Attachment system of aircraft components

Abstract

An attachment system for attaching a component ( 11 ) such as a vertical tail plane to a fuselage ( 27 ) of an aircraft; the component ( 11 ) being structured as a box comprising front and rear spars ( 13, 14 ), ribs ( 15 ) extending from the front spar ( 13 ) to the rear spar ( 14 ), and a skin ( 17 ), and also comprising a plurality of intermediate spars ( 23 ) arranged to be attached to fuselage frames ( 33 ); the fuselage ( 27 ) comprising a skin ( 31 ) and frames ( 33 ) and also comprising a mounting arrangement suitable for receiving the additional spars ( 23 ) and for allowing its attachment to the frames ( 33 ).

1 . An attachment system for attaching a component ( 11 ) to the fuselage ( 27 ) of an aircraft; the component ( 11 ) being structured as a box comprising front and rear spars ( 13 ,  14 ), ribs ( 15 ) extending from the front spar ( 13 ) to the rear spar ( 14 ) and a skin ( 17 ); the fuselage ( 27 ) comprising a skin ( 31 ) and frames ( 33 ); characterized by comprising:
 in the component ( 11 ), a plurality of intermediate spars ( 23 ) arranged to be attached to the frames ( 33 ); and   in the fuselage ( 27 ), a mounting arrangement suitable for receiving the plurality of intermediate spars ( 23 ) and for allowing the attachment of the fuselage to the frames ( 33 ).   
     
     
         2 . The attachment system according to  claim 1 , characterized in that the plurality of intermediate spars ( 23 ) are arranged to be attached to contiguous frames ( 33 ). 
     
     
         3 . The attachment system according to  claim 1 , characterized in that the plurality of intermediate spars ( 23 ) are attached by one of its ends to any of the front and rear spars ( 13 ,  14 ) and optionally to any of the ribs ( 15 ). 
     
     
         4 . The attachment system according to  claim 1 , characterized in that the mounting arrangement comprises a plurality of access doors ( 45 ) in the fuselage skin ( 31 ) allowing the correct positioning of the component ( 11 ) on the fuselage ( 27 ). 
     
     
         5 . The attachment system according to  claim 1 , wherein the attachment system is further characterized as comprising at least two longitudinal elements ( 49 ) constructed to be joined to the fuselage skin ( 31 ) and to the skin ( 17 ) of the component ( 11 ). 
     
     
         6 . The attachment system according to  claim 1 , characterized in that the component ( 11 ) is a vertical tail plane. 
     
     
         7 . The attachment system according to  claim 6 , characterized in that the frames ( 33 ) and the intermediate spars ( 23 ) have a C-shaped transversal section; in that each of the frames ( 33 ) comprises a web ( 25 ) and each of the intermediate spars ( 23 ) comprises a web ( 35 ); and in that the intermediate spars ( 23 ) are arranged in a manner so that the lower part of their webs ( 25 ) can be attached to the webs ( 35 ) of the frames ( 33 ) by mechanical means. 
     
     
         8 . The attachment system according to  claim 7 , characterized in that each of the frames ( 33 ) comprises a flange ( 37 ) and each of the intermediate spars ( 23 ) comprises a flange ( 27 ), and in that the frames ( 33 ) and the intermediate spars ( 23 ) are arranged in a manner so that the flanges ( 37 ) of the contiguous frames ( 33 ) and the flanges ( 27 ) of the plurality of intermediate spars ( 23 ) are oppositely oriented. 
     
     
         9 . The attachment system according to  claim 2 , characterized in that the plurality of intermediate spars ( 23 ) are attached by one of its ends to any of the front and rear spars ( 13 ,  14 ) and optionally to any of the ribs ( 15 ). 
     
     
         10 . The attachment system according to  claim 9 , characterized in that the mounting arrangement comprises a plurality of access doors ( 45 ) in the fuselage skin ( 31 ) allowing the correct positioning of the component ( 11 ) on the fuselage ( 27 ). 
     
     
         11 . The attachment system according to  claim 10 , wherein the attachment system is further characterized as comprising at least two longitudinal elements ( 49 ) constructed to be joined to the fuselage skin ( 31 ) and to the skin ( 17 ) of the component ( 11 ). 
     
     
         12 . The attachment system according to  claim 11 , characterized in that the component ( 11 ) is a vertical tail plane. 
     
     
         13 . The attachment system according to  claim 12 , characterized in that each of the frames ( 33 ) and each of the intermediate spars ( 23 ) have a C-shaped transversal section; in that each of the frames ( 33 ) comprises a web ( 25 ) and each of the intermediate spars ( 23 ) comprises a web ( 35 ); and in that the intermediate spars ( 23 ) are arranged in a manner so that the lower part of their webs ( 25 ) can be attached to the webs ( 35 ) of the frames ( 33 ) by mechanical means. 
     
     
         14 . The attachment system according to  claim 13 , characterized in that each of the frames ( 33 ) comprises a flange ( 37 ) and each of the intermediate spars ( 23 ) comprises a flange ( 27 ), and in that the frames ( 33 ) and the intermediate spars ( 23 ) are arranged in a manner so that the flanges ( 37 ) of the contiguous frames ( 33 ) and the flanges ( 27 ) of the intermediate spars ( 23 ) are oppositely oriented.