Abstract: A method and device for managing communication channels for data exchange from an aircraft establishes at least one connection path between the aircraft and at least one ground entity with a plurality of communication channels of at least two different types. After detecting an event such as modification of a communication channel condition or a modification of aircraft position, a communication configuration enabling the aircraft to receive or transmit data from or to the ground entity via at least one of the communication channels is determined. A mechanism for establishing at least one connection path is then adapted based on the communication configuration. Advantageously, the transmission of at least one datum includes determining a priority level of the datum and determining the type of communication channel of the connection path, the datum being transmitted if the determined type of communication channel is compatible with the priority level.

Abstract: A toilet arrangement for a vehicle includes a first toilet compartment, an adjacent second toilet compartment and a partition wall situated between the first toilet compartment and the second toilet compartment, wherein the partition wall is movably supported and designed for being transferred into an open position, in which the partition between the first toilet compartment and the second toilet compartment is removed. This makes it possible to convert two relatively small toilet compartments into a larger toilet compartment that is suitable for use by persons with limited mobility.

Abstract: The display system (1) comprises means (5, 11A, 14) to take into account a recorded symbology, in the event of a malfunction in the emission of a symbology, to perform a display of symbology.

Abstract: An overhead bin for use on both sides in a passenger cabin of an aircraft, includes a first baggage compartment and a second baggage compartment, a first opening and a second opening for loading items into the first baggage compartment and into the second baggage compartment, and a partition for dividing the first baggage compartment from the second baggage compartment. The first baggage compartment and the second baggage compartment differ from each other in their shape and/or alignment. With several overhead bins, the alignment of a larger and a smaller baggage bin can alternate so that adequate bin space for stowing hand baggage is available to passengers in the center seats.

Abstract: An apparatus for testing an aircraft tank system includes a fuel supply device including a fuel reservoir, a fuel supply line for supplying fuel from the fuel reservoir to a fuel outlet of the fuel supply device, and a first isolation valve disposed in the fuel supply line. A fuel transfer line transfers fuel from the fuel outlet of the fuel supply device to the aircraft tank system and a second isolation valve is disposed in the fuel transfer line. An electronic control unit (ECU) of the apparatus is adapted to control the first isolation valve and the second isolation valve so as to interrupt the supply of fuel through the fuel supply line and the transfer of fuel through the fuel transfer line, respectively, in response to a test parameter signal provided to the electronic control unit (ECU).

Abstract: A device and method for the contactless and therefore non-destructive measurement of a degree of dryness of a coat of paint applied to a substrate. The device comprises at least one transmitter for electromagnetic radiation, at least one receiver for determining the absorption of the electromagnetic radiation radiated into the coat of paint, and a measuring means. In the measuring means, the raw measured values measured by the receiver are processed and the degree of dryness, calculated therefrom, of the coat of paint is displayed. Either microwave radiation or infrared radiation in the near infrared range is used as measuring radiation, at least one time-dependent measurement of the absorption at a constant wavelength being made in both cases. In addition, the invention relates to a method for determining the degree of dryness of a coat of paint by means of the device.

Abstract: An aircraft structure includes a wing spar (10), with orbital frames (24, 24?, 24?) arranged in transverse planes, right and left horizontal spars (26) connected to the wing spar (10) at the upper panel (14) of the spar respectively to the right and to the left of the spar, and for each right or left horizontal spar (26), a triangular panel (50) that includes a wall (60), a first edge arranged at the horizontal spar (26), a second side arranged at the wing spar (10), and a third side at which a first rectilinear oblique reinforcement (62) connecting the horizontal spar (26) and the wing spar (10) is provided, characterized in that the triangular panel (50) includes at least one second rectilinear oblique reinforcement (64) that connects the horizontal spar (26) and the wing spar (10).

Abstract: A fire extinction device comprises a reservoir (2) of extinguishing agent and means for generating a pressurized gas (30) such that the gas generated (16) may enter the reservoir (2) when the extinguishing agent (4) is to be ejected onto a fire zone. The device of the invention comprises furthermore a refractory separating element (40) between the extinguishing agent (4) and the pressurizing gas generated (16), in order to avoid heat exchanges between them and to optimise the ejection of the extinguishing agent (4).

Abstract: A process for manufacturing a piece made of composite material that includes fibers that are immersed in a resin matrix, whereby the piece is placed in a first chamber with at least one flexible wall. The process includes a thermal cycle with essentially a first phase (50) at a first temperature during which the resin is liquid or in the “gel” state, and then a second phase (52) at a second temperature that is higher than the first during which solidification of the piece takes place by polymerization of the resin. An external pressure is applied to the outside of the first chamber and an internal pressure is generated inside the first chamber, wherein during the first phase (50), the relative internal pressure is less than 0 during a first period, and then greater than 0 during a second period preceding the beginning of the polymerization for reducing the porosity rate.

Abstract: A container assembly and aircraft fuselage for air transport of freight. The container assembly includes a spacer layer formed of malleable material. The spacer layer is positioned between and in contact with a bottom plate of the container and the floor of an aircraft. The aircraft fuselage for the freight transport is equipped with a floor adapted to receive and bear a load. A spacer layer integral with the floor is positioned between the floor and the load. The spacer layer is formed of a malleable material.

Abstract: A method for predicting the aerodynamic performance of an aircraft element under predetermined conditions, the aircraft element having at least one break at least partially separating two parts that cannot or should not be modeled with a common envelope form, in which: a digital form representative of the form that the aircraft element assumes under the predetermined conditions studied and in which each break is represented, is created, for each break, a totally non-coincident boundary surface at the joining of the two parts is created, and a partial structured meshing around each part is generated, the two partial meshings made in this way being independent of one another, and digital aerodynamic simulation computations using this meshing are carried out with the aid of an aerodynamic computation code capable of processing a totally non-coincident join.

Abstract: A method for producing, in a composite material, a component that has a re-entrant angle, includes stacking layers of fibres which have been pre-impregnated with a resin so as to obtain a preform and placing the preform in a tooling fixture in order to subject it to a polymerization cycle including a temperature cycle, with a temperature-increase phase and at least one soak at which the temperature is maintained, and a pressure cycle on the outside of the tooling fixture with a pressure-increase phase and a pressure-hold phase, with the layers of pre-impregnated fibres being able to slip against one another when the temperature of the temperature cycle is equal to or higher than a threshold temperature Tf dependent on the resin. The temperature-increase phase includes a soak at a temperature higher than or equal to Tf, the soak beginning before the end of the pressure-increase phase.

Abstract: Process for linear transparency friction stir welding of a flange of a stiffener onto at least one panel for an aircraft, wherein a weld bead is made along the flange of the stiffener and wherein the weld bead extends in cross-section from a first lateral edge to an opposite second lateral edge of the stiffener flange. System for the implementation of the above welding process, which includes three welding heads arranged as a triangle, each of which includes a rotating pin as well as a shoulder extending at the base of said rotating pin.

Abstract: A method for disinfecting a vehicle drinking water tank is disclosed, wherein the method is designed for dynamic disinfection. By providing a vehicle drinking water tank with a spray diffuser, which is arranged inside the vehicle drinking water tank, the disinfecting liquid can be sprayed over substantially the entire inner surface of the tank. Partial filling of the drinking water tank with a disinfecting liquid starts the disinfection method. The dynamics of the disinfection method are achieved by spraying the disinfecting liquid in such a way that a moved film of disinfecting liquid is formed and wets an inner surface of the drinking water tank. Material transport at the inner wall of the tank is improved and mechanical shear forces act on the biofilm, which is to be removed and/or disinfected, in combination with the biochemical disinfection forces.

Abstract: An apparatus and method are provided for reducing the drag caused by a complex-section part in an airflow, for example the landing gear of an aircraft, making it possible to optimize the lift/drag ratio and to reduce the aerodynamic noise by reducing the local noise source. To do so, the complex-section part is masked with a special casing. More specifically, the aero-acoustically optimized complex-section metal mechanical part is fitted with an aerodynamically shaped cover made of several longitudinal parts articulated with hinges to facilitate their installation. This cover is attached to at least two supports placed away from one another along the axis of the part, each support locally mating with the section of the part.

Abstract: Method and arrangement for supplying essentially hollow bodies with equipment wherein the hollow bodies each have a transverse dimension and a longitudinal dimension being larger than the transverse dimension. The bodies have at least one opening for accessing their interior from outside along their longitudinal dimension. The hollow bodies are arranged essentially side-by-side along the longitudinal dimension and they are moved along their transverse dimension in a clocked fashion. An arrangement comprises a plurality of conveyor means for moving hollow bodies, wherein the conveyor means are arranged such that the hollow bodies are arranged side-by-side along their longitudinal dimension and moved along their transverse dimension in a clocked fashion.

Abstract: Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever (58, 95).

Abstract: A method for monitoring the operating health of a lighting system having a plurality of operating components, in one example includes acquiring test data from a plurality of operating components at a plurality of different operating states of the lighting system, and a data set is acquired for each operating state of the lighting system, and a plurality of data sets are acquired. A model of the lighting system may be constructed using the plurality of data sets.

Abstract: A wheel drive system for an aircraft that features at least one electric motor and at least one fuel cell as energy source for the electric motor, wherein the electric motor is coupleable to at least one wheel of at least one landing gear of the aircraft. The wheel drive system reduces the fuel consumption and lowers the emission of CO2 and pollutants—primarily carbon monoxide and unburned hydrocarbons. Persons, vehicles and other aircraft furthermore are not endangered by a jet blast while the aircraft is taxiing because the main engines do not have to be started until the take-off and landing strip is reached. The operation of the wheel drive system furthermore leads to a reduced noise pollution.

Abstract: A method of servicing an aircraft cooling system comprises connecting a refilling container containing a two-phase refrigerant to a refrigerant connection provided in a cooling circuit of the cooling system, supplying refrigerant from the refilling container into the cooling circuit of the cooling system, and operating a condenser disposed in the cooling circuit so as to liquefy gaseous refrigerant flowing through the cooling circuit.