (Journal)
Electronic Resource
English
Calculation of finite axisymmetric deflections of thin short shells of revolution
British Library Online Contents | 1996
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