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

Kód výsledku v 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>

Výsledek na webu

<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>

Jazyk výsledku

angličtina

Název v původním jazyce

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

Popis výsledku v původním jazyce

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.

Název v anglickém jazyce

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

Popis výsledku anglicky

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.

Druh

J_SC - Článek v periodiku v databázi SCOPUS

CEP obor

—

OECD FORD obor

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

Projekt

—

Návaznosti

R - Projekt Ramcoveho programu EK

Rok uplatnění

2023

Kód důvěrnosti údajů

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

Název periodika

Structural Integrity Procedia

ISSN

2452-3216

e-ISSN

—

Svazek periodika

42

Číslo periodika v rámci svazku

7/2022

Stát vydavatele periodika

CZ - Česká republika

Počet stran výsledku

6

Strana od-do

398-403

Kód UT WoS článku

—

EID výsledku v databázi Scopus

2-s2.0-85159027968