Patent ID: 8870117

Claim:
An aircraft frame ( 1 ) comprising: two segments ( 10 , 20 ), each of the two segments ( 10 , 20 ) being a single unitary element made of composite material, and each of the two segments ( 10 , 20 ) including: at least one arc-shaped web ( 2 ) with a convex-shaped outer side wall ( 2 ow), and a concave-shaped inner side wall ( 2 iw) so that each of the two segments ( 10 , 20 ) has an open interior, a stiffening structure with multiple components ( 31 , 32 , 33 ), each of which extends in a direction that is perpendicular to the convex-shaped outer side wall ( 2 ow), and a fitting ( 4 ) arranged in a position located where a portion of the multiple component ( 31 , 32 , 33 ) join each other, wherein the two segments ( 10 , 20 ) are joined together by the fitting ( 4 ) of each of the two segments ( 10 , 20 ) using rivets ( 4 r), thereby forming the aircraft frame ( 1 ) in a manner such that the concave-shaped inner side walls ( 2 iw) of each of the two segments ( 10 , 20 ) directly face each other.