Patent ID: 8276848

Claim:
A rib structure for a torsion box of an aircraft wing or a horizontal stabiliser which comprises a front spar ( 1 a ) and a rear spar ( 1 b ), the rib structure comprising: a center element ( 2 ) which extends between the front spar ( 1 a ) and the rear spar ( 1 b ); a plurality of vertical stiffening elements ( 3 ) arranged between an upper skin ( 4 a ) and a lower skin ( 4 b ) and joined to the center element ( 2 ) of the rib; each vertical stiffening element ( 3 ) comprising a vertical body ( 3 a ) with an upper end part ( 3 b ) and a lower end part ( 3 c ), a first lateral wing ( 3 d ) which extends in the direction of said front spar ( 1 a ) and a second lateral wing ( 3 e ) which extends in the direction of said rear spar ( 1 b ); said lateral wings ( 3 d , 3 e ) emerging from respective opposite sides of the vertical body ( 3 a ) and being attached to the center element ( 2 ) of the rib; upper stringers ( 5 ) and lower stringers ( 6 ) respectively attached internally to the upper skin ( 4 a ) and lower skin ( 4 b ), and arranged in a direction substantially perpendicular to the center element ( 2 ) of the rib, each stringer ( 5 , 6 ) comprising a base ( 5 a , 6 a ) with which it is joined to the respective skin ( 4 a , 4 b ); wherein at least one of the end parts ( 3 b , 3 c ) of each of the vertical stiffening elements ( 3 ) is joined directly to one of the stringers( 5 , 6 ); and wherein at least one of the skins ( 4 a , 4 b ) is attached to the center element ( 2 ) by the stiffening elements ( 3 ).