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: Procedure for the manufacture of a composite material part (11) having, at least, one reinforced area (13) of greater thickness than the surrounding areas, in which the dimensions and laying up sequence of the plies (21, 21?, 21?, 21??) that are used in the laying up step of said reinforced area (13), are determined so that, at least one of the plies (21?, 21?, 21??) crosses over the ply situated beneath it for reducing the volume of said reinforced area (13). The invention also refers to a composite material part (11) manufactured with said procedure, particularly a CFRP skin of an aircraft lifting surface.

Abstract: Its object is to allow measurement of the volume of fuel (2) using optic fibre cables (3); it is characterized in that, adhered to one or more of the inner faces of the tank (1) there is at least one sheet (4) in which a plurality of optic fibre cables (3) with different lengths are included, located between the inner face of the tank and the sheet (4). One set of the ends (10) of the optic fibre cables (3) are disposed so that they are in contact with the fuel (2) when it reaches their level, thereby allowing measurement of the fuel level at all times. The preferred embodiment distributes the optic fibre cables (3) on two opposing lateral faces of the tank (1) so that they cross over one another and in opposite directions to measure any fuel level. It is applied in aeronautics.

Abstract: Aircraft component which comprises at least one panel (11) of composite material, formed by a skin (13) and a plurality of stiffening stringers (15) which are configured with a core (17) and a base (19) of width (A), said stiffening stringers (15) comprising first local flarings (21) of their bases (19) intended to provide areas for joining with other parts located in flat zones of the skin (13) and second local flarings (23) of their bases (19) which are intended to provide areas for joining with other parts located in zones of the skin (13) which include change-in-thickness ramps (33), being configured in the form of two end sections (41, 45) located above flat zones of the skin (13) and a central section (43) located above one of said ramps (33) of the skin (13), one of said end sections (41, 45) acting as an area for joining with other parts.

Abstract: Fairing (9) which closes the internal end of an elevator (3) of an aircraft with respect to the fuselage section (1) on which the fairing (9) moves, with the elevator (3) arranged on a horizontal stabiliser (2) of the aircraft, such that the horizontal stabiliser (2) moves with a trim angle (?) with respect to the fuselage section (1) in turn rotating the elevator (3) with an elevator angle (?) with respect to the horizontal stabiliser (2), with the fairing (9) maintaining a distance (6) with respect to the fuselage section (1) during its movement in which the distance (6) is a minimised distance for all movement ranges of the elevator (3) for the trim angle (?) of the horizontal stabiliser (2) and the elevator angle (?) of the elevator (3), thereby reducing aerodynamic losses through parasitic resistance which is not caused by support of the aircraft. A method for obtaining the design of the fairing (9) is also disclosed.

Abstract: Composite material part (11) with stringer (31) on ramp, manufactured from a stack of fabrics, which comprises at least one zone (13) with two sectors (17, 19) having a greater thickness than that of the surrounding zones and with the stringer (31) situated on an edge (21) of said zone (13) in which: a) each group of fabrics (27, 27? . . . ; 29, 29?, . . . ) of said sectors (17, 19) has the dimensions to form on said edge (21) a ramp with an acceptable gradient 1/p so that the stringer (31) remains situated on the ramp; b) the stacking of the zone (13) is carried out firstly by placing the fabrics (27, 27?, . . . ) of the first sector (17) and on these the fabrics (29, 29?, . . . ) of the second sector (19) in such a way that in the coinciding section (35) of said edge (21) the gradient of the resulting ramp is 1/(p/2).

Abstract: Applicable in aeronautical structures provided with a first fixed component (1) and a second component (2) displaceable with respect to the first. The first (1) and second (2) components include electrically conducting surfaces. It is characterized in that it includes a first conductive piece (6, 10) fixed to the first component (1) and a second conductive piece (9) fixed to a second component (2). The first (6, 10) and second (9) piece are joined together with the possibility of sliding one on the other, in such a way that the first piece (6, 10) is connected to the conductive surface of the first component (1) and the second piece (9) to the conductive surface of the second component (2), so that, when displacements take place of the second component (2) with respect to the first (1), the first piece (1) slides on the second piece (9) maintaining the electrical conductivity between the first (1) and second (2) component.

Abstract: A part (5) of composite material having a wedge (13) between two zones (11, 15), the second zone (15) being shorter than the first zone (11), whose structure comprises from its outer surface (21) to its inner surface (23): a first section (31) formed from at least two continuous sheets (41) extending parallel to its outer surface (21), the gradient of the wedge (13) being between 20% and 50%; a wedge (33) in the shape of a triangular prism with its larger surface (27) dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section (35) formed by a plurality of continuous sheets (45) extending parallel to the surface bounded by the said first section (31) with the said wedge (33) placed upon it. The invention also relates to a process for manufacture of the part (5).

Abstract: The drainage valves have the purpose of removing the water accumulated in the lower part of fuel tanks of an aircraft, said valves being affix in correspondence with a lower skin forming part of said 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 said valves to that skin. It is characterized in that the recesses comprise a conical structure obtained by deformation of the lower skin, and with said 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 said area from weakening as it happens conventionally.

Abstract: The angular profile consists of sections (4) arranged one after another joined to each other, in order to simplify the connections between said sections (4). It is characterized in that the adjacent ends of each section (4) present in one of their sides an extension (7) complementary to a recess (8) provided in the same side of the end of the adjacent section (4) for locating the extension (7) in the recess (8) and, by means of bolted joints (9), to fix the extension (7) in the opposite side of the adjacent section (4) constituting the profile. The sections (4) and the bolted joints (9) are made of metal to provide electrical continuity. The angular profile constitutes the trailing edge of a tail rudder (1) of an HTP of an aircraft.

Abstract: The invention comprises an elastic material in order to carry out the joining and sealing between a first (2) and a second (3) element; and which has the aim of avoiding the formation of pinching of the sealing profile when carrying out the assembly and sealing between the first (2) and second (3) elements. For this, the sealing profile (6 and 7) presents a wedge-shaped configuration which projects with respect to the first (2) element, and on the sloping surface of which the second (3) element presses in order to facilitate its deformation and the assembly and sealing of the first (2) and second (3) element, in which position the surface of the wedge shape that projects with respect to the first element (2) presses against the second element (3). The invention is preferably applicable to aeronautical structures, particularly to those structures where both first and second elements form part of the aerodynamic surface.

Abstract: The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas (11, 15) of different thickness and a transition area (13) between both configured with a single slope (17), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics (21, 21?; 29, 29?) extending along the three mentioned areas (11, 13, 15); a second section formed by one or more symmetrical and balanced fabric packets (23) ending in the transition area (13) placed among one or more continuous fabrics (25); a third section formed by a symmetrical and balanced fabric packet (27) extending along the three mentioned areas (11, 13, 15) placed among one or more continuous fabrics (25).

Abstract: The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas (11, 15) of different thickness and a transition area (13) between both configured with a single slope (17), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics (21, 21?; 29, 29?) extending along the three mentioned areas (11, 13, 15); a second section formed by one or more symmetrical and balanced fabric packets (23) ending in the transition area (13) placed among one or more continuous fabrics (25); a third section formed by a symmetrical and balanced fabric packet (27) extending along the three mentioned areas (11, 13, 15) placed among one or more continuous fabrics (25).

Abstract: The invention provides a process for the alkylation of an aromatics compound with a olefin alkylation agent which comprises contacting the aromatic compound, especially benzene, with the alkylation agent, especially ethylene and/or propylene, in the presence of an oxide material which is delayered MWW-type zeolitic material, very suitably the material known as ITQ-2.

Abstract: A zeolite catalyst is described corresponding to an acid form of ITQ-7 zeolite and/or all its possible intergrowths, its method of preparation and its application for the alkylation of aromatics with olefins, alcohols or polyalkylated aromatic compounds. It is considered that the catalyst and the application to which this present invention refers are particularly valuable for the production of cumene.

Abstract: The invention provides a process for the alkylation of an aromatics compound with a olefin alkylation agent which comprises contacting the aromatic compound, especially benzene, with the alkylation agent, especially ethylene and/or propylene, in the presence of an oxide material which is delayered MWW-type zeolitic material, very suitably the material known as ITQ-2.