Abstract

This work summarizes the recent developments of a numerical framework to predict the mechanical behaviour of thermoplastic composites. It supports the design of a next generation thermoplastic multi-functional fuselage which uses advanced joining techniques such as thermoplastic welding to reduce both weight and cost by limiting the amount of mechanical fasteners required. At the lower end of the testing pyramid the framework is able to accurately predict typical preliminary design allowables such as laminate, open-hole and welded joints strength through a high-fidelity modelling approach. This information is then passed on to the structural level in a validated building-block approach to efficiently virtual test the compression strength of fuselage panels during post-buckling while also taking into account the influence of damages at the skin-stiffener interface.

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References

[1] Falco, O., Ávila, R.L., Tijs, B. and Lopes, C.S. Modelling and simulation methodology for ´ unidirectional composite laminates in a Virtual Test Lab framework. Composite Structures (2018) 190:137–159.

[2] Tijs, B.H.A.H., Turon, A. and Bisagni, C. The importance of accounting for large shear deformation on modelling matrix failure of thermoplastic and thermoset composites. Proceedings of the 7th ECCOMAS Thematic Conference on the Mechanical Response of Composites(COMPOSITES 2019), Girona, Spain, Sept. 18-20 (2019).

[3] van Dooren, K.S., Labans, E., Tijs, B.H.A.H., Waleson, J.E.A., and Bisagni, C. Analysis and testing of a thermoplastic composite stiffened panel under compression. Proceedings of the 22nd International Conference on Composite Materials (ICCM22), Melbourne, AU, Aug. 11-16 (2019).

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Document information

Published on 15/02/21
Accepted on 15/02/21
Submitted on 15/02/21

DOI: 10.23967/emus.2020.005
Licence: CC BY-NC-SA license

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