  In order to save mass of satellite solar arrays, the flexibility of the
panels becomes not negligible and they may strike each other; this may damage
the structure. To prevent this, rubber snubbers are mounted at well chosen
points of the structure and they act as one sided linear spring; as a negative
consequence, the dynamic of these panels becomes nonlinear. The finite element
approximation is used to solve partial differential equations governing the
structural dynamic. Frequency sweep has been performed numerically to study the
dynamic behavior. Non linear normal modes are under study
