Abstract: The disclosed embodiments relate to a device for protection against intrusions into the landing gear housings of an aircraft, including at least one sensor, for at least one housing, covering at least one housing entry area and connected to a calculator capable of processing the data from the sensor for detecting the intrusion of a target and generating intrusion occurrence information for triggering an alarm, wherein the calculator is connected to a device for providing aircraft flight phases and/or ground speed information, the device including a means adapted for changing the detection status from an active mode to an inactive mode based on the flight phases and/or ground speed information.

Abstract: A computer-aided method for predicting particle uptake by a surface of an object moving in a flow current. The method includes preparing a discrete model of the object and the surrounding flow, including a projection area for projecting the particles formed by a mesh of cells with an identical size, and a mesh of cells of the surface. The method also includes simulating the projection of particles with a different size from the projection area on the surface, both the density Di of projected particles and their size distribution being identical for the cell. The method further includes obtaining for each cell of the surface the local uptake efficiency parameter by dividing the density Df of particles impacting against the cell by the density Di of particles projected from the projection area.

Abstract: The present invention provides a method for providing a fault diagnosis for at least one system, in particular of an aircraft. The method comprises: (a) providing a number N1, n1?[1, . . . , N1], of systems, wherein the n1-th system, in each case, provides a number N2, n2?[1, . . . , N2], of instances of a main function of a number N3, n3?[1, . . . , N3], of main functions of the aircraft; (b) providing a number N4, n4?[1, . . . , N4], of IMA modules, wherein in each case the n4-th IMA module provides resources at least for the respective n2-th instances of the main functions; (c) providing a generic diagnostic unit; (d) instantiating the generic diagnostic unit to provide a predetermined number N5, n5?[1, . . . , N5], of instances of the generic diagnostic unit; and (e) configuring the n5-th instance, in each case, of the generic diagnostic unit for adaption of the corresponding n5-th diagnostic unit to at least one system.

Abstract: A method and device for optimizing the orientation of a laser anemometer on an aircraft. The device can determine an optimal orientation of a sighting axis of the anemometer and deduce therefrom the orientations of the other sighting axes.

Abstract: A method for automatically managing a lateral trajectory upon triggering an emergency descent includes determining a value of lateral offset and generating an offset setpoint by using the value of lateral offset. The generating an offset setpoint includes calculating a sum of the value of lateral offset and any initial value of lateral offset defined between a central axis of a protected sector that the aircraft travels along and an initial lateral trajectory. The offset setpoint is selected to be the smaller of the sum or a lateral offset maximum, which maintains the aircraft within the protected sector at all times. The aircraft is then operated to move the aircraft to the offset setpoint during the emergency descent, which helps avoid further air traffic that may be located at different altitude levels within the same protected sector, especially along the central axis.

Abstract: A system for spraying liquid (100) for a windshield (111) of an aircraft including a spray-liquid supply circuit (101), a pressurized-gas supply circuit (102) designed to purge the spray-liquid supply circuit, and at least one nozzle (114) disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on a windshield, characterized in that the system includes an auxiliary means of compression (107) ready to compress gas designed to circulate in the pressurized-gas supply circuit, the auxiliary means of compression being positioned near the nozzle. Also, an aircraft cockpit provided with at least such a spray system.

Abstract: A power rectifying circuit for an electric current signal supplied by an alternating power source, which includes: two separate switching assemblies adapted to be connected to a power terminal of the source, wherein at least one switching assembly includes a plurality of boost cells in cascade, each boost cell including a diode, a switch mechanism and a capacitor, the capacitors of the two terminal boost cells of the switching assemblies having one terminal in common. The circuit may include two assemblies of boost cells, and can be used in electric systems onboard aircrafts.

Abstract: A headrest includes a first part referred to as the lower part, equipped with a connecting unit enabling an adjustable connection of the headrest to the seat back of a pilot seat, and a second part referred to as the upper part, located opposite the lower part, as well as a front face intended to serve as a support surface for the head of a user. A receptacle, connected to the mask, stores an oxygen mask and/or a supply line. The upper part of the headrest forms a hinged cover on the lower part of the headrest and it closes the receptacle. A seat, a cockpit, and an aircraft include such headrest.

Abstract: A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers being mounted to pivot between an open position and a closed position, said substitution device comprising a body, two anchors attaching to the engine mounts of the engine support mast, and bearing portions adapted to receive support portions belonging to the protective covers. A method for installing such a substitution device in a nacelle, which makes it possible to close the engine covers and authorize the movement of the aircraft.

Abstract: An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.

Abstract: A support structure for an air supply arrangement for air conditioning aircraft passenger cabins. The air supply arrangement comprises at least one centrally controlled cabin ventilation system and an individually adjustable cabin ventilation system. The support structure includes: a first section for receiving and/or integrating cabin ventilation system components, a second section for receiving and/or integrating passenger emergency oxygen supply components and a third section comprising a plurality of receiving devices. Each receiving device receives and releasably secures an active module for individually adjustable cabin ventilation. The third section has at least the number of receiving devices required for at least one receiving device to be associated with each seating row for a maximum number of seating rows arrangeable in the cabin A supply system includes at least one such support structure and at least one of the active modules. A method is provided for configuring a corresponding supply system.

Abstract: An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead.

Abstract: Process for assembling a first part made of metal material and a second part made of composite material, by an attachment element, which includes: —pre-piercing the parts to form a recess with a diameter D1 in the first and the second parts; —installing an insert having a variable diameter in the direction of the thickness of the parts in the recess, the insert including a main hollow body and at least one flange designed to rest at least partially against the outside surface of a part, the insert being designed to accommodate the attachment element; generating residual compression constraints by radial expansion on the inner wall of the insert by an expansion tool having an outside diameter that works with the inside diameter of the insert in at least one zone of the two parts along the circumference of the insert; —boring the recess of the main body wider so that the insert has a final inside diameter that is significantly greater than the outside diameter of the attachment element to allow play between the

Abstract: A wireless communication device for an aircraft that includes at least one antenna, for example a wide-band antenna, and a transparent multilayered substrate, for example a side glazing, a front glazing or a porthole of the aircraft, adapted for receiving the at least one antenna. At least a portion of one layer of the substrate is at least partially reflective to electromagnetic waves transmitted or received by the at least one antenna, wherein the at least one portion of the layer of the substrate is located at least partially opposite the at least one antenna. The at least one portion of the layer of the substrate can be a de-icing or defogging heating film.

Abstract: A pylon for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge, as well as a first hot air distribution channel passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel belonging to a system for supplying pressurized air to the aircraft. The second channel is housed inside the first channel.

Abstract: The present invention relates to a fuselage nose door for sealing an opening in the hull of an aircraft. In order to make loading and unloading as efficient as possible, a door shell is proposed that is movably held between a closed setting and an open setting by a bearing device, wherein the door shell can be pivoted and shifted in relation to the bearing device. The invention also relates to an aircraft with such fuselage nose door. In addition, the invention also relates to a method for opening and closing an opening in the hull of an aircraft with a fuselage nose door, which has a door shell that is movably held by a bearing device between the closed setting and open setting, wherein the door shell is pivoted and shifted in relation to the bearing device in the opening and closing process.

Abstract: A device for selective emergency evacuation of persons from a first level to a second level situated above the first level, or to a third level situated below the first level. For evacuation to the second level a stair arrangement is provided. One end of the device is connected to the first level while the other end is displaceable between the second level and the third level or vice versa. For evacuation to the third level, the device is changeable to a slide. The device may provide for emergency evacuation of persons from a first level deck, or passenger deck of a blended wing-body aircraft, selectively to the top, second level of the aircraft, or to the bottom third level of the aircraft.

Abstract: A differential pressure-controlled locking mechanism (10) comprises a housing (12), as well as a first pressure chamber (14) which is arranged in the housing (12) and which is connectable to a first ambient zone. A second pressure chamber, arranged in the housing (12), is connectable to a second ambient zone and is separated from the first pressure chamber (14) by a mobile separating device (18). The separating device (18) is in an inactive position when the pressure in the first pressure chamber (14) is equal to the pressure in the second pressure chamber. Conversely, the separating device (18) is movable from its inactive position into a differential pressure position when a predetermined differential pressure acts on the separating device (18). An actuation element (22), which is held in a first position by the separating device (18) when the separating device (18) is in its inactive position, is movable into a second position when the mobile separating device (18) is in its differential pressure position.

Abstract: An anti-lightning system for a composite structure having an external surface configured to be subjected to an air flow, the aforementioned system including at least one electrically conducting strip and fasteners attaching this strip to the aforementioned structure. According to the disclosed embodiments, with this structure including holes configured to accept the fastenings for the strip, at least some these fastenings comprise an attachment element that attaches the lightning to this structure. This attachment element is configured to be inserted in the hole with its upper part substantially flush with the external surface of the structure, this attachment element being in electrical contact with the electrically conducting strip. The electrically conducting strip is configured to be positioned on the opposite side of the structure to the external surface and electrically earthed.

Abstract: An image generating illumination device is provided for interior surfaces of a means of transport. The illumination device includes, but is not limited to at least one or several projection units and a light-emitting diode arrangement. The projection units are designed to project a continuous image onto the surface of hat racks that are arranged one beside the other, and the light-emitting diode arrangement is designed to illuminate ceiling panels. The light that is projected by the light-emitting diode arrangement merges seamlessly into the continuous image.