The paper is concerned with the safety factor for geodesic composite lattice aircraft structures. Lattice structures, in contrast to traditional stringer structures, consist of systems of ribs which are the basic load-carrying elements of the structure, where as a thin skin does not take the load. Because lattice composite structures are fabricated by filament winding of unidirectional carbon-epoxy composite material with high specific (with respect to density) strength and stiffness, these structures are characterized with high weight and cost efficiency and demonstrate high potentials in application to aircraft structures. Thus, the study of reliability of composite lattice structures is of some practical interest.