Browsing by Author "Chao Correas, A."

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    Analytical development on impact behaviour of composite sandwich laminates by differentiated loading regimes
    (Elsevier, 2022-06-02) Chao Correas, A.; Ghasemnejad, Hessam
    Given the widespread usage of composite components in critical structures within the aerospace and automotive industries, it is deemed as an essential task to determine the effect of normal operation phenomena on its performance in impact. In particular, the present study aims for providing the developed analytical modelling techniques which are needed for describing the low velocity impact dynamic response of sandwich laminated structures. Alongside the analytical models, experimentally validated high-fidelity numerical models are used to check both the validity of the assumptions made as well as the accuracy of the analytical results in the different considered scenarios. An extensive analysis of the sandwich laminate impact performance has been studied, eventually resulting in a much improved, herein developed analytical formulation which is capable of accounting for the differentiated loading, unloading and reloading indentation regimes as well as for the lower facesheet local deflections. These considerations, which are normally neglected in equivalent studies, allow a precise capture of the energy absorption mechanisms.
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    Analytical solutions to predict impact behaviour of stringer stiffened composite aircraft panels
    (Springer, 2021-05-25) Chao Correas, A.; Casares Crespo, A.; Ghasemnejad, Hessam; Roshan, G.
    This paper aims to develop an analytical method to predict the low-velocity impact response of simply supported stringer stiffened panels. Since the combination of stringer and panel provides aircraft structure with variable thicknesses, significant mathematical modelling is required to predict the transverse impact response of this type of designs. Within this analysis, the effect of variable stiffness distribution due to the stringer presence has been included. The performance of various layups is investigated to find the most suitable combination for panel-stringer laminate under impact loading. Analytical models were developed based on a spring-mass system to predict the dynamic behaviour of the striker-plate domain and, finally, determine the contact force history, which shows the main novelty of this research. Compared with Finite Element results, the model developed proved to successfully predict stringer stiffened composite panels' response with a range of layups and geometry designs under low-velocity impact loading conditions. The analytical results agree with the available data in the literature, and the error is less than 5%.