Patent ID: 8262024

Claim:
A reinforcing frame ( 1 ) of the fuselage ( 2 ) of an aircraft, said fuselage ( 2 ) comprising a skin ( 3 ) and stringers ( 20 ), characterized in that it comprises a structural member ( 4 ) and a closed, internally hollow honeycomb member ( 5 ), the structural member ( 4 ) comprising a lower base ( 6 ) which is arranged on the inner face of the skin ( 3 ) of the fuselage ( 2 ), and through which the stringers ( 20 ) connecting the frames ( 1 ) to the rest of the structure of the fuselage ( 2 ) pass, and upper reinforcing members ( 7 ) on which the mentioned honeycomb members ( 5 ) are arranged, such that the honeycomb members ( 5 ) increase the inertia and the stiffness of the frame ( 1 ) without adding weight thereto, the frame ( 1 ) having high stiffness in the transverse direction, in addition to being intrinsically stable against local buckling.