Abstract: A method for monitoring the coordinated execution of sequenced tasks by an electronic device including a main electronic card including at least one main processor synchronized to a main clock and at least one auxiliary electronic card including at least one auxiliary processor synchronized to an auxiliary clock, includes emitting by the main processor of a coordination marker to the auxiliary processor at the start of each main time period; emitting by the auxiliary processor of a response word formed on the basis of the last coordination marker received to the main processor at the end of each auxiliary time period; validating by the main processor of the response word received with respect to the first coordination marker emitted; and signaling by the main processor if the response word received is not valid so as to signal a defect of coordination of the auxiliary processor.

Abstract: The invention relates to a method for producing a composite component reinforced by stiffening elements. Composite component is produced by the inside gluing of a monolithic component to a multiplicity of stiffening elements by means of an adhesive suitable for this particular application. Stiffening elements are formed with a fiber reinforced, amorphous thermoplastic material. Monolithic component of composite component consists of a fiber reinforced duroplastic material—for example a composite epoxy matrix—in which are embedded, for reinforcement, carbon fibers, basalt fibers, natural fibers, ceramic fibers, Aramide® fibers, Kevlar® fibers or any combination thereof. Monolithic component is glued to thermoplastic stiffening elements by an adhesive under the influence of pressure and temperature. Here a tolerance compensation is carried out essentially by stiffening elements, if necessary being plastically deformed, so that high dimensional stability is achieved.

Abstract: A system for managing a user's access rights to avionic information, loaded on board an aircraft, that includes at least one identification device able to read the user's identity information contained on a personal card, and an avionic computer having means of managing access rights able to authenticate the user and determine access rights to avionic information based on the user's identity.

Abstract: An avionic system for an aircraft including at least two pieces of equipment which can exchange information by means of at least one electrical bus for simultaneous bidirectional communication, in which the information can be exchanged between pieces of equipment via an optical bus that can be connected to the electrical interfaces of the equipment. The optical bus of the avionic system includes at least one optical cable having at least one optical fiber and, at each end, a connector having means for converting electrical signals into optical signals and means for converting optical signals into electrical signals. The optical bus is connected to the electrical outlets of existing equipment.

Abstract: A process for the production of a stiffener made of composite material that includes a central part with wings on both sides such that when the wings are resting against an element to be reinforced, the central part is separated from the element to be reinforced, with the process including producing a flat strip (16) that includes at least one layer of fibers, placing it on a mold (26) that includes at least one hollow shape that corresponds to the central part of the stiffener that is to be produced, heating the strip (16), and deforming it in such a way as to make it assume the shapes of the mold (26), characterized in that it includes exerting a transverse traction on the strip (16) during the deformation of the strip.

Abstract: A storage system for an emergency apparatus provided in a conveyance includes at least one structure-holder connectable to a structural component of the conveyance. A frame is attached to the at least one structure-holder, and a carrier is configured to receive the emergency apparatus. A locking apparatus has a locking position in which the carrier is fastened to the frame, and an unlocking position in which the carrier is detached from the frame. A belt element is fixedly connected to the carrier. A first end of a retaining belt is connectable to a structural component of the conveyance via a belt-winder, and a second end of the retaining belt is fastenable in a detachable manner via a belt lock to the belt element.

Abstract: A storage compartment is provided for a transportation means, for mounting in an overhead region. The storage compartment includes, but is not limited to a universal housing module and a transformable container module. Various container modules, in particular fixed bins and pivot bins, can be installed in the universal housing module without this requiring any alteration of the housing module. The transformable container module can be converted within the housing module from a state as a fixed container to a state as a movable chute.

Abstract: The invention relates to a curtain support assembly to receive a curtain rail for a curtain for separating at least two regions in a cabin of a vehicle, comprising one or several header components for covering a space formed between the curtain rail and a ceiling in the cabin. The assembly according to the invention comprises one or several load-bearing frame structures, each comprising at least one profile component, on which in each case on at least one side the header components are arranged. The frame structure may be made from standard components and may comprise header components that are hardly subjected to any mechanical loads and that are therefore less demanding to produce.

Abstract: An oxygen supply system is provided for generating oxygen from cabin air in an aircraft. The oxygen supply system exhibits a modular cabin unit with an oxygen port and a decentralized oxygen supply unit with an oxygen outlet, and the decentralized oxygen supply unit is set up in the modular cabin unit. The decentralized oxygen supply unit is set up to generate oxygen-enriched air from the cabin air by means of electrical power, and the oxygen-enriched air can be provided to the oxygen port of the modular cabin unit via the oxygen outlet.

Abstract: A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component.

Abstract: The invention relates to a sensor network for determining the position of devices and gear in an aircraft. The sensor network exhibits several sensor nodes, which have an autonomous power supply. The sensor nodes can communicate wirelessly with each other and with a central processing unit. The position of each individual sensor node can be determined by evaluating high-frequency signal parameters.

Abstract: A data transmission network comprising: a base comprising: a base light source and a base light detector; a plurality of nodes, each node comprising a node light source and a node light detector; and a plurality of optical fibers arranged to form a optical fiber network. Each optical fiber is arranged to receive light from the base light source, transmit the light received from the base light source to one or more of the node light detectors via an air gap, receive light from one or more of the node light sources via an air gap, and transmit the light received from the node light source(s) towards the base light detector.

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: A preferred embodiment of the invention relates to a cyclone separator for a vacuum toilet system, with a casing; an input-side swirl generator, whose input openings impart a swirl to the inflowing fluid; a separating wall arranged in the casing, which encloses the fluid stream in the cyclone separator ring-like and whose interior cross section tapers downstream; and a collection tank in the casing for receiving and accumulating constituents separated out of the fluid. In addition, the invention relates to a wastewater tank and vacuum toilet system having such a cyclone separator.

Abstract: Disclosed is a display system for an aircraft cockpit. The display system includes a plurality of display devices, each of which comprises at least one viewing screen configured to display a display format, and a cursor management unit linked to each display device and configured for moving a cursor over sensitive objects on the viewing screens of the display devices.

Abstract: A heating system according to the invention comprises a heating layer that is integrated into a prepreg layer of a high-resistance prepreg material. The heating layer may comprise a bonded heating fabric, a metal oxide coating or electrically conductive threads. According to the invention, the heating system is integrated into a component to be heated. This component may consist, for example, of a floor panel for an aircraft.

Abstract: A process for manufacturing a piece made of composite material with a hollow form and including a fiber preform (50) that is embedded in a matrix, includes placing the preform (50) in a first chamber (64) delimited by a mold (52) that is in contact with the surface of the piece to be produced outside of the hollow form and a counter-mold (54) that is in contact with the surface of the piece to be produced inside of the hollow form, and using a mold (52) that is made in at least two parts (52.1, 52.2) and elements (78) for controlling the spacing of the at least two parts (52.1, 52.2) that are contiguous using the expansion phenomenon during the polymerization phase.

Abstract: A retaining nut comprises a nut body and a plurality of axially extending integrally formed deflectable locking fingers. The locking fingers have a frusto-conical surface opposite a threaded surface. The frusto-conical surface of the locking fingers are adapted to co-operate with a conical washer. Tightening the threaded nut on a threaded shaft against the washer causes the locking fingers to deflect radially towards the shaft. This provides a secure radial clamping of the nut on the shaft.

Abstract: A process for producing a panel for acoustic treatment including a resistive porous layer, an alveolar structure, a reflective layer with openings, and a drainage plate having a furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film a core whose cross-section is adapted to that of the evacuation pipe so that the core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the core, demolding the drainage plate and removing the core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

Abstract: Thermal test apparatus comprising a specimen supported by a fixture, a thermal shroud comprising a flexible insulating fabric forming an enclosure around at least a portion of the specimen, and a temperature controlled air supply connected to an opening formed in the enclosure for delivering a supply of temperature controlled air into the enclosure. Also, a method of conducting a thermal test.