Abstract: The invention relates to a device for fastening systems in an aircraft. It comprises on the one hand a ring-shaped base (2) and on the other hand arms (4, 6) borne by the ring-shaped base (2), extending outward from the latter and bearing systems supports.

Abstract: An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).

Abstract: A method monitors at least one avionic system connected to a communication medium that includes at least one active communication switch component. The method includes determining a state of the switch component and evaluating an indicator of a state of the communication medium from the state of the switch component and from a predetermined modeling of communication flows of the communication medium. The method also includes selecting and activating an alarm according to the evaluated state of the communication medium and according to a predetermined modeling of consequences of the evaluated state of the communication medium on a function of the at least one avionic system. A corresponding device and a method for determining conditions for alarm activation are also disclosed.

Abstract: The invention relates to a method for manufacturing a core composite (1, 20, 26) having a folded honeycomb core (2, 21, 29) provided on both sides with cover layers (3, 4, 22, 23, 27, 28) wherein the folded honeycomb core (2, 21, 29) has a number of drainage-enabling channels (5). First a core filler material (16, 17) is introduced into the folded honeycomb core (2, 21, 29) at least in some areas in order to provide the filler material with sufficient stability for the subsequent sewing process. The cover layers (3, 4, 22, 23, 27, 28) which are not yet impregnated with a curable plastics material are then placed on the folded honeycomb core (2, 21, 29) and stitched to this along the base lines (6 to 8) and/or apex lines (9, 10) at least in some sections by means of a sewing thread (19). The infiltration of the overall structure with a curable plastics material is then carried out followed by hardening by applying pressure and/or temperature.

Abstract: A cargo loading system for a means of transport with a power drive unit 201 for moving cargo in a cargo hold of a means of transport and with an operational control unit. The operational control unit is designed for controlling the entire movement of the cargo by means of the power drive unit.

Abstract: An assembly includes a support fastened to a structure by a fastening element extending along a fastening axis. and includes a bore for the passage of the fastening element. The fastening element includes a surface for driving in rotation. The assembly includes a device for locking the fastening element in rotation including a moveable end resting against the surface for driving in rotation the fastening element. The locking device is configured so that, at rest, the moveable end enters into the volume normally occupied by the surface of the fastening element. The locking device is placed between the support and the fastening element so as to be deformed elastically by the surface when the fastening element is put in place in the bore of the support. The moveable end includes locking shapes capable of interacting with the external shapes of the driving surface to stop the fastening element from rotating.

Abstract: Methods and apparatus are described for an aircraft network that permits an automatic configuring and/or repairing of the network.

Abstract: The present invention provides methods for positioning at least one component, in particular a seat, in or on an aircraft or spacecraft comprising the following steps: controlling at least one light source of the aircraft or spacecraft to display at least one desired position of at least one component; and positioning the at least one component in the at least one desired position displayed.

Abstract: An emergency supply system for a transportation means is provided. The system includes at least one fuel cell, a hydrogen tank, an oxygen tank, an extinguishing agent container, an oxidant supply unit and an extinguishing-agent supply unit. The oxidant supply unit includes an oxygen inlet connectable to the oxygen tank, an air inlet connectable to an air source, and an oxidant outlet connected to an oxidant inlet of the fuel cell. The oxidant supply unit either conveys oxygen from the oxygen inlet or air from the air inlet to the oxidant outlet. The extinguishing-agent supply unit includes a first extinguishing agent inlet connected to an exhaust air outlet of the fuel cell, a second extinguishing agent inlet connected to the extinguishing agent container, and an extinguishing agent outlet that is connectable to an extinguishing-agent inlet unit of at least one space of the transportation means.

Abstract: A device for securing a mobile device in an aircraft cabin includes a first connection element having a bar receiving member. The device further has a second connection element which includes a bar which is suitable for co-operating with the bar receiving member of the first connection element, the bar being moveable between an unlocking position and a locking position, in which the bar of the second connection element is able to be brought into engagement with the bar receiving member of the first connection element.

Abstract: An aerodynamic body, with at least one ancillary flap arranged such that it can be moved on the aerodynamic body with the aid of a guide mechanism, and with a drive device for purposes of actuating the ancillary flap, the guide mechanism having a pivotal articulation, by which the ancillary flap is articulated on the aerodynamic body such that it can be extended, and which is arranged in a rear region of the ancillary flap as viewed in the flow direction.

Abstract: A monument complex is provided for a rear area of a passenger cabin. The rear contour of the monument complex is adapted to the contour of the bulkhead so that an additional wash basin can be installed without there being any loss of space in the passenger cabin.

Abstract: A power distribution device has a number N1 of conversion devices comprising a respective cascade generator for converting a first part of a mechanical power into a first electrical power with an alternating voltage of constant amplitude and constant frequency, and comprising a respective frequency converter for supplying a second electrical power with the alternating voltage of constant amplitude and constant frequency as a function of a second part of the mechanical power; a number N2 of constant frequency buses for the respective transfer of the electrical power of constant frequency supplied by the at least one conversion device to a number N3 of loads which comprises at least a number N4 of loads to be controlled in terms of their power consumption; and a number N4 of control devices, wherein the respective control device is coupled between the respective load to be controlled and the constant frequency bus and is designed to control the power consumption of the load to be controlled.

Abstract: A wing of an aircraft provided with a main wing and an arrangement of leading edge lifting bodies, which as seen with reference to the incident flow direction are arranged on the leading edge, which are adjustably arranged on the main wing one behind another as seen in the spanwise direction of the main wing by means of respectively two positioning devices spaced apart from one another in the spanwise direction of the main wing. The wing has a connecting device, which is coupled to each of two adjacent leading edge lifting bodies, wherein the connecting device is configured such that in the event of a fracture of a positioning device of a positioning body external forces acting on the latter are transferred via the respective connecting device to the leading edge lifting bodies coupled up via the latter.

Abstract: A component for building a fuselage section of an aircraft includes a border area connectable to a corresponding further border area of a further component so as to form an electrically conductive joint, wherein the component includes a composite structure.

Abstract: The device for controlling the display of a radar image on board an aircraft, in particular a weather radar image, is suitable for performing at least one predetermined test on a radar echo in order to decide on a representation corresponding to the echo in a radar image display.

Abstract: A method for the manufacture of a fibre composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mould core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fibre composite component with a multiplicity of openings, each of which is edged by an integral collar.

Abstract: A structural assembly for an aircraft comprising a cover with outer and inner faces, an inner support element and urging means on the inner support element, wherein opposing edges of the cover are fixedly mounted relative to the inner support element, and the urging means acts on the inner face of the cover to urge the cover to distend outwardly and locate in a predetermined position. Another aspect of the invention relates to a method of forming a structural assembly for an aircraft comprising an cover with outer and inner faces, an inner support element and urging means on the inner support element, the method comprising the steps of fixedly mounting opposing edges of the cover relative to the inner support element and operating the urging means to act on the inner face of the cover so that the cover is urged to distend outwardly into a predetermined position.

Abstract: Device for localizing acoustic sources and/or measuring their intensities, intended in particular to be used in confined spaces, the device including at least one acoustic antenna having a first series of microphones delimiting a first volume, and a second series of microphones delimiting a volume containing at least substantially the first series of microphones.

Abstract: A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin.