The presented work, within the framework of the European research project MAAXIMUS (More Affordable Aircraft through eXtended, Integrated and Mature nUmerical Sizing), is dedicated to the numerical simulation of assemblies with components made of laminated composites. These assemblies involve two types of high non-linearities. First ones are linked to the interfaces between parts (unilateral contact and friction). Second ones are linked to the constitutive material behaviour, from its initial properties to the complex evolution of degradations. These two non-linearities have a strong influence on the response of the assembly, which involves solving systems with a high number of degrees of freedom and generally requires the use of parallel computing resources.The coupling between the two sources of non-linearities requires dedicated and robust algorithms, able to run on parallel architectures and to deal with many very strong non-linearities. The efficiency of the LATIN method (LArge Time INcrement) has already been highlighted in the case of assemblies with elastic components. A first aim of this work is thus to extend the method to the case of damageable and anelastic components' behaviour.A second aim is to deal with the variability of the coefficients involved in the non-linear laws. Each set of parameters (friction coefficients, preload of fasteners, damage threshold of material laws...) requiring a given calculation, the multiparametric strategy of the LATIN method must be extended to the case of non-linear materials in order to efficiently reduce the computation time.
