Finite Element Model Update of an Aircraft Interior Lining Panel

Abstract

In aviation, new propulsion concepts and aircraft configurations are explored to reduce the carbon footprint. Turboprop engines experience a comeback in hydrogen powered aircraft concepts. Compared to conventional aircraft with jet engines, there are changes in noise sources and vibro-acoustic transfer paths. The calculation of these transfer paths should therefore be carried out at the preliminary design phase of a new aircraft to assess the noise exposure of the passengers.

DLR developed a process to automatically generate finite element (FE) models of an aircraft fuselage based on preliminary design data. These models enable the calculation of noise transmission from the source to the passenger's ears. For the enhancement and validation of model parameters, parts with a major influence on the noise transmission are analyzed. This article presents such a process for a commercial aircraft lining panel. The component is subjected to a modal testing with free-free boundary conditions. Experimental data of several tests are composed and modal data are extracted. Based on a 3D scan of the lining panel a FE model is set up. A model update process with Ansys optiSLang improves numerous geometric and material parameters.