Modal parameter identification of a compression-loaded CFRP stiffened plate and correlation with its buckling behaviour
作者： M. Chaves-Vargas , A. Dafnis , H.-G. Reimerdes , K.-U. Schröder
DOI: 10.1016/J.PAEROSCI.2015.05.009
关键词: Structural engineering 、 Compression (physics) 、 Buckling 、 Fuselage 、 Finite element method 、 Tailplane 、 Modal 、 Modal analysis 、 Wing 、 Engineering 、 Mechanical engineering 、 Mechanics of Materials 、 Aerospace engineering
摘要: Abstract In order to study the dynamic response and buckling behaviour of several load-carrying structural components civil aircraft when subjected transient load scenarios such as gusts or a landing impact, generic mid-size is defined within European research project DAEDALOS. From this aircraft, sections panels in different regions wing, vertical tailplane fuselage are defined. The stiffened carbon-fibre-reinforced plastic (CFRP) plate investigated present work represents simplified version wing panel selected from aircraft. As part current work, modal properties under effect static in-plane compression studied. This accomplished by means test series including quasi-static tests an experimental analysis (EMA). One key objectives pursued correlation studying relationship between natural frequencies its corresponding load. verified finite element analysis.
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