The aeronautical sector needs to optimize the weight of its structures without losing their functions. Nowadays, with the expansion of the additive manufacturing technologies, it is possible to satisfy the most extreme requirements of the lightweight design. This is often done thanks to lattice structures. In this thesis, a real application is described. It is a de-icing system for aircrafts constituted by a sandwich panel with a lattice core and patented by Politecnico di Torino. This thesis is focussed on the structural behaviour of the reticular frame under a static compression load. A general analytical method, which neglects the edge effects and is based on beam’s theory, is exposed.