Numerical calculation of the stress-strain state of a composite shell aircraft nacelle structure

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Published: 17-02-2026
DOI: https://doi.org/10.33108/
Keywords:
stress-strain state, finite element method, aircraft nacelle, sandwich composite, numerical modeling, Tsai-Wu criterion

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Mykhailo Prykhodko
National Technical University of Ukraine “Igor Sikorsky Kyiv Polytechnic Institute”
Serhii Pyskunov
National Technical University of Ukraine “Igor Sikorsky Kyiv Polytechnic Institute”
Serhii Trubachev
National Technical University of Ukraine “Igor Sikorsky Kyiv Polytechnic Institute”

Abstract

This paper presents a numerical analysis of the stress-strain state of a composite shell structure of an aircraft engine nacelle using the finite element method (FEM). The central part of the nacelle, modeled as a cylindrical sandwich shell with carbon fiber reinforced polymer (CFRP) laminates as face sheets and a Nomex honeycomb core, is investigated under internal pressure to evaluate its static strength. Particular attention is paid to the mechanical behavior of orthotropic layers and the application of the Tsai-Wu failure criterion for determining the ultimate states. The analysis showed that the maximum values of the failure index (FI) for all layers remain below 1, while the margin of safety (MS) is positive, which confirms the structural integrity and the presence of a sufficient strength reserve under ultimate loading conditions.

Article Details

Issue

Vol. 120 No. 4 (2025)

Section

Articles
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This work is licensed under a Creative Commons Attribution 4.0 International License.

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