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

V. G. Dmitriev; V. I. Biryukov; O. V. Egorova; S. I. Zhavoronok; L. N. Rabinskii

doi:10.3103/S1068799817020027

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

Авторы: Dmitriev V.G.¹, Biryukov V.I.¹, Egorova O.V.¹, Zhavoronok S.I.², Rabinskii L.N.¹
Учреждения:
1. Moscow Aviation Institute (National Research University)
2. Institute of Applied Mechanics
Выпуск: Том 60, № 2 (2017)
Страницы: 169-176
Раздел: Structural Mechanics and Strength of Flight Vehicles
URL: https://journals.rcsi.science/1068-7998/article/view/230059
DOI: https://doi.org/10.3103/S1068799817020027
ID: 230059

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Аннотация

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.