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

  • Structural Mechanics and Strength of Flight Vehicles
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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.

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Authors and Affiliations

  1. Moscow Aviation Institute (National Research University), Volokolamskoe shosse 4, Moscow, 125993, Russia

    V. G. Dmitriev, V. I. Biryukov, O. V. Egorova & L. N. Rabinskii

  2. Institute of Applied Mechanics, Russian Academy of Science, prt. Leningradskii 7, Moscow, 125040, Russia

    S. I. Zhavoronok

Authors
  1. V. G. Dmitriev
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  2. V. I. Biryukov
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  3. O. V. Egorova
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  4. S. I. Zhavoronok
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  5. L. N. Rabinskii
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Additional information

Original Russian Text © V.G. Dmitriev, V.I. Biryukov, O.V. Egorova, S.I. Zhavoronok, L.N. Rabinskii, 2017, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2017, No. 2, pp. 8–15.

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Dmitriev, V.G., Biryukov, V.I., Egorova, O.V. et al. Nonlinear deforming of laminated composite shells of revolution under finite deflections and normal’s rotation angles. Russ. Aeronaut. 60, 169–176 (2017). https://doi.org/10.3103/S1068799817020027

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  • DOI: https://doi.org/10.3103/S1068799817020027

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