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<p>The article presents the results of research work performed under the TEBUK project, aiming primarily to develop a reference methodology for assessing the impact of damage on the strength of structures made of carbon epoxy prepregs. The tests described in the paper were concerned with a fragment of the structure (FS) of the TEBUK project demonstrator, made of carbon epoxy composite, with an artificial circular delamination measuring 40 mm in diameter. Numerical and experimental test of FS have been performed under quasi-static compression load. The buckling of the skin observed in the delamination area, as well as the propagation of the latter were investigated. The numerical calculations have been performed with the use of the commercially available MSC Marc/Mentat calculation suite based on the Finite Elements Methods. Results of the numerical calculations have been compared with experimental measurements made with the use of the Digital Image Correlation (DIC) method. The tests performed aimed to provide a preliminary verification of the numerical model. The results obtained have shown a very good correlation between the numerical and experimental results concerned with critical load levels at which stability of the layers separated by delamination is lost (buckling). The lack of convergence of the numerical model’s results after exceeding the critical load values has rendered it impossible to unequivocally compare the results concerned with propagation of the delamination area.</p>
</abstract>

The article presents the results of research work performed under the TEBUK project, aiming primarily to develop a reference methodology for assessing the impact of damage on the strength of structures made of carbon epoxy prepregs. The tests described in the paper were concerned with a fragment of the structure (FS) of the TEBUK project demonstrator, made of carbon epoxy composite, with an artificial circular delamination measuring 40 mm in diameter. Numerical and experimental test of FS have been performed under quasi-static compression load. The buckling of the skin observed in the delamination area, as well as the propagation of the latter were investigated. The numerical calculations have been performed with the use of the commercially available MSC Marc/Mentat calculation suite based on the Finite Elements Methods. Results of the numerical calculations have been compared with experimental measurements made with the use of the Digital Image Correlation (DIC) method. The tests performed aimed to provide a preliminary verification of the numerical model. The results obtained have shown a very good correlation between the numerical and experimental results concerned with critical load levels at which stability of the layers separated by delamination is lost (buckling). The lack of convergence of the numerical model’s results after exceeding the critical load values has rendered it impossible to unequivocally compare the results concerned with propagation of the delamination area.

Experimental Verification of Numerical Calculations with the Use of Digital Image Correlation

Transactions on Aerospace Research

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

The article presents the results of research work performed under the TEBUK project, aiming primarily to develop a reference methodology for assessing the...

Experimental Verification of Numerical Calculations with the Use of Digital Image Correlation

Pubblicato online: 03 set 2019

Pagine: 1 - 15

DOI: https://doi.org/10.2478/tar-2018-0011

Parole chiave
digital image correlation, FEM, delamination, buckling, carbon-epoxy laminate

© 2017 Copyright by Lukasiewicz Research Network – Institute of Aviation

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Experimental Verification of Numerical Calculations with the Use of Digital Image Correlation

Pubblicato online: 03 set 2019

Pagine: 1 - 15

DOI: https://doi.org/10.2478/tar-2018-0011

Parole chiavedigital image correlation, FEM, delamination, buckling, carbon-epoxy laminate

© 2017 Copyright by Lukasiewicz Research Network – Institute of Aviation

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Parole chiave
digital image correlation, FEM, delamination, buckling, carbon-epoxy laminate