Nonlinear Fracture Resistance Parameters for Elements of Aviation Structures under Biaxial Loading
- Authors: Shlyannikov V.N.1,2, Zakharov A.P.1, Tumanov A.V.1
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Affiliations:
- Kazan Science Center of RAS
- Tupolev Kazan National Research Technical University
- Issue: Vol 61, No 3 (2018)
- Pages: 340-346
- Section: Structural Mechanics and Strength of Flight Vehicles
- URL: https://journals.rcsi.science/1068-7998/article/view/230579
- DOI: https://doi.org/10.3103/S1068799818030042
- ID: 230579
Cite item
Abstract
This study is concerned with practical application of nonlinear deformation and fracture resistance parameters for residual durability estimation of the fuselage elements with operation damage. By means of numerical calculations for the fragment of fuselage skin with central crack the governing parameters of the elastic-plastic crack-tip stress field are determined as a function of biaxial loading. Two variants of modeling of the crack-tip stress field were performed for the panel of homogeneous isotropic material and a set of the special cohesive elements. As a result the assessment of the biaxial loading influence of fracture damage zone state on crack tip stress field in fuselage panel is given.
About the authors
V. N. Shlyannikov
Kazan Science Center of RAS; Tupolev Kazan National Research Technical University
Email: alex.zakharov88@mail.ru
Russian Federation, ul. Lobachevskogo 2/31, Kazan, 420111; ul. Karla Marksa 10, Kazan, 420111
A. P. Zakharov
Kazan Science Center of RAS
Author for correspondence.
Email: alex.zakharov88@mail.ru
Russian Federation, ul. Lobachevskogo 2/31, Kazan, 420111
A. V. Tumanov
Kazan Science Center of RAS
Email: alex.zakharov88@mail.ru
Russian Federation, ul. Lobachevskogo 2/31, Kazan, 420111