Analysis of Compressive Behaviour of Pristine and Cracked 5-Stringer Butt-Joint Panels made from Carbon Fibre Reinforced Thermoplastic Polymer

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F23%3AN0000004" target="_blank" >RIV/00010669:_____/23:N0000004 - isvavai.cz</a>

Result on the web

<a href="https://www.sciencedirect.com/science/article/pii/S2452321622006072" target="_blank" >https://www.sciencedirect.com/science/article/pii/S2452321622006072</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.prostr.2022.12.050" target="_blank" >10.1016/j.prostr.2022.12.050</a>

Result language

angličtina

Original language name

Analysis of Compressive Behaviour of Pristine and Cracked 5-Stringer Butt-Joint Panels made from Carbon Fibre Reinforced Thermoplastic Polymer

Original language description

The FE analysis of 5-Stringer Butt-Joint Panel made from carbon fibre reinforced thermoplastic polymer (CFRTP) loaded in compression is introduced. The panel is intended to rotorcraft tail and demonstrates the alternative to CFRP panels made from fabrics by common laminate process. The pristine and cracked (initially delaminated) panels were investigated. Several methods to analyse panel’s behavior, i.e., buckling and strength, are introduced and compared each other. Simple finite element (FE) model was created as basic. The other, advanced detailed multi-layered model was generated by ABAQUS plug-in PbPModGen so that each composite layer was represented by a layer of finite elements. Cohesive elements (CZM) were applied to join the subparts of the panel. Buckling mode shapes and eigenvalues were determined by linear (eigenvalue) analysis using simple FE model. Explicit nonlinear solver was used to study gradual buckling development for both, simple and detailed model. The effect of initial delamination between central stringer and the skin was analysed. Local skin buckling in the delaminated area was found in addition to pristine panel and caused lower strength of the panel. Compared to the test results, the simple FE model is good choice to deal with buckling. On the contrary, the mode of panel failure was captured only by detailed multilayered model with the lower load of 3% for pristine and 9% for cracked panel. The collapse occurred after local debonding of one stringer from the skin with its subsequent breakage and failure extension to other stringers. The presented work introduces buckling and post-buckling behaviour assessment, shows the effect of a crack on the compressive strength and compares several methods of solution.

Czech name

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Czech description

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Type

J_SC - Article in a specialist periodical, which is included in the SCOPUS database

CEP classification

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OECD FORD branch

20505 - Composites (including laminates, reinforced plastics, cermets, combined natural and synthetic fibre fabrics; filled composites)

Project

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Continuities

R - Projekt Ramcoveho programu EK

Publication year

2023

Confidentiality

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Name of the periodical

Structural Integrity Procedia

ISSN

2452-3216

e-ISSN

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Volume of the periodical

42

Issue of the periodical within the volume

7/2022

Country of publishing house

CZ - CZECH REPUBLIC

Number of pages

6

Pages from-to

398-403

UT code for WoS article

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EID of the result in the Scopus database

2-s2.0-85159027968