Patent ID: 8439307

Claim:
A fuselage structure for an aircraft or spacecraft, comprising: an outer skin having an arc-shaped inner curvature; and a structural component, the structural component comprising: a rib element formed in the shape of an arc corresponding to the inner curvature of the outer skin; a cross member element, transversely connecting at least two arc sections of said arc-shaped rib element to each other, wherein the cross member element has a higher stiffness than the rib element; an energy absorbing element, connecting a load introduction zone of the rib element to an opposing section of the cross member element, wherein the energy absorbing element comprises at least one of a closed circular profile, a closed elliptical profile, a half-closed Ω-shaped profile, a semi-circular profile, or a semi-elliptical profile; and a coupling element which couples at least one arc section of the rib element to a stiffening element, wherein the coupling element has a mechanical strength which is lower than a mechanical strength of the stiffening element.