Aircraft fuselage structural components and methods of making same

Abstract

Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.

1 . An aircraft fuselage structural component comprising:
 plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough;   plural longitudinally oriented stringers, each of the stringers being positioned within a respective one of the stringer holes of the frame members; and   reinforcement members lap joined by a friction stir weld region to corresponding surfaces of the frame members in a vicinity of the stringer holes.   
   
   
       2 . The component of  claim 1 , wherein the reinforcement member comprises a continuous or discontinuous structure. 
   
   
       3 . The component of  claim 1 , further comprising a skin attached to the frame members and/or stingers. 
   
   
       4 . The component of  claim 1 , wherein the friction stir weld region is a continuous friction stir weld line. 
   
   
       5 . The component of  claim 1 , wherein the reinforcement members comprise an L-shaped flanged structure having one flange rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       6 . The component of  claim 1 , wherein the reinforcement members comprise a curved plate rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       7 . The component of  claim 1 , wherein the reinforcement members comprise a reverse S-shaped structural member having a flange rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       8 . The component of  claim 7 , wherein the flange of the S-shaped structural member is rigidly lap joined to flange of the frame member. 
   
   
       9 . The component of  claim 7 , wherein the flange of the S-shaped structural member is rigidly lap joined to a center span of the frame member. 
   
   
       10 . The component of  claim 1 , wherein the reinforcement members comprise a reinforcement bar positioned laterally of a stringer opening and rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       11 . The component of  claim 1 , wherein the reinforcement members comprise a reinforcement bar positioned laterally of a stringer opening and curved plate rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       12 . A method of making an aircraft fuselage structural component comprising:
 providing plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough;   positioning each of a plurality of longitudinally oriented stringers within a respective one of the stringer holes of the frame members;   structurally reinforcing the stringer openings by lap joining reinforcement members to corresponding surfaces of frame members in a vicinity of the stringer holes, and   friction stir welding the reinforcement members rigidly to the corresponding surfaces of the frame members to form a friction stir weld region therebetween.   
   
   
       13 . The method of  claim 12 , wherein the reinforcement member comprises a continuous or discontinuous structure. 
   
   
       14 . The method of  claim 12 , further comprising attaching a skin to the frame members and/or stingers. 
   
   
       15 . The method of  claim 12 , wherein the step of friction stir welding forms a continuous friction stir weld line. 
   
   
       16 . The method of  claim 12 , wherein the reinforcement members comprise an L-shaped flanged structure, and wherein one flange of the structure is rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       17 . The method of  claim 12 , wherein the reinforcement members comprise a curved plate rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       18 . The method of  claim 12 , wherein the reinforcement members comprise a reverse S-shaped structural member having a flange rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region. 
   
   
       19 . The method of  claim 18 , wherein the flange of the S-shaped structural member is rigidly lap joined to a flange of the frame member. 
   
   
       20 . The method of  claim 18 , wherein the flange of the S-shaped structural member is rigidly lap joined to a center span of the frame member. 
   
   
       21 . The method of  claim 12 , wherein the reinforcement members comprise a reinforcement bar positioned laterally of a stringer opening and is rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region.