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: Provided herein are drainage valves for removing water accumulated in the lower part of fuel tanks of an aircraft. The valves can be affixed in correspondence with a lower skin forming part of the tanks. The lower skin includes recesses for the complementary housing of the heads of the valves that, in combination with some axial fastening nuts, immobilize the valves to that skin. The recesses can comprise a conical structure obtained by deformation of the lower skin, and with the deformation an inner elevated seat is further obtained, on which seat the axial fastening nuts press, maintaining the thickness of the skin in the area where the valves are located, thus preventing the area from weakening as it happens conventionally.

Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).

Abstract: Aircraft horizontal stabilizer surface (8) in which the sweep angle (40) of this surface (8), where this angle (40) is the one formed by the projection of the reference line of points located at 25% of the local chord (19) of the horizontal stabilizer surface (8) on a plane perpendicular to the aircraft plane of symmetry (21), and which also contains this plane to the flight direction of the aircraft with respect to the aircraft plane of symmetry (21), is less than 90 degrees, with this angle (40) being measured in the flight direction of the aircraft. In addition, the structural connection of this horizontal stabilizer surface (8) to the aircraft fuselage (1) is located at a closing frame (13) of this fuselage (1).

Abstract: Portable robot for carrying out the drilling process in the assembly of aeronautical components which are secured on a support known as a stand. The robot comprises a displaceable platform in order to permit it to be located close to the stand, and an arm, which supports a frame comprising a beam intended to support a drilling head that can be displaced in the three axes.

Abstract: The present invention relates to a jig for the manufacture, by means of injection and curing processes, of preforms of composite material frames for aircraft fuselages by using the RTM (resin transfer molding) technology. Two preforms are thus manufactured, one with a C shaped section and another with a L shaped section, together with the preforms of the stabilization ribs for stabilizing the web of the frames and the preform of the roving or staple fiber to cover the gap between the C shaped preform and the L shaped preform. Theses preforms are previously manufactured by any known process for manufacturing preforms. According to a second aspect, the present invention relates to a method of manufacturing composite material load frames for aircraft.

Abstract: A computer-aided method of obtaining a preliminary ply model of a composite component to be used in the manufacture of industrial parts by stacking and joining a plurality of plies of composite materials, comprising the following steps: a) obtaining from stress calculations a ply stacking sequence for the component subdivided into panels; b) automatically generating a stacking table containing the ply sequence for each different zone (defined by its ply sequence); c) automatically generating a grid table; d) optimizing said stacking table; e) performing the plies drop-off distribution by means of a tool that allows carrying out said distribution automatically according to a predetermined staggering rule; f) obtaining an output table containing the data required for representing the ply model in a CAD program.

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 invention relates to a hybrid tooling (1) for the curing of composite pieces, comprising a support structure (3) made of a metallic material with high thermal diffusivity, a base plate (31) with an identical surface geometry as that of the piece to be cured, made of INVAR 36 or NILO 36, an intermediate structure (21) between the support structure (3) and the base plate (31), with a cell configuration, with the sides of each cell sufficiently lightened so as to facilitate the flow of air under the base plate (31) during the curing cycle, made of INVAR 36 or NILO 36, and means of fixing the intermediate structure (21) to the support structure (3) which allow their free expansion.

Abstract: A part of composite material having a wedge between two zones, the second zone being shorter than the first zone, whose structure includes from its outer surface to its inner surface: a first section formed from at least two continuous sheets extending parallel to its outer surface, the gradient of the wedge being between 20% and 50%; a wedge in the shape of a triangular prism with its larger surface dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section formed by a plurality of continuous sheets extending parallel to the surface bounded by the first section with the wedge placed upon it. The invention also relates to a process for manufacture of the part.

Abstract: A computer-aided method suitable for calculating the position of a mobile surface of an object such an aircraft that moves through a fluid medium, which is affected by at least an upstream or downstream object component, for achieving a predetermined value Vo of a predetermined object performance target, including the following steps: preparing a computer-implemented CFD model of the object having said mobile surface in a first position; solving the CFD model and obtaining the value Vi of said object performance target; if the difference between Vi and Vo is greater than a predetermined value, modifying the CFD model changing the position of the mobile surface in the CFD model and iterating the solving step. The invention also refers to a system for carrying out the method.

Abstract: Rib structure for a torsion box of an aircraft wing or a horizontal stabilizer. The structure comprises a center element which extends between the front spar and the rear spar of the torsion box, a series of vertical stiffening elements arranged between an upper skin and a lower skin of the torsion box. The vertical stiffening element consists of a first lateral wing which extends in the direction of said front spar and a second lateral wing which extends in the direction of said rear spar. These lateral extensions emerge from respective opposite sides of the vertical body and are attached side to side to the center element of the rib.

Abstract: Load introduction zone in the rear end of an aircraft comprising receiving elements (3, 4) of the loads of the horizontal and vertical tail stabilizers connected to structural elements (2, 8, 9) wherein: a) said structural elements are the cladding (8), two contiguous load-bearing frames (2) with a ? or omega cross-section and, at least, a third frame (9); b) the receiving element of the horizontal tail stabilizer load is a first fitting (3) structured as a torque box, transversely arranged between said load-bearing frames (2) and connected to them, and the receiving elements of the vertical tail stabilizer loads are some second fittings (4) coupled to these frames (2, 9); c) said frames (2, 9) and said first and second fittings (3, 4) are entirely made of composite material.

Abstract: A device for rescue from the interior of a confined space via a manhole which includes at least a tray, a prying structure and two elements for tightening of a person to the tray and the prying structure respectively. The tray is elongated and includes on one of its sides at least two means of coupling where the prying structure is inserted; the other side being smooth. Also defined is a method of utilization of said device.

Abstract: The invention relates to an electrical bonding device of a shielding (3) of electrical cables (5) in aircraft arranged in its structure in an area (15) made with a carbon fiber-based composite, comprising a metallic plate (9) with a lug (7) where a bonding lead (1) projecting from the shielding (3) is connected, being fixed to said area (15) by means of titanium rivets (11) installed under dry conditions with cadmium steel rings (17), which are coated with a sealing material (19).

Abstract: A manhole assembly in the lower skin (37) of an aircraft wing made of a composite material for giving access to an installation placed inside said aircraft wing such as a fuel tank, comprising an inner cover (31) and an outer cover (33) joined by first fastener means (35); the lower skin (37) being configured with a rebated edge (45) around the manhole so that the outer cover (33) can be mounted over the lower skin (37) maintaining the aerodynamic continuity in the aircraft wing surface; the inner cover (31) being mounted over the lower skin (37) by its inner surface with a sealing profile (41) between them and being joined to the lower skin (37) by second fastener means (47).

Abstract: Method for locating pressure losses in vacuum bags used in the manufacturing of composite material parts, according to which the vacuum bag with a part in its interior coated by airweave at a pressure lower than atmospheric pressure, is exposed to contact with a gas dispersion at atmospheric pressure of solid suspended tracing particles, preferably tar, which in the event of there being pressure losses in the vacuum bag, are deposited in the airweave areas close to them. The contact between the vacuum bag and the gas dispersion is performed preferably through an applier of said gas dispersion over the vacuum bag through an application device, either in open surroundings or in closed surroundings such as an autoclave.

Abstract: A device for the fixing of a prismatic mechanical test piece, which consists of two mechanisms that secure the test piece (7) on both sides, where each mechanism consists of two independent blocks (1 and 2), the second block (2) being displaceable in relation to the first (1), at least two rods (3) and a cylinder (4) for assisting the attachment between both blocks (1 and 2), a screw (5) for assuring the attachment between both blocks (1 and 2), and an adapter plate (6) which is adjusted to the second block (2) by means of a pin or bolt (8). Moreover, both blocks (1 and 2) have on the surface facing the test piece (7), an inclined plane (9) which has a grinding at each end in the form of a dovetail (10), such that the test piece (7) remains secured between the two grindings (10).

Abstract: A fairing system for a horizontal stabilizer of an aircraft and to a process for installing said system, such that the fairing system for the sealing of the horizontal stabilizer and the fuselage of the aircraft includes a primary fairing arranged on the horizontal stabilizer of the aircraft, the primary fairing being solidly connected to the horizontal stabilizer which is in turn trimmable with respect to the fuselage, the fairing system in turn comprising a secondary fairing such that the primary fairing is coupled to the horizontal stabilizer through supports arranged in the direction of the chord of the primary fairing, said supports being located in the outer part of said primary fairing with respect to the fuselage, the secondary fairing being arranged in the outer part of the supports.

Abstract: A metalization structure of aircraft panels and process for obtaining such structure including a panel made in composite material, the panel including a metal mesh or foil in its outer part, said panel further including a bore which in turn comprises a shank and an upper countersinking, such that the mentioned panel is fixed to another structural aircraft element by means of metal fixing elements. The structure includes a metallization layer arranged on the upper countersinking, extending in the adjacent area of the metal mesh or foil, such that it is ensured that electrical continuity exists between the upper countersinking and the metal mesh or foil during the time that the lightning bolt strikes the structure of the panel, further ensuring that most of the current discharged by the lightning bolt is conducted over the surface of the structure of the panel.