3. Conclusion

The fuselage, an essential structural element of a transport aircraft, is mainly designed for pressurization. Under steady-state conditions, the membrane fluxes induced in the skins define the fatigue durability of the structure around discontinuities (openings, fasteners, assemblies). In the transient regime, the loads defined in this article are used to define the current skin thickness verifying the elastic limit and rupture criteria. In the initial climb and final descent phases, i.e. excluding pressurization, it is the bending of the fuselage that requires a stability calculation (local buckling), the loads of which include the maneuvering load factor.

The elements presented in this article enable pre-dimensioning in the linear domain or at the limit of the linear domain, and present the main technologies used in the design and dimensioning of fuselage shells....