Abstract: The invention comprises a cylindrical reservoir (1) with a mouth (14), side through hole (3), shaft (28) and perimeter flange (8) whose top is associated with a concentric cover (2) anchored to the container (6) equipped with an upper mouth (13), vertical or diagonal grooves (16) and a lower mouth (11); the cover (2) enables the rotary or longitudinal sliding of the reservoir (1), which is activated by the pressure exerted by the cap (T) on said reservoir (1) which descends when the container is closed and takes the side through hole (3) out from inside the cover (2), descent that enables the reservoir (1) to be filled; when removing said cap (T), the reservoir (1) rises driven by the compression means (10), (17), (24) or (25) leaving the through hole (3) thereof enclosed inside the cover (2); the dose (Ds) is selected by tipping over the container (6) and when the liquid returns to the vertical position and is levelled, it is calibrated and when the cap is unscrewed, it is served and used, and so on.

Abstract: A device for the supply of fuel to aircraft includes an elevating arm (1) situated above a mobile trolley (1.2) and where the elevating arm (1) is articulated with respect to a shaft (1.1) between a first position that is substantially horizontal and parallel to the surface of the floor and a second elevated position; an adaptor assembly (2) integrally joined to the upper surface of the elevating arm (1) and from which a drive handle (5) emerges frontally which is configured to mobilise the mobile trolley (1.2) by multiple wheels (1.3); and an articulated clamp (3) actuated by an actuation mechanism (4) integrally joined to the adaptor assembly (2) on the lower and internal surface of the elevating arm (1) such that said the articulated clamp (3) is configured to be adjusted on a handle of the pit coupler.

Abstract: A container (6) and a metering cap (3) are designed to be fitted together and include a cap (3) defined as a concave component with a curved top and a sloping cylindrical neck on the side thereof, with a mouth (1) that can be closed by a stopper (T), the lower distal end (1a) of the neck extending into the concave cavity defined by the cap (3), wherein this extension does not project beyond the bottom plane defined by the lower peripheral edge (9) of the cap (3); and wherein the container (6) comprises a hemispherical protrusion (2) which corresponds to a cavity (Oi) located on one side of the top of the container (6).

Abstract: A method for manufacturing long lasting phosphorescent fabrics and articles of clothing including fabric for use in fields such as security, domestic, sports, health, professional, etc., includes (i) preparing a composition for dyeing having a strontium aluminate pigment doped with europium and dysprosium; (ii) coating a starting fabric with the composition by air knife coating or cylinder; (iii) drying; and (iv) polymerizing. The fabrics thus obtained have long lasting phosphorescent properties and a high resistance to washing, maintaining the factory specifications of the starting fabric with respect to its mechanical properties, comfort, breathability and/or high visibility properties, if relevant.

Abstract: A computer-readable storage medium, method and system for optimization-level aware branch prediction is described. A gear level is assigned to a set of application instructions that have been optimized. The gear level is also stored in a register of a branch prediction unit of a processor. Branch prediction is then performed by the processor based upon the gear level.

Abstract: A method for manufacturing long lasting phosphorescent fabrics and articles of clothing including fabric for use in fields such as security, domestic, sports, health, professional, etc., includes (i) preparing a composition for dyeing having a strontium aluminate pigment doped with europium and dysprosium; (ii) coating a starting fabric with the composition by air knife coating or cylinder; (iii) drying; and (iv) polymerizing. The fabrics thus obtained have long lasting phosphorescent properties and a high resistance to washing, maintaining the factory specifications of the starting fabric with respect to its mechanical properties, comfort, breathability and/or high visibility properties, if relevant.

Abstract: The invention relates to a cap for glass bottles comprising a body with skirting with at least three cuts made from the outside to the inside of the body, wherein a core is provided with at least three reinforcement ribs and a first concave region or area that coincides with a second concave region or area is provided on the inside of the body, creating a chamber; and wherein said second concave region is integrated into a second body attached to the first body and wherein said second body comprises a flange having a plurality of cuts, whereas in the lower part thereof, said second body has a threaded area in which a plurality of lips are defined and in which reinforcement spokes are provided contiguously.

Abstract: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

Abstract: A composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness E1 and a second zone having a thickness E2, which is made as a single part with a transition zone, external surfaces of which have gradients of magnitude, in which the structure of the stack includes; b1) a plurality of continuous plies that extend in the three zones; b2) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone; b3) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone.

Abstract: Its object is to allow measurement of the volume of fuel (2) using optic fiber 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 fiber 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 fiber 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 fiber 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: A device provides electrical continuity between aeronautical components including a first fixed component and a second component displaceable with respect to the first component. The first and second components include electrically conducting surfaces. A first conductive piece is fixed to the first component and a second conductive piece is fixed to the second component. The first and second pieces are joined together with the possibility of sliding one on the other, in such a way that the first piece is connected to the conductive surface of the first component and the second piece is connected to the conductive surface of the second component, so that, when displacements take place of the second component with respect to the first component, the first piece slides on the second piece maintaining the electrical conductivity between the first and second components.

Abstract: A computer-readable storage medium, method and system for optimization-level aware branch prediction is described. A gear level is assigned to a set of application instructions that have been optimized. The gear level is also stored in a register of a branch prediction unit of a processor. Branch prediction is then performed by the processor based upon the gear level.

Abstract: A method for laying-up the tapes of a prepeg composite material in the 0° direction of a non-planar composite component on a suitable mold using an ATL machine includes the steps of: a) determining the trajectories of the tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the curvature radius R2 of their curved segments is bigger than a predetermined value Rmin; that the gap G2p between two contiguous tapes is comprised between 0 and a predetermined value Gmax; and b) providing modified trajectories to the ATL machine. The invention also refers to a non-planar composite component such as an skin of an aircraft wing having the tapes in the 0° direction following trajectories complying with conditions described.

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: The present invention relates to a lid for glass bottles, preferably made of metal or any other type of suitable plastic material, comprising a body (1) with a skirt or external flange (2) that is segmented by conical slits, characterised in that said flange (2) comprises a plurality of longitudinal conical slits transverse to the axis of the lid and running around the periphery of the flange (2), designed to snugly fit over the external surface of the lip (4) of the neck (3) of the bottle to be sealed; the body (1) having been provided with a concentric V-shaped annular rib (5) which snugly fits against the internal contour of the mouth of the neck (3) of the bottle, which has a liner (7), said rib (5) defining an upwardly domed surface (6).

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: Procedure for the manufacture of a composite part (13) of a closed compartment, said part (13) having an access assembly to said compartment through an opening (11) in said part (13), said access assembly comprising a cover (27) for said opening (11) and a housing panel (25) for said cover (27), comprising steps of: a) providing common laminates (31, 31?, 31?) of a composite material for said cover (27) and said housing panel (25) in an uncured state; b) cutting said common laminates (31, 31?, 31?) by the perimeter foreseen for said cover (27) and separating the cover laminates (33, 33?, 33?) and the housing panel laminates (35, 35?, 35?); c) manufacturing separately, on the one side, the cover (27) using said cover laminates (31, 31?, 31?) and, on the other side, the part (13) together with said housing panel (25) using said housing panel laminates (35, 35?, 35?).

Abstract: An aircraft lifting surface structured as a torsion box comprising upper and lower skins (19, 21) stiffened by span wise stringers (25, 25?, 25?), said aircraft lifting surface comprising one or more fuel tanks (31, 33, 35, 37) arranged inside of said torsion box and separated by bulkheads (41), the stringers (25, 25?, 25?) having extended feet in the intersection areas with said bulkheads (41), also comprising filler panels (45) of said skins (19, 21) covering the holes that remain between said skins (19, 21) and said bulkheads (41) outside said intersection areas, whose configuration is adapted for covering the space between the extended feet (26, 26?) of stringers (25, 25?), leaving a gap with them of a predetermined width (W1), thereby providing a self-fastening capability over each skin plane that facilitates the attachment of said filler panels (45) to said skins (19, 21).

Abstract: A method for laying-up the tapes of a prepeg composite material in the 0° direction of a non-planar composite component on a suitable mould using an ATL machine comprising steps of: a) determining the trajectories of said tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the curvature radius R2 of their curved segments is bigger than a predetermined value Rmin; that the gap G2p between two contiguous tapes is comprised between 0 and a predetermined value Gmax; b) providing said modified trajectories to said ATL machine. The invention also refers to a non-planar composite component such as an skin of an aircraft wing having the tapes in the 0° direction following trajectories complying with said conditions.

Abstract: A composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness E1 and a second zone having a thickness E2, which is made as a single part with a transition zone, external surfaces of which have gradients of magnitude, in which the structure of the stack includes; b1) a plurality of continuous plies that extend in the three zones; b2) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone; b3) a plurality of plies that extend in the first zone and in the transition zone, terminating in a stepped manner in the transition zone.