THE ISSUE OF RESIDUAL STRENGTH TESTS OF THIN FIBRE METAL LAMINATES

摘要: Modern aircraft structures contain sheathing elements which are supposed to not only carry loads, e.g static ones, but also at the same time possess resistance corrosion or dynamic impact. As a consequence, new kinds of hybrid materials, fibre metal laminates, were created. They combine mechanical and physical properties various materials. Until now, most common widespread GLARE® laminates (aluminium/glass-epoxy composites), characterised by high fatigue properties, as well impact resistance. The concurrent influence many negative factors during exploitation causes gradual decrease in functional these One affecting e.g. strength is low-velocity Low-velocity often leads macroscopically invisible damage composite structure, with delaminations ply cracking occurring energy absorption. Fibre much better load-carrying capacity, limiting absorbing some through elastic-plastic deformation. In order assess on residual Compression After Impact (CAI) tests carried out. Normalised CAI testing used for classic 5 mm thick structures. However, literature suggests, it effective case particularly those thickness more then 1.1 mm. work presents an analysis possibility conducting (ensuring valid assessment reduction) test 1.5 FML panels after An alternative workstation construction was proposed, simulations experimental verifications conducted. It observed that solution based ASTM standard does apply thin laminated panels. Deformation specimen occurs areas located far from site. values differ neither plates impact-induced nor ones without it. proposed holder compression eliminates premature material damage. On basis conducted numerical simulations, stated using occurrence first buckling mode area, stress concentration its vicinity. Such form deformation may allow one correctly composites.