Abstract: A passenger supply arrangement provides a communications system and comfort system for a passenger of an aeroplane. The passenger supply arrangement includes a presentation surface configured to be integrated into a backrest of a passenger seat of an aeroplane and a passenger supply module configured to be disposed above the passengers seats of the aeroplane. The passenger supply module includes at least one projector configured to project an image onto the presentation surface. The image includes a monitoring area for playback of video and an operating area for displaying and for actuation of operating elements of the passenger supply module.

Abstract: The present invention provides a digital signal processor, a communication system comprising such a digital signal processor and a method for operating such a digital signal processor. The digital signal processor for a communication system in an aircraft cabin of an aircraft comprises a provision means for providing a predeterminable digital signal suitable for forming a respective wave form for mapping a respective pre-determined service signal and a pre-determined noise signal.

Abstract: An aerofoil connection on a fuselage airframe comprising a plurality of double-jointed coupling members. In each case at least two z-coupling members extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members are arranged in the region of two longitudinal edges of a fuselage airframe recess wherein the xz-coupling members are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis. The xz-coupling members are capable of absorbing force components parallel to the x-axis as well as force components which arise parallel to the z-axis.

Abstract: An avionics device able to be installed on board an aircraft, including means of processing information and a connector able to receive and/or transmit information, the aforementioned connector including an electrical coupling interface able to transmit and/or receive information in the form of electrical signals, and an electro-optical connection interface able to convert electrical signals into optical signals and to transmit information in the form of optical signals and/or receive information in the form of optical signals and convert these optical signals into electrical signals.

Abstract: Disclosed are methods for firmly joining fiber-reinforced, plastic-based adherends, wherein depressions are introduced into opposing lateral surfaces of the adherends, and have injected into them a fiber-reinforced plastic material that serves as an adhesive, a device for implementing such a method, as well as a component joined in this way.

Abstract: The invention relates to the automatic detection of the presence of non-authorized persons in the vicinity of an apparatus of the aircraft type. To this end, the invention comprises equipping persons with radio transmitters for identifying them as authorized personnel. The aircraft are also fitted, such as at the existing PODs, with a transceiver device of a radio identification system of the RFID type for recognition of the persons wearing the radio transmitters. Only the persons who are not authorized in the vicinity of the aircraft initiate an alarm procedure.

Abstract: An aircraft pylon support system for mounting and supporting aircraft propulsion systems to a fuselage section of an aircraft that includes an internal, central support box disposed within and extending across the interior of an aircraft fuselage, and external support boxes extending laterally into pylons disposed at both sides of the aircraft, each of the internal and external support boxes being made of a composite material and structured as multi-spar boxes containing lateral spars and at least one central spar, wherein the central and lateral support boxes are connected together to provide a continuous interface therebetween with a full transfer of loads therebetween and between any interrupted, intermediate frame members.

Abstract: A device for the protection against the rupture of pipes carrying a fluid includes two or more flow channels and a closing element which interrupts the flow of fluid if a predetermined permissible volume flow is exceeded. At least one of the flow channels can be closed by a test closure in order to increase the flow speed in the remaining flow channels and for test purposes to bring about a movement of the closing element into the closing position. In this way, devices for the protection against the rupture of pipes integrated into complex systems carrying a fluid can be tested in situ to verify their proper functioning.

Abstract: The invention relates to a method for protecting a multi-phase autotransformer for an aircraft, including the steps of receiving (100) values of current output from (Ia, Ib) the first and second phases and a value of current input into (IB) the second phase; determining (101), from these received values of the second phase, a value of current representative of the operation (IFb) of the second phase; determining (102), as a function of this determined value and of the value of current output from (Ia) the first phase, a value representative of the homopolar current (Idet-a) flowing in the first phase; comparing (104) this value of homopolar current (Idet-a) with a first predetermined threshold value (S1) at least during a first predetermined period (D1); and controlling (106) the values of currents input into (IA, IB) and/or output from (Ia, Ib) the phases as a function of the said first comparison.

Abstract: The invention relates to a device for limiting the deflection of a door (1), particularly a hatch or a freight door, arranged in a fuselage cell (3) of an aircraft, having at least one holding element (5) arranged preferably in the region of a door jamb (4) or in the region of a door leaf edge (7). In order to ensure deflection limitation for doors, hatches and freight doors in aircraft which can be triggered manually independently of an actuation of the normal locking system, it is proposed according to the invention that the at least one holding element (5) can, if there is a sufficient pressure difference ?p between the internal pressure pi prevailing in the fuselage cell (3) and the outside air pressure pa prevailing outside of the fuselage cell (3), be brought into engagement with at least one abutment (6) arranged in the region of the door leaf edge (7) or the door jamb (4).

Abstract: An exemplary embodiment of the present invention provides a compartment for accommodating at least one flight crewmember, comprising a first module and a stowage area, wherein the first module comprises a first rest facility, wherein the first rest facility is arranged substantially perpendicular to the longitudinal axis of the aircraft, as well as substantially parallel to the traverse axis of the aircraft, and wherein the stowage area is substantially arranged under the first rest facility.

Abstract: An electric flight control system onboard an aircraft provided with flight control surfaces and controllers for controlling these surfaces, that include at least one local electro-hydraulic generator to supply hydraulic servocontrols connected to flight control surfaces.

Abstract: A press device for the energy-efficient curing of a sandwich component for an aircraft, includes an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides. The sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space. At least one of at least one cover layer and the core structure includes a curable duroplastic plastic material. A conveying device feeds heated air through the core structure of the sandwich component in a closed heated-air circuit or preferably in an open heated-air circuit in order to ensure energy-efficient curing of the sandwich component from the inside out. The heated air is temperature-controlled by a heater. In the case of an open heated-air circuit, heat recovery by a heat exchanger is provided.

Abstract: The device displays on one and the same indicator (11) of display means (7) indication elements (14, 16, 17, 33) illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a possible exceeding of a limit temperature of the turbine engine, a margin to a possible exceeding of a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: The present invention concerns fastening devices. More particularly, but not exclusively, this invention concerns a fastening device suitable for fastening two or more separate items together. The invention provides a fastening device comprising: a first fixing element 12 and a second fixing element 14. The first fixing element 12 comprises a locking member 16 and the second fixing element comprises an elongate member 18. The locking member 16 is configured to allow passage of the elongate member 18 through the first fixing element 12 in a first direction and resist passage of the elongate member 18 through the first fixing element 12 in a second direction, the second direction being opposite to the first direction.

Abstract: An aircraft nacelle includes an air intake, connected to a means of propulsion, which defines a longitudinal direction, an outer wall, an inner duct including an annular flange connected, by means of connecting elements, to the means of propulsion, and a forward frame and a rear frame which connects the outer wall and the inner duct. The rear frame includes a first ring and a second ring, in longitudinal planes. The rings include a first connection to the outer wall. The first ring includes a second connection with the annular flange. The second ring includes a third connection with the inner duct. The third connection is remote from the second connection.

Abstract: A method for producing an acoustic treatment panel, including: assembling two plates, at least one of which is deformed so as to separate the plates locally in order to form cavities of a cellular structure between the two plates, said cavities being delimited by facets and partitions formed by at least one of the deformed plates, producing at least one opening on the facets of one of the two plates, and pressing an acoustically resistive plate against the surface of the cellular structure including the openings.

Abstract: A method of producing a structural component comprising manufacturing a structural component from a moisture absorbable material the toughness of which increases with increasing moisture absorption and subsequently subjecting the structural component to at least one of elevated temperature and humidity for a period of time such that the structural component attains a predetermined moisture content and distribution.

Abstract: The invention relates to a process and an on-board system for evaluating flight strategies aboard an aircraft, linked with a flight plan (13) of the aircraft, including: calculation means (5) for determining relations between the flight parameters including parameters of time, of fuel quantity, of altitude and of speed, interface means (9) for providing at least one envelope of values (25a-25d) representative of a domain of definition of a plurality of flight strategies, interface means (9) for providing at least one determined strategy defined by determined values assumed by the flight parameters at a reference point, interface means (9) to allow the selection and setting of the value of a first parameter among said flight parameters, generating and supplying another envelope of values allowing exploration of another plurality of possible strategies, and interface means (9) to allow the selection and setting of the value of a second parameter, generating and supplying another determined strategy.

Abstract: Method and device for implementing the thrust reversers of an aircraft. According to the invention, the following successive steps are carried out automatically: • deployment (E3) of the previously armed thrust reversers of the aircraft; • application (E5) of a predetermined engine speed; reduction (E6) of the engine speed; —re-furling (E7) of the thrust reversers of the aircraft.