Method for the continuous production of a connecting part made from composite material

1. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, made of composite material, said connecting part comprising at least one hollow body ( 32 ) and at least one yoke ( 34 ) at each of the ends ( 36 ) of said body ( 32 ), characterized in that said body ( 32 ) and said yokes ( 34 ) of the connecting part ( 30 ) are derived from a single profile (P, P 1 , P 2 ) of composite material obtained by pultrusion.

2. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 1 , wherein the profile (P, P 1 , P 2 ) comprises at least two flanges ( 46 ) connected by at least one solid web ( 48 ).

3. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 2 , wherein the profile (P 1 ) comprises a protective outer shell ( 52 ).

4. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 3 , wherein the outer shell ( 52 ) assumes the shape of a membrane ( 54 ) that surrounds the flanges ( 46 ) of the profile (P 1 ) and continues on the outer periphery of the cross-section (S 1 ) of the profile (P 1 ).

5. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 4 , wherein said outer shell ( 52 ) is cylindrical over the length (L 1 ) of said profile (P 1 ).

6. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 3 , wherein the profile (P 1 ) comprises at least two solid webs ( 48 ) connecting at least two flanges ( 46 ), and wherein at least two solid webs ( 48 ) connecting the flanges ( 46 ) are an integral part of the protective outer shell ( 52 ).

7. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 3 , wherein the flanges ( 46 ) are flat.

8. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 3 , wherein it consists in at least:

selecting a portion ( 58 ) of predetermined length (L 1 ) from the profile (P 1 ) of composite material,

performing the cutting of the yokes ( 34 ) at each end ( 60 ) of said portion,

making the bores ( 40 ) through said cut yokes.

9. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 8 , wherein the cutting operations consist in making tapered cuts ( 62 ) at the ends ( 60 ) of the length (L 1 ) of selected profile (P 1 ) and on both sides of the flanges ( 46 ) of said profile (P 1 ), in stopping the solid web or webs ( 48 ) of the profile (P 1 ) by straight cuts ( 64 ) at right angles with the tapered cuts ( 62 ), and in giving their final shape to the lugs ( 38 ) of the yokes ( 40 ) of the connecting part ( 30 ).

10. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 2 , wherein the first profile (P 2 ) comprises at least two solid webs ( 48 ) connecting the flanges ( 46 ).

11. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 10 , wherein the two flanges ( 46 ) are flat and parallel.

12. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 10 , wherein the first profile (P 2 ) receives an outer shell ( 74 ) for protection against impacts, and wherein said outer shell ( 74 ) assumes the shape of a second profile (P 3 ).

13. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 12 , wherein said outer shell ( 74 ), or the second profile (P 3 ), assumes the shape of a membrane ( 76 ) surrounding the flanges ( 46 ) and the web or webs ( 48 ) of the first profile (P 2 ) and continues on the outer periphery of the cross-section (S 2 ) of the first profile (P 2 ).

14. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 13 , wherein said outer shell ( 74 ), or the second profile (P 3 ), is cylindrical over the length (L 2 ) of said first profile (P 2 ).

15. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 12 , wherein attaching means ( 78 ) are provided between said first profile (P 2 ) and said second profile (P 3 ).

16. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 15 , wherein the attaching means ( 78 ) consist in at least one collar ( 80 ) provided around the first profile (P 2 ) and of a shape corresponding to the inside contour ( 82 ) of the second profile (P 3 ), and/or in at least one stop ( 84 ) attached to said first profile (P 2 ) and that stops the second profile (P 3 ) in translation.

17. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 15 , wherein the attaching means ( 78 ) consist in a dimensional adjustment of the profiles (P 2 ) and (P 3 ) so that they are in sliding contact, and then in a very localized gluing so as to bond them in position relative to one another.

18. Method for producing a connecting part, particularly a connecting rod of an aircraft, of composite material according to claim 12 , wherein it consists in at least:

selecting a portion ( 86 ) of predetermined length (L 2 ) from the first profile (P 2 ) of composite material,

performing the cutting of the yokes ( 34 ) at each end ( 88 ) of said portion,

preparing the second profile (P 3 ) at an appropriate length (L 3 ),

attaching said second profile (P 3 ) around the first profile (P 2 ), particularly using attaching means ( 78 ),

making the bores ( 40 ) through said cut yokes ( 34 ).

19. Method for producing a connecting part, particularly a connecting rod of an aircraft, of composite material according to claim 18 , wherein the cutting operations of the first profile (P 2 ) consist in stopping the solid webs ( 48 ) of the first profile (P 2 ) by straight cuts ( 90 ) recessed from the ends ( 92 ) of the flanges ( 46 ) of said first profile, and in giving their final shape to the lugs ( 38 ) of the yokes ( 34 ).

20. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, made of composite material, said connecting part comprising at least one hollow body ( 32 ) and at least one yoke ( 34 ) at each of the ends ( 36 ) of said body ( 32 ), characterized in that said body ( 32 ) and said yokes ( 34 ) of the connecting part ( 30 ) are derived from a single profile (P, P 1 , P 2 ) of composite material obtained by a continuous manufacturing process, wherein it foresees adding reinforcing pieces ( 94 ) at the level of said yokes.

21. Method for producing a connecting part ( 30 ), particularly a connecting rod of an aircraft, of composite material according to claim 1 , wherein,

the profile comprises at least two flanges ( 46 ) connected by at least one solid web ( 48 ), and

in cross-section, an outermost edge of each flange ( 46 ) is attached to an inside edge of said at least one solid web ( 48 ).