A. Manes, A. Gilioli, M. Giglio

DOI Number: N/A

Conference number: IFASD-2017-125

This paper is aimed at the investigation on the building of accurate numerical structural model aimed to investigate in the Limit Cycle Oscillation (LCO) phenomenon which is an actual issue on several aircraft configurations and which is generally encountered in external store configurations that are theoretically predicted to be flutter sensitive. Primary tools used in the industry are based on linearized and reduced order models. These models exhibit great difficulties in the prediction and reproduction of LCO most likely due to non-linear effects. Therefore, in the present paper, a numerical non-linear Finite Element Model (FEM) has been built in order to reproduce the mechanical behaviour of a representative structure of an aircraft pylon. Particular attention has been paid to highlight the sources of non-linearity: the friction between the spring and the payload has been identified as the main cause of the nonlinear behaviour.

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In Categories: 1. IFASD 2017, 1.Events, Computational Aeroelasticity
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