Abstract: A thermal regulation device for a member to be heated or to be cooled includes a fluid-circulation conduit having at least one flexible part able to deform according to the pressure of the fluid within the conduit, and at least one contact zone coming into contact with said member when the pressure of the fluid in the conduit is higher than a given pressure and which is moved away from said member when the pressure of the fluid in the conduit is below the given pressure, the thermal regulation device including regulation means able to vary the pressure of the fluid in the conduit.

Abstract: A method for manufacturing a part made from composite material of a thermoplastic or thermosetting matrix reinforced with fibers includes producing a structure of fibers, that is optionally pre-impregnated. The method further includes aligning and juxtaposing fibers, while stretching them between return elements, and keeping them separated from each other, so as to obtain a first layer. The method includes superimposing, on said first layer, a second layer obtained in an identical manner to the first, in which the fibers are parallel to those of the first layer and kept apart from it. The method includes repeating the superimposing operation until the desired thickness is obtained and stiffening the material making up the matrix (M) by a method that suits its nature.

Abstract: The method for warning of risk of rupture or deformation of a part made of a composite material when it is subjected to a force relates to a part including a fibre-reinforced thermoplastic or thermohardenable matrix. The method includes arranging the fibers in a lattice structure produced by winding fibers to form bars that join together or intersect at nodes. The method includes designing at least one bar of the lattice and/or integrating, into the part, at least one additional bar with a determined location and tensile strength and associating, with the at least one bar, inside the part, a sensor to detect the rupture thereof. The method further includes associating, with the sensor, an emitter, outside the part, for a signal relating to the rupture.

Abstract: An assembly comprising a housing (6) having walls (11) and containing groups of electrical cells (7). Each wall contains at least one space in which, at a given time, a flow of thermal fluid (F2) can be present. The said space, and thus the corresponding wall (11), has a flow of fluid inlet and outlet. In a flow of fluid-tight manner, the flow of fluid inlet and outlet communicate with, respectively, a supply (25a) of thermal flow of fluid and a discharge (25b) of said flow of fluid, so that the flow of fluid can circulate in said space. Through the surrounding wall and said sealed communications, said space is physically isolated from the cells, so that the flow of fluid (F2) therein and the interior space (9) of the housing do not communicate. The wall (11) extends parallel to at least one of the lateral faces of at least one said cell (7).

Abstract: A window frame element (30) for a vehicle (10), in particular a motor vehicle, said frame element being substantially horizontal and configured to extend, to the exterior of the vehicle, along a substantially horizontal edge of a window (20, 22) and in the extension of this window, this element comprising a body (32) configured to be carried by a support of the vehicle characterised in that it further comprises at least one screen (28) for displaying pixel information and a control and communication system (34), which is configured to receive first signals (36) and to transmit second signals (38) to said at least one screen (28), which is configured to display information in accordance with said second signals.

Abstract: The method for warning of risk of rupture or deformation of a part made of a composite material when it is subjected to a force relates to a part including a fibre-reinforced thermoplastic or thermohardenable matrix. The method includes arranging the fibers in a lattice structure produced by winding fibers to form bars that join together or intersect at nodes. The method includes designing at least one bar of the lattice and/or integrating, into the part, at least one additional bar with a determined location and tensile strength and associating, with the at least one bar, inside the part, a sensor to detect the rupture thereof. The method further includes associating, with the sensor, an emitter, outside the part, for a signal relating to the rupture.

Abstract: A method for manufacturing a part made from composite material of a thermoplastic or thermosetting matrix reinforced with fibers includes producing a structure of fibers, that is optionally pre-impregnated. The method further includes aligning and juxtaposing fibers, while stretching them between return elements, and keeping them separated from each other, so as to obtain a first layer. The method includes superimposing, on said first layer, a second layer obtained in an identical manner to the first, in which the fibers are parallel to those of the first layer and kept apart from it. The method includes repeating the superimposing operation until the desired thickness is obtained and stiffening the material making up the matrix (M) by a method that suits its nature.

Abstract: A link arm for connecting a first unsuspended mass to a second suspended mass, and its manufacturing method are provided. In some embodiment the arm applies in particular to a suspension system for a motor vehicle, wherein the arm is able to equip a wheel suspension by having triangular housings to receive a stub axle of the wheel and two connecting links to the chassis of the vehicle. In some embodiments, the arm comprises housings to receive a first linkage joint to the first mass, and at least a second linkage joint to the second mass, and comprises: a stiffening portion which comprises a first thermoplastic or thermosetting matrix composite material reinforced with fibers and which comprises a peripheral rim of the arm, and an anti-buckling portion interposed in the stiffening portion and extending from the rim over substantially the entire arm.

Abstract: A connection device is suitable for connecting two tubes to one another, and optionally to a fluid tank for fluid transmission piping of an aircraft or a spacecraft Also disclosed are pipes incorporating said tubes and said device; and a method for manufacturing said device. The device includes an injection-molded tip that has at least one angled or inwardly curved area and is made of a composite material with a thermoplastic matrix reinforced by a reinforcement system including carbon fibers. The tip has a median longitudinal mold parting plane (P). The carbon fibers extend so as to be oriented along the tip, which incorporates mechanical and vibratory stiffening means which are integrally molded with the tip and lie in said parting plane or symmetrically relative to said plane in said at least one area and/or immediately near said area.

Abstract: The invention aims to make aircraft doors easier to open by preventing ice formation or, at the very least, favoring rapid breaking of the ice on the door edges connected to the skin of the fuselage. To that end, it is provided to supply energy along the door when specific conditions are met. According to one embodiment, an anti-icing/de-icing system for an aircraft door (1) according to the invention includes an excitation energy source and devices (81 to 83) for dissipating such energy extending parallel to a side surface (11) of the aircraft door (1), along a sealing gasket (4) support (5) secured to the door (1) across from a fuselage (2) side surface (21) framing (20) the door (1). The sealing gasket (4) of the door (1) is compressed against bearing (6) from a side surface (25) of the fuselage (2) when the door (1) is closed.

Abstract: The present invention relates to a link arm for connecting a first unsuspended mass to a second suspended mass, and its manufacturing method. The invention applies in particular to a suspension system for a motor vehicle, wherein the arm is able to equip a wheel suspension by having triangular housings to receive a stub axle of the wheel and two connecting links to the chassis of the vehicle. This arm (1) comprises housings (14, 15, 16) to receive a first linkage joint (14a) to the first mass, and at least a second linkage joint (15, 16) to the second mass, and comprises: a stiffening portion (2) which comprises a first thermoplastic or thermosetting matrix composite material reinforced with fibers and which comprises a peripheral rim (8) of the arm, and an anti-buckling portion (3) interposed in the stiffening portion and extending from the rim over substantially the entire arm.

Abstract: A connecting rod comprises a convex elongated body around a longitudinal axis of symmetry and two connecting ends for connecting to adjacent structures. The connecting rod includes two shells with two longitudinal edges that are assembled in these edges and that each have a base of at least one shell web including continuous shell fibers primarily parallel to this axis of symmetry and impregnated with a thermoplastic shell matrix. The connecting rod incorporates at least one assembly web wound around and along the shells, and assembly fibers primarily inclined relative to the axis and impregnated with a thermoplastic assembly matrix remelted in contact with the shell matrix.

Abstract: A connection device is suitable for connecting two tubes to one another, and optionally to a fluid tank for fluid transmission piping of an aircraft or a spacecraft Also disclosed are pipes incorporating said tubes and said device; and a method for manufacturing said device. The device includes an injection-molded tip that has at least one angled or inwardly curved area and is made of a composite material with a thermoplastic matrix reinforced by a reinforcement system including carbon fibers. The tip has a median longitudinal mold parting plane (P). The carbon fibers extend so as to be oriented along the tip, which incorporates mechanical and vibratory stiffening means which are integrally molded with the tip and lie in said parting plane or symmetrically relative to said plane in said at least one area and/or immediately near said area.

Abstract: The present invention relates to a connecting rod, an aeronautic floor structure incorporating it, and a method for manufacturing this connecting rod. The invention applies to a connecting rod suitable for reacting primarily axial forces, in particular in the aeronautics field. This connecting rod comprises a tubular body with two ends and two heads for connecting those ends to adjacent structures and that is suitable for reacting primarily axial forces, each head comprising an end-piece flared toward the body and glued on the latter in a gluing interface. According to the invention, the connecting rod comprises at least one first sealing gasket mounted radially between and against the body and the end-piece of each head, axially toward the inside of the gluing interface.

Abstract: The present invention relates to a composite connecting rod, an aeronautic ceiling or floor structure incorporating it, and a method for manufacturing this connecting rod. The invention applies to reacting primarily axial forces, in particular in the aeronautics field. The connecting rod comprises a convex elongated body around a longitudinal axis of symmetry and two connecting ends for connecting to adjacent structures, and it includes two shells with two longitudinal edges that are assembled in these edges and that each have a base of at least one shell web including continuous shell fibers primarily parallel to this axis of symmetry and impregnated with a thermoplastic shell matrix. According to the invention, the connecting rod incorporates means for assembling shells comprising at least one assembly web wound around and along shells at said body, and assembly fibers primarily inclined relative to said axis and impregnated with a thermoplastic assembly matrix remelted in contact with the shell matrix.

Abstract: The invention aims to make aircraft doors easier to open by preventing ice formation or, at the very least, favoring rapid breaking of the ice on the door edges connected to the skin of the fuselage. To that end, it is provided to supply energy along the door when specific conditions are met. According to one embodiment, an anti-icing/de-icing system for an aircraft door (1) according to the invention includes an excitation energy source and devices (81 to 83) for dissipating such energy extending parallel to a side surface (11) of the aircraft door (1), along a sealing gasket (4) support (5) secured to the door (1) across from a fuselage (2) side surface (21) framing (20) the door (1). The sealing gasket (4) of the door (1) is compressed against bearing (6) from a side surface (25) of the fuselage (2) when the door (1) is closed.

Abstract: A ducting and associated method is provide in which the ducting includes a pipe with a thermoplastic or thermoplastic elastomeric layer and a reinforcing layer. The pipe has a curved or bent geometry and the reinforcing layer is made of a composite material based on reinforcement in intimate and direct contact with the subjacent layer. The geometry is obtained by hot forming the inner layer to give the geometry, and the reinforcement is either impregnated with a thermosetting matrix to form a thermosetting composite, or reinforcing fibers are intermixed with thermoplastic fibers or powders, or impregnated with a plastic polymeric coating that is curable chemically. Alternatively, the inner layer is first covered with the reinforcing layer in which the reinforcement includes reinforcing fibers intermixed with a thermoplastic material in the form of fibers, film or powder is blow-molded to give the pipe its final geometry.

Abstract: A profile with one or more portion(s) whose cross-sections are substantially U-shaped, locally provided with capabilities of increasing torsional rigidity and potentially flexural rigidity, a load-bearing structural element of a vehicle such as a support grille of an electrical and/or hydraulic system incorporating that profile, and a method of manufacturing that profile are provided. The profile includes at least one U-shaped portion having a slot bounded by two wings and a core and that is locally provided and capable for increasing torsional rigidity, the profile being formed of a fibre-reinforced plastic composite, having at least one cross brace formed in the slot from a single part with the wings and the core. The wings and the core are reinforced by fibres mostly oriented in the longitudinal direction of the profile, with more than 60% of the fibres oriented in a ?30° to +30° angle with that direction.

Abstract: The present invention relates to a ducting for a fluid transfer pipeline for an aircraft or spacecraft, an aeronautical structure incorporating it and a method for producing this ducting. The ducting (1) comprises a pipe (2) with a thermoplastic or thermoplastic elastomeric layer (4) and a reinforcing layer (5) surmounting it.

Abstract: A ducting and associated method is provide in which the ducting includes a pipe with a thermoplastic or thermoplastic elastomeric layer and a reinforcing layer. The pipe has a curved or bent geometry and the reinforcing layer is made of a composite material based on reinforcement in intimate and direct contact with the subjacent layer. The geometry is obtained by hot forming the inner layer to give the geometry, and the reinforcement is either impregnated with a thermosetting matrix to form a thermosetting composite, or reinforcing fibers are intermixed with thermoplastic fibers or powders, or impregnated with a plastic polymeric coating that is curable chemically. Alternatively, the inner layer is first covered with the reinforcing layer in which the reinforcement includes reinforcing fibers intermixed with a thermoplastic material in the form of fibers, film or powder is blow-molded to give the pipe its final geometry.