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Numerical study of fatigue damage accumulation in composite wing panels of prospective supersonic transport aircraft

Numerical study of fatigue damage accumulation in composite wing panels of prospective supersonic... In this paper, the patterns of fatigue damage accumulation for a stringer panel and a panel with lattice reinforcement made of a polymer composite material (PCM) were studied using the Wim Van Paepegem calculation method. Both panels have the same overall dimensions, are made of the same material and are designed to carry the same compressive load. Based on the results of the calculations, the zones were determined in which the greatest loss of stiffness occurs in one of the components for both types of panels. The number of cycles to complete loss of stiffness for these components for each of the zones was obtained. It was found that in the stringer panel, the greatest loss of stiffness occurs in the layers of the stringer web and in the panel with lattice reinforcement in the zone where the diagonal ribs intersect. At the same time, it was found that in a lattice panel, these fatigue damage occurs under a smaller number of applied cycles than in a stringer panel. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aerospace Systems Springer Journals

Numerical study of fatigue damage accumulation in composite wing panels of prospective supersonic transport aircraft

Turbin, N. V.; Shelkov, K. A.
Aerospace Systems , Volume OnlineFirst – Mar 1, 2023
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10 pages

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Publisher
Springer Journals
Copyright
Copyright © Shanghai Jiao Tong University 2023. Springer Nature or its licensor (e.g. a society or other partner) holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2523-3947
eISSN
2523-3955
DOI
10.1007/s42401-023-00200-1
Publisher site
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Abstract

In this paper, the patterns of fatigue damage accumulation for a stringer panel and a panel with lattice reinforcement made of a polymer composite material (PCM) were studied using the Wim Van Paepegem calculation method. Both panels have the same overall dimensions, are made of the same material and are designed to carry the same compressive load. Based on the results of the calculations, the zones were determined in which the greatest loss of stiffness occurs in one of the components for both types of panels. The number of cycles to complete loss of stiffness for these components for each of the zones was obtained. It was found that in the stringer panel, the greatest loss of stiffness occurs in the layers of the stringer web and in the panel with lattice reinforcement in the zone where the diagonal ribs intersect. At the same time, it was found that in a lattice panel, these fatigue damage occurs under a smaller number of applied cycles than in a stringer panel.

Journal

Aerospace Systems – Springer Journals

Published: Mar 1, 2023

Keywords: Fatigue strength; Durability; Lattice panel; Stringer panel; FEM

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