Patent ID: 8640990

Claim:
A circumferential stiffener configured for a fuselage of an aircraft, the circumferential stiffener comprising: a stiffening profile comprising: a web disposed at an angle to a normal axis of the circumferential stiffener; at least one inner flange; at least one outer flange; and an integral angle profile including a foot plate configured for connection to a skin section of the fuselage and an arm which extends away from the foot plate to a free end section, wherein the free end section translates integrally into the stiffening profile such that the stiffening profile is configured to be spaced away from the skin of the fuselage, and wherein a shear center of the circumferential stiffener, as viewed from a lateral direction of the aircraft, is positioned between a surface center of gravity of the foot plate and a surface center of gravity of the web.