Numerous rivets have to be modelled for aeronautical framework crashes. A n
umerical procedure based on FE modelling and characterisation of material f
ailure constitutive models is proposed in order to limit the experimental p
rocedure. Quasi-static and dynamic experiments are carried out on elementar
y tension (punched) and shear (riveted) specimens. No strain rate sensitivi
ty has been measured on the riveted joint assemblies failure. The experimen
ts are used to identify, by an inverse method, the Gurson damage parameters
of each material (2024-T351 and 7050 aluminium alloys for the sheet metal
plate and the rivet). The characterisation gives rise to a satisfactory cor
relation between FE models and experiments. Optimised parameters are valida
ted for each material by means of a uniaxial tension test for the sheet met
al plate and an ARCAN type specimen in pure tension for the rivet. Results
can then be used to identify macroscopic failure criterion to model the riv
et behaviour in aeronautical framework crashes. FE tools can also resolve p
roblems linked to limit-design or the design of new riveted joint assemblie
s more rapidly and cost effectively than experiments. (C) 1999 Editions sci
entifiques et medicales Elsevier SAS.