Nonlinear deforming of laminated composite shells of revolution under finite deflections and normal’s rotation angles

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 th...

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Bibliographic Details
Published in:Russian aeronautics 2017-04, Vol.60 (2), p.169-176
Main Authors: Dmitriev, V. G., Biryukov, V. I., Egorova, O. V., Zhavoronok, S. I., Rabinskii, L. N.
Format: Article
Language:English
Subjects:
Automotive Engineering
Engineering
Structural Mechanics and Strength of Flight Vehicles
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Summary: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.
ISSN:1068-7998
1934-7901
DOI:10.3103/S1068799817020027