The structural performance of an aircraft seat back frame, mainly made of unidirectional carbon/epoxy laminates, has been simulated using the finite element (FE) method. The loading case is a certification test named 'side-test'. The FE analysis is linear elastic, based on classical lamination theory; contact between the loading parts and the seat back frame was modelled. First-ply-failure prediction, and the static deformation characteristics were both predicted. There is good agreement (load level and failure initiation site) between the computational predictions and the laboratory experiments. All the seat back frames tested in this test program passed the certification 'side test'. The finite element model used in this study successfully predicted the mechanical response of the seat under the side test. This model can be used in order to optimise the seat back frame layup sequence. The qualitative description of the failure path allowed weaker areas in the seat back frame to be identified.
Design and performance of a lightweight composite seat for civil aircraft applications
2002
7 Seiten, 17 Bilder, 1 Tabelle, 1 Quelle
Aufsatz (Konferenz)
Datenträger
Englisch