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Spring-in prediction for carbon/epoxy aerospace composite structure

Abstract : This paper presents an engineering method to predict the spring-back of aircraft thick composite structures produced through an autoclaving process. The model previously developed by the same authors is firstly enhanced to be used in an aeronautic case study: an Airbus A350 rib. Results show that the out-of-plane shear stress distribution in the interface and the through-thickness in-plane normal stress gradient of the laminate are correctly represented. The interface is shown to have only a small influence on the final deformation and therefore a global model of the structure can be proposed. Finally a methodology is proposed to predict complex structures through a global-local approach.
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Contributor : Pierre Naegelen <>
Submitted on : Tuesday, December 11, 2018 - 9:15:15 AM
Last modification on : Wednesday, June 24, 2020 - 4:18:55 PM


  • HAL Id : hal-01950756, version 1


M. Fiorina, A. Seman, Bruno Castanié, K. M. Ali, C. Schwob, et al.. Spring-in prediction for carbon/epoxy aerospace composite structure. Composite Structures, Elsevier, 2017, 168, pp.739--745. ⟨hal-01950756⟩



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