This chapter focuses on composite bar/beam elements with different layers. Based on a generalized stress-strain relationship, the calculation steps based on the simplified classical laminate theory are introduced. The simplifications come from the application of one-dimensional members and the treatment of each single layer as an isotropic material. Based on the internal reactions, i.e. the internal normal force and the internal bending moment, the strain and stress distribution in each single layer can be evaluated. These values may serve then for a subsequent failure analysis based on different criteria.