Abstract: Joining of a structural aircraft element (1) that has a section in an omega shape, to another structural aircraft element (10) with a differently shaped section, with the aforementioned joint of these structural elements (1, 10) with a different section comprising at least two joining elements (4) in an angular shape, which are joined with the external flanges (5) of the structural elements (1, 10), in such a manner that this joint allows the section change to take place continually, through simple elements (4) in its manufacturing and assembly, thanks to its geometric simplicity. The assembly of this joining of structural elements (1, 10) is also with a section change of great flexibility, allowing the tolerances of the joint to be absorbed, and achieving that the load distribution between the structural elements (1, 10) and the joining elements (4) is optimal.

Abstract: The invention relates to fittings (41, 71) for fixing the vertical tail stabilizer of an aircraft in an area of its rear fuselage integrally manufactured with a composite material comprising: a) a first piece (43, 73) comprising lugs (45, 45?; 75, 75?) for fixing the vertical tail stabilizer and vertical walls (47, 47?; 77, 77?) for fixing the fitting (41, 71) to the frames (7); b) at least one pair of additional pieces (49, 49?; 79, 79?) comprising horizontal walls (51, 51?; 81, 81?) for fixing the fitting (41, 71) to the skin (5). The fitting (71) for fixing with an inclined load also comprises a second pair of pieces (90, 90?) having an angular shape comprising vertical walls (93, 93?) for the fixing with the lugs (75, 75?). The invention also relates to processes for assembling these fittings (41, 71).

Abstract: Joint arrangement for composite-material structural members in components comprising a skin and a plurality of structural members, applicable to pairs of first and second intersecting structural members (11, 21), such as a beam and a frame in an aircraft fuselage, both members having a configuration which includes webs (31, 41), inner flanges(33, 43) and outer flanges(35, 45), in which, in the zone of intersection between said members (11, 21), the laminations of one or both flanges(33, 35) of the first member (11) include transverse flaps (55, 55; 57, 59) which are joined to one or both flanges(43, 45) of the ends of the segments (23, 25) of the second member (21) which are separated at the intersection, acting as means for transmission of loads between them.