Monolithic and bi-functional extruded structural element
View Patent ↗The invention relates to a bi-functional extruded structural element, particularly a stringer for aeronautical construction, comprising a base that can be fixed on a surface, and a body, wherein the base comprises a first aluminum-based alloy, and further wherein the body comprises a second heat treatable aluminum-based alloy, having properties that are different from the properties of the first aluminum based alloy.
1. A monolithic extruded structural element capable for use as a stringer for aeronautical construction, said element comprising
a base that can be fixed onto a surface,
and a body,
wherein said base comprises a first aluminium-based alloy
and wherein said body comprises a second heat treatable, aluminium-based alloy having properties different from the properties of the first aluminum-based alloy, and wherein the monolithic extruded structural element comprises an extruded element comprising at least two co-extruded alloys that is obtained by machining from a single piece of extruded partly finished product without assembly, and further wherein said structural element includes a diffusion zone that is at least about 116 μm wide.
2. A structural element according to claim 1 , wherein the first aluminium-based alloy is fusion weldable.
3. A structural element according to claim 1 , wherein the second heat treatable, alloy comprises an alloy from the group 7xxx.
4. A structural element according to claim 3 , wherein the second heat treatable alloy is at least one selected from the group consisting of 7049, 7149, 7249, 7349, 7449, 7050, 7055, 7075, 7068, 7036 and 7136 alloys.
5. A structural element according to claim 1 , wherein the first alloy comprises at least one alloy in the 6xxx, 5xxx and/or 4xxx group.
6. A structural element according to claim 5 , wherein the first alloy is at least one selected from the group consisting of 6056, 6056A, 6156, 6060, 6013, 6110, 5005, 5083 and 5086 alloys.
7. A manufacturing process for an extruded structural element having a diffusion zone that is at least about 116 μm wide and that is suitable for aeronautical construction comprising: preparing a hollow cylindrical extrusion billet with axial symmetry comprising an internal tube comprising a first aluminium-based alloy, and an external tube comprising a second heat treatable, aluminium-based alloy, co-extruding the alloys to form a hollow tube on a mandrel comprising a plurality of ribs, such that at least a portion of said ribs comprise said second heat treatable, alloy, while the wall of the hollow tube comprises said first alloy, to form a product, cutting out the product and optionally machining said product, so as to obtain a structural element comprising a base comprising said first alloy and a body comprising said second heat treatable alloy.
8. A process according to claim 7 , further comprising inserting said internal tube comprising said first aluminium-based alloy into said external tube comprising said second heat treatable aluminium-based alloy by cold contraction of the said internal tube.
9. A process according to claim 7 , wherein said extruding comprises inverse extrusion.
10. A process according to claim 7 , wherein said first alloy comprises a fusion weldable alloy.
11. A process according to claim 7 , wherein said second heat treatable alloy is at least one selected from the group consisting of 7049, 7149, 7249, 7349, 7449, 7050, 7055, 7075, 7068, 7036, and 7136 alloys.
12. A process according to claim 7 , wherein said first alloy is at least one selected from the group consisting of 6056, 6056A, 6156, 6060, 6013, 6110, 5005, 5083, 5086 alloys.
13. A process according to claim 11 , wherein said first alloy is at least one selected from the group consisting of 2024, 2024A, 2056, 2124, 2224, 2324, 2424, and 2524 alloys.
14. A manufacturing process for preparing a structural element suitable for aeronautical construction comprising welding an extruded structural element according to claim 1 onto a structural product or element comprising a heat treatable aluminium alloy, to obtain a welded structural element, optionally performing a heat treatment on said welded structural element.
15. A structural element according to claim 2 , wherein the second heat-treatable alloy comprises at least one alloy in the 6xxx, 5xxx and/or 4xxx group.
16. A structural element according to claim 3 , wherein the second heat-treatable alloy comprises at least one alloy in the 6xxx, 5xxx and/or 4xxx group.
17. A structural element according to claim 2 , wherein the first alloy is at least one selected from the group consisting of 6056, 6056A, 6156, 6060, 6013, 6110, 5005, 5083 and 5086 alloys.
18. A structural element according to claim 3 , wherein the first alloy is at least one selected from the group consisting of 6056, 6056A, 6156, 6060, 6013, 6110, 5005, 5083, and 5086 alloys.
19. A process according to claim 8 , wherein said first alloy comprises a fusion weldable alloy.
20. A process according to claim 9 , wherein said first alloy comprises a fusion weldable alloy.
21. A manufacturing process for preparing a structural element suitable for aeronautical construction comprising fusion welding an extruded structural element according to claim 2 onto a structural product or element comprising a heat treatable aluminium alloy, to obtain a welded structural element, optionally performing a heat treatment on said welded structural element.
22. A manufacturing process for preparing a structural element suitable for aeronautical construction comprising welding an extruded structural element according to claim 5 onto a structural product or element comprising a heat treatable aluminium alloy, to obtain a welded structural element, optionally performing a heat treatment on said welded structural element.
23. A manufacturing process for preparing a structural element suitable for aeronautical construction comprising welding an extruded structural element according to claim 3 onto a structural product or element comprising a heat treatable aluminium alloy, to obtain a welded structural element, optionally performing a heat treatment on said welded structural element.
24. A manufacturing process for preparing a structural element suitable for aeronautical construction comprising welding an extruded structural element according to claim 4 onto a structural product or element comprising a heat treatable aluminium alloy, to obtain a welded structural element, optionally performing a heat treatment on said welded structural element.
25. A structural element made by a process according to claim 21 .
26. An aeronautical part comprising a structural element made by a process of claim 21 .
27. A structural element made by a process according to claim 14 .
28. An aeronautical part comprising a structural element made by a process of claim 14 .
29. A structural element according to claim 1 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
30. A structural element according to claim 29 wherein the yield stress is at least about 650 MPa.
31. A structural element according to claim 2 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
32. A structural element according to claim 31 wherein the yield stress is at least about 650 MPa.
33. A structural element according to claim 3 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
34. A structural element according to claim 33 wherein the yield stress is at least about 650 MPa.
35. A structural element according to claim 4 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
36. A structural element according to claim 35 wherein the yield stress is at least about 650 MPa.
37. A structural element according to claim 5 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
38. A structural element according to claim 37 wherein the yield stress is at least about 650 MPa.
39. A structural element according to claim 6 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
40. A structural element according to claim 39 wherein the yield stress is at least about 650 MPa.
41. A structural element of claim 1 that has a body pull-out force of at least about 300 MPa.
42. A structural element of claim 41 that has a body pull out force of at least about 350 MPa.
43. A structural element of claim 2 that has a body pull-out force of at least about 300 MPa.
44. A structural element of claim 43 that has a body pull out force of at least about 350 MPa.
45. A structural element of claim 3 that has a body pull-out force of at least about 300 MPa.
46. A structural element of claim 45 that has a body pull out force of at least about 350 MPa.
47. A structural element of claim 4 that has a body pull-out force of at least about 300 MPa.
48. A structural element of claim 47 that has a body pull out force of at least about 350 MPa.
49. A structural element of claim 5 that has a body pull-out force of at least about 300 MPa.
50. A structural element of claim 49 that has a body pull out force of at least about 350 MPa.
51. A structural element of claim 6 that has a body pull-out force of at least about 300 MPa.
52. A structural element of claim 51 that has a body pull out force of at least about 350 MPa.
53. A structural element of claim 29 that has a body pull-out force of at least about 300 MPa.
54. A structural element of claim 53 that has a body pull out force of at least about 350 MPa.
55. A structural element of claim 31 that has a body pull-out force of at least about 300 MPa.
56. A structural element of claim 55 that has a body pull out force of at least about 350 MPa.
57. A structural element of claim 33 that has a body pull-out force of at least about 300 MPa.
58. A structural element of claim 57 that has a body pull out force of at least about 350 MPa.
59. A structural element of claim 35 that has a body pull-out force of at least about 300 MPa.
60. A structural element of claim 59 that has a body pull out force of at least about 350 MPa.
61. A structural element of claim 37 that has a body pull-out force of at least about 300 MPa.
62. A structural element of claim 61 that has a body pull out force of at least about 350 MPa.
63. A structural element of claim 39 that has a body pull-out force of at least about 300 MPa.
64. A structural element of claim 63 that has a body pull out force of at least about 350 MPa.
65. A structural element suitable for aeronautical construction prepared by a process comprising welding an extruded structural element according to claim 1 onto a structural product or element comprising a heat treatable aluminum alloy, to obtain a welded structural element, optionally performing a heat treatment on said welded structural element.
66. A structural element according to claim 41 that comprises a monolithic and bi-functional structural element, wherein the body has a yield stress R p0,2 of at least about 600 MPa and said base is fusion-weldable.
67. A structural element according to claim 66 wherein the yield stress is at least about 650 MPa.
68. A fuselage element comprising a structural element of claim 1 .
69. A fuselage element comprising a structural element of claim 2 .
70. A fuselage element comprising a structural element of claim 3 .
71. A fuselage element comprising a structural element of claim 29 .
72. A fuselage element comprising a structural element of claim 31 .
73. A fuselage element comprising a structural element of claim 33 .
74. A fuselage element comprising a structural element of claim 35 .
75. A fuselage element comprising a structural element of claim 37 .
76. A fuselage element comprising a structural element of claim 39 .
77. A manufacturing process for preparing a structural element suitable for aeronautical construction comprising fixing an extruded structural element according to claim 1 onto a structural product comprising a heat treatable aluminium alloy, to obtain a final structural element, optionally performing a heat treatment on said final structural element.
78. A process according to claim 77 , wherein said fixing comprises fusion welding.
79. A process according to claim 77 , wherein said fixing comprises riveting.