Abstract: A composite structure, including a laminate that includes a set of plies, the laminate extending between a first edge and a second edge and including a rising ramp and a falling ramp. The rising ramp includes a starting point and an upper point and the falling ramp includes the upper point and an end point. Plies are partially located over their preceding ply and alternatively extend from the first edge or the second edge and are shorter than the ply located before the preceding ply so that their ends are stepped successively until they reach the top of the ramp.

Abstract: A device and a process for manufacturing a composite part, the device comprising four molding mandrels that can be arranged in a mold arrangement in which they form a mold for the composite part, as well as a locking mandrel configured to lock the molding mandrels in the mold arrangement and to be extracted from between the molding mandrels to release the molding mandrels from their mold arrangement. The locking mandrel extends from one longitudinal end of the molding mandrels to another opposite longitudinal end of the molding mandrels.

Abstract: A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.

Abstract: A composite structure, including a laminate that includes a set of plies, the laminate extending between a first edge and a second edge and including a rising ramp and a falling ramp. The rising ramp includes a starting point and an upper point and the falling ramp includes the upper point and an end point. Plies are partially located over their preceding ply and alternatively extend from the first edge or the second edge and are shorter than the ply located before the preceding ply so that their ends are stepped successively until they reach the top of the ramp.

Abstract: A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.

Abstract: A method and apparatus is provided for harvesting electricity from a biofilm retained in a zero chamber, no interphase container, the biofilm having a portion supporting aerobic microbial activity and a second portion supporting anaerobic microbial activity, wherein the first and the second portion are in direct physical contact. A ground or a power harvester is electrically connected, directly or indirectly, to the second portion of the biofilm.

Abstract: A method and apparatus is provided for harvesting electricity from a biofilm retained in a zero chamber, no interphase container, the biofilm having a portion supporting aerobic microbial activity and a second portion supporting anaerobic microbial activity, wherein the first and the second portion are in direct physical contact. A power harvester is electrically connected, directly or indirectly, to the second portion of the biofilm.

Abstract: A fitting for transporting an industrial part, the fitting including: a first fitting member comprising a first surface, and a second fitting member including a second surface, wherein the first surface of the first fitting member includes a protuberance and the second surface of the second fitting member includes a recess, wherein the protuberance and the recess are configured such that the protuberance is insertable in the recess when the protuberance is inserted along the recess the first fitting member and the second fitting member are slidable one on another along at least a first direction.

Abstract: A method and apparatus is provided for harvesting electricity from a biofilm retained in a zero chamber, no interphase container, the biofilm having a portion supporting aerobic microbial activity and a second portion supporting anaerobic microbial activity, wherein the first and the second portion are in direct physical contact. A ground or a power harvester is electrically connected, directly or indirectly, to the second portion of the biofilm.

Abstract: A method and apparatus is provided for harvesting electricity from a biofilm retained in a zero chamber, no interphase container, the biofilm having a portion supporting aerobic microbial activity and a second portion supporting anaerobic microbial activity, wherein the first and the second portion are in direct physical contact. A power harvester is electrically connected, directly or indirectly, to the second portion of the biofilm.

Abstract: One embodiment relates to a computer-implemented method of compiling a software program into an executable binary file, including determining a data layout in the binary file and a data layout in the executable's dynamically allocated memory. The method includes taking into account data types of data as a factor in determining a data layout for the binary file and for the executable's dynamically allocated memory, wherein the data types include a floating-point data type and a non-floating-point data type. Other embodiments, aspects and features are also disclosed herein.

Abstract: Method of manufacture of one or more pairs of components in composite material (11, 13; 11?, 13?) intended to form part of aerofoils located on both sides of the axis of symmetry of an aircraft whose shape has a conical tendency in the longitudinal direction, the angle of conicity being less than 10°, that comprises the following stages: a) Lay-up of layers on a flat tape lay-up table forming the laminate of a hypothetical component formed by all of the components of said pairs (11, 13; 11?, 13?), the components of each pair being arranged adjacently and the first components (11, 11?) and the second components (13, 13?) of each pair being arranged alternately, and the whole being arranged symmetrically relative to a hypothetical horizontal axis X-X of the tape lay-up jig; b) Cutting of the flat laminates corresponding to each of said components); c) Forming and curing said components.

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: 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: It is intended for installing and fitting, in conjunction with other iron fittings, a fairing on an aircraft in correspondence with a housing located at the junction of a stabilizer and a fuselage of an aircraft structure. Wherein each iron fitting comprises: a base plate (5) joined integrally to a torsion box (6) of the stabilizer (3); a mobile support (7) joined integrally to the fairing (1) and which is guided, over a linear movement, over the base plate (5); an adjustment screw (8) that is coupled into a threaded opening (15) of the base plate (5), which screw joins this base plate (5) to the mobile support (7), with the rotation of said adjustment screw (8) in combination with a retaining plate (23) dragging the respective mobile support (7) that is integral to the fairing (1).

Abstract: The lifting surfaces comprise a torsion box capable of bearing aerodynamic and inertial loads. The torsion box has lateral parts that are connected together by an attachment comprising a rib, having a central upper part and a central support lower part joined only by angled cross bars, forming a truss structure along the length of the central support upper part and the central support lower part. The angled cross bars are attached to the upper and the lower parts of the central support: alternatively to both sides of a plane of symmetry defined by said upper and lower parts of the central support, dividing the torsion box in the two lateral parts making a zone of access perpendicular to the length of the central supports, where said zone of access is closed with a piece provided with at least one hole for permanent access.

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: 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: It is intended for installing and fitting, in conjunction with other iron fittings, a fairing on an aircraft in correspondence with a housing located at the junction of a stabiliser and a fuselage of an aircraft structure. Wherein each iron fitting comprises: a base plate (5) joined integrally to a torsion box (6) of the stabiliser (3); a mobile support (7) joined integrally to the fairing (1) and which is guided, over a linear movement, over the base plate (5); an adjustment screw (8) that is coupled into a threaded opening (15) of the base plate (5), which screw joins this base plate (5) to the mobile support (7), with the rotation of said adjustment screw (8) in combination with a retaining plate (23) dragging the respective mobile support (7) that is integral to the fairing (1).

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.