Analysis and Parametric Study of Non-Circular Pressurized Sandwich Fuselage Cross Section Using a High-Order Sandwich Theory Formulation

Abstract

Results obtained as part of a design study regarding a non-circular pressurized sandwich fuselage cross section are presented. The originating problem is associated with preliminary studies for the “Global Range Transport” envisaged by the “New World Vistas” program of the United States Air Force. The modeling and analysis is conducted using a high-order sandwich theory formulation in which the elastic response of each face laminate is accounted for, including bending-stretching coupling, and including the transverse flexibility of the core material. The paper includes a presentation of the high-order sandwich theory approach adopted for the analysis of the fuselage section, including the formulations for flat and curved sandwich panels. The paper is concluded by presentation of the results of a parametric study, which includes the effects on the structural response of varying the sandwich panel mid-plane asymmetry, the core properties, and the radius of curvature of the fuselage cross section corners.