Abstract: A lower fuselage shell for an aircraft rear fuselage section, wherein the lower fuselage shell is made of a composite material and comprises at least one lower skin and stringers integrally formed with the lower skin, and frame segments extending crosswise relative to the stringers. Shear-ties are co-cured or co-bonded with the lower skin and extend crosswise relative to the stringers. Frame segments are fastened to the shear-ties, such that the frame segments are distanced from the lower skin. An aircraft rear fuselage section comprises an upper fuselage shell and the described lower fuselage shell. The upper fuselage shell has an upper skin reinforced with omega-shaped stringers, and the lower shell has a lower skin reinforced with T-shaped stringers.

Abstract: A lower fuselage shell for an aircraft rear fuselage section, wherein the lower fuselage shell is made of a composite material and comprises at least one lower skin and stringers integrally formed with the lower skin, and frame segments extending crosswise relative to the stringers. Shear-ties are co-cured or co-bonded with the lower skin and extend crosswise relative to the stringers. Frame segments are fastened to the shear-ties, such that the frame segments are distanced from the lower skin. An aircraft rear fuselage section comprises an upper fuselage shell and the described lower fuselage shell. The upper fuselage shell has an upper skin reinforced with omega-shaped stringers, and the lower shell has a lower skin reinforced with T-shaped stringers.

Abstract: An aircraft rear section (20) including a fuselage rear section (21) extending from the rear pressure bulkhead (23) to the end of the fuselage and an empennage (12) including at least a vertical tail plane (13). An aircraft rear section (20) with a continuous skin (31) is formed by two lateral sides placed symmetrically with respect to the middle vertical plane of the aircraft, each side including an upper portion (26) for the torsion box (14) of the vertical tail plane (13), a lower portion (28) for the fuselage rear section (21) and a transition portion (27) between the upper and lower portions (26, 28). The upper and lower portions (26, 28) of the continuous skin (31) are joined to inner structural components of the vertical tail plane (13) and the fuselage rear section (21).

Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft.

Abstract: Weathertight fitting (41) for the mounting of the tail vertical stabilizer of an aircraft in a rear area of its fuselage, the construction being based on a casing (5) made with a composite material as one unitary piece and some frames (7) that are comprised of: one first piece (43) comprised of two bodies (45, 45?), that include the mounting lugs (47, 47?) for the tail vertical stabilizer and some vertical walls (49, 49?) for joining the fitting (43) to the frames (7) of the fuselage, and a weathertight central profile (51); two pairs of additional pieces (55, 55?; 65, 65?) of angular shape, that include some horizontal walls (57, 57?; 67, 67?) for joining to the casing (5) and some vertical walls (59, 59?; 69, 69?) for joining to the aforementioned bodies (45, 45?). All the weathertight fitting's (41) pieces are made with a composite material.

Abstract: A method for repairing the skin of the fuselage of an airplane from the inside to be used when the skin of the fuselage has been damaged between a first stringer and a second stringer adjacent to the first one is provided. The method includes filling the damage, placing a first doubler over the filling, placing a second doubler over the first doubler and bending this second doubler at least over a flange of one of the stringers, and securing the second doubler.

Abstract: A ball-joint support for thin parts, through which a ball-joint is operably coupled to a thin part, and where the ball-joint includes an inner part with a central coaxial orifice through which a longitudinal axis is introduced, and an outer part that engages complementarily to the inner part is provided. The ball joint support includes a cap including a central through hole in which the ball joint is embedded inside via the outer part, and externally, the cap is embedded in a cylindrical opening included in the thin part, and mechanical means for axial retention of the thin part to the cap, wherein the thickness of the cap is greater than the thickness of the thin part where the cap engages.

Abstract: An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions (20) that form, when joined, the aforementioned frame in its entirety, with these partitions (20) comprising sections (1) with a length (2), and sections (1) that are being arranged on the inside of the skin (3) that forms the fuselage of the aircraft. This fuselage is integrally embodied in a single piece, with the length (2) of the sections (1) being the maximum possible, In such a way that the maximum separation (5) between the frame section (1) and the skin (3), with the separation (5) being measured by the inside of the aforementioned skin (3), is lower than the limit value permitted for the use of a liquid sealant.

Abstract: A joint construction for an aeronautical structure made from composite material having an internal structural element and an adjoining skin element which define the aeronautical structure, which includes a coupling element disposed between and contiguous with the internal structural element and the adjoining skin element, wherein the coupling element has opposing adjoining diagonally configured end portions which form a wedge shaped diagonal joint therebetween which terminates at the internal structural element at one end and the skin element at the other end, and a plurality of rivets extending from the internal structured element to the adjoining skin, across the coupling element and across the diagonal joint.

Abstract: Aircraft component, such as an aircraft wing, that comprises at least one panel (11) of a composite material formed by a skin (13) and at least a stiffening stringer (15) configured by a web (17) and a foot (19) bonded to said skin (13); the stringer (15) having a run-out zone inside said panel (11) subjected to a high load level; the stringer (15) having a web (17) of decreasing height in said run-out zone and a foot (19) having a first section (31) of variable width from an initial value W1 to a final value W2 and a second section (33) with a width W2 in said run-out zone; the foot (19) and the web (17) of said stringer (15) having a decreasing thickness in said run-out zone for improving the load transfer from the stringer (15) to the skin (13).

Abstract: A fitting is provided to fix a vertical tail stabilizer of an aircraft to a composite skin and a composite frame of the aircraft in an area of a rear fuselage thereof. The fitting includes a first composite piece having lugs to attach to the vertical tail stabilizer and having vertical walls to fix the fitting to the composite frame of the rear fuselage. The fitting further includes at least one pair of additional composite pieces, each having a horizontal wall to fix the fitting to the composite skin of the rear fuselage. A second pair of additional composite pieces may be provided to further secure the fitting to the skin of the aircraft.

Abstract: A joint arrangement for composite-material structural members in components including a skin and a plurality of structural members, applicable to pairs of first and second intersecting structural members, such as a beam and a frame in an aircraft fuselage, both members having a configuration which includes webs, inner flanges and outer flanges, in which, in the zone of intersection between said members, the laminations of one or both flanges of the first member include transverse flaps which are joined to one or both flanges of the ends of the segments of the second member which are separated at the intersection, acting as means for transmission of loads between them.

Abstract: The ball joints are embedded via the coaxial orifice thereof, centered on a longitudinal shaft. The invention is characterized in that it comprises a bush (1) in the inner space of which the ball joint (2) is embedded, whilst, externally, this bush (1) is embedded in a cylindrical opening of a thin piece (10), mechanical means for axial retention of the bush (1) in both directions with respect to the thin piece (10) being included. All the aforesaid allows a thin structure or piece to be connected completely securely to a ball joint, thereby achieving a completely firm, solid connection.

Abstract: Interface arrangement between a first component (11) and a second component (21) of an aircraft structure having an aerodynamic contour, such as a wing skin and a wing leading edge panel, the first component (11) having a joggle so that it includes a first area (13) which surface (15) belongs to the aircraft aerodynamic contour and a second area (17) where the joint with the second component (21) takes place, the second component (21) having a surface (23) belonging to the aircraft aerodynamic contour, in which the second component (21) includes a chamfer-shaped ending (29) that extends beyond the overlapping area (27) where the joint with the first component (11) takes place so that the gaps (26, 28) between the first component (11) and the second component (21) are minimized.

Abstract: A method for repairing the skin of the fuselage of an airplane from the inside to be used when the skin of the fuselage has been damaged between a first stringer and a second stringer adjacent to the first one is provided. The method comprises four steps which are: filling the damage, placing a first doubler over the filling, placing a second doubler over the first doubler and bend this second doubler at least over a flange of one of the stringers, and securing the second doubler. If either one of the stringers or two of them adjacent to the damage are also damaged, the present method can be used. This invention also proposes a smaller width of the foot of the stringer object of the present invention than the width of a same stringer designed considering the methods currently used for repair design principles.

Abstract: Weathertight fitting (41) for the mounting of the tail vertical stabiliser of an aircraft in a rear area of its fuselage, the construction being based on a casing (5) made with a composite material as one unitary piece and some frames (7) that are comprised of: one first piece (43) comprised of two bodies (45, 45?), that include the mounting lugs (47, 47?) for the tail vertical stabiliser and some vertical walls (49, 49?) for joining the fitting (43) to the frames (7) of the fuselage, and a weathertight central profile (51); two pairs of additional pieces (55, 55?; 65, 65?) of angular shape, that include some horizontal walls (57, 57?; 67, 67?) for joining to the casing (5) and some vertical walls (59, 59?; 69, 69?) for joining to the aforementioned bodies (45, 45?). All the weathertight fitting's (41) pieces are made with a composite material.

Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft.

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).

Abstract: An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions (20) that form, when joined, the aforementioned frame in its entirety, with these partitions (20) comprising sections (1) with a length (2), and sections (1) that are being arranged on the inside of the skin (3) that forms the fuselage of the aircraft. This fuselage is integrally embodied in a single piece, with the length (2) of the sections (1) being the maximum possible, in such a way that the maximum separation (5) between the frame section (1) and the skin (3), with the separation (5) being measured by the inside of the aforementioned skin (3), is lower than the limit value permitted for the use of a liquid sealant.

Abstract: Arrangement of a circumferential joint of structural elements with a coupling element manufactured in composite material in a aeronautic structure, which comprises: two sections (13, 15) of skin (11) manufactured in a composite material with an external surface (17) and an internal surface (19); an internal structural element (41); a plurality of rivet rows (12) and a coupling element (21) to facilitate the joint of adjoining skin (11) sections (13, 15), with an external surface (23) and an internal surface (25), manufactured in composite material in a plurality of separate parts (27, 29), with the ends of each pair of adjoining parts (27, 29) being formed in a wedge shape, with one of them pointing to the skin (11) and the other to the internal structural element (41) and with their inclined faces overlapping (31,33).