Sandwich structures consisting of contact-aided compliant mechanisms are presented for morphing aircraft skin. A contact mechanism is used to alleviate stresses and to decrease the oul-of-plane deflection. A methodology to design such mechanisms, which takes into account the aerodynamic loads, is presented. The method is applied to a small UAV and results are compared with those of honeycomb structures in terms of structural mass, global strain and maximum stresses. Different material models such as linearly elastic and multi-linear elastic are considered. For linearly elastic materials, contact-induced stress-relief is advantageous and for nonlinear elastic materials, reduction of transverse deflection due to contact is useful. In either ease, the structural mass of the contact-aided structures is less than that of the corresponding non-contact structures.