Abstract: A virtual window assembly for an airborne vehicle includes at least one camera configured to capture a panoramic and time-resolved image data stream from the view to the outside of the airborne vehicle, an image data processor coupled to the camera and configured to receive the captured image data stream and split the image data stream into a plurality of partial image data streams corresponding to different viewing angles of the panoramic image data stream, and a plurality of electronic displays mounted to an inside of a hull of the airborne vehicle, coupled to the image data processor and configured to receive partial image data streams. Each of the electronic displays is configured to display one of the partial image data streams so that the physical mounting location of the electronic displays in the airborne vehicle corresponds to the associated camera viewing angle of the displayed partial image data stream.

Abstract: A cap for forming a sealed cavity around an end of a fastener protruding from a structure. The cap has: a cap body with an annular base terminating at a rim which surrounds an opening into a central cavity; an annular skirt providing an annular pocket between the skirt and the base; and an inlet hole in the skirt. The inlet hole is in fluid communication with the pocket and arranged to interconnect with a sealing material injection device to provide a flow of sealing material through the skirt via the inlet hole into the pocket. An outlet is also provided in the skirt. The outlet is in fluid communication with the pocket and arranged to enable air to escape the pocket through the skirt via the outlet hole as the sealing material flows from the inlet hole into the pocket.

Abstract: A method and tool for repairing a damaged zone of an aircraft radome, using the actual radome itself as a heating chamber to avoid resorting to an autoclave and the removal of certain parts of the radome which cannot withstand the curing temperature needed for the repair. The method for repairing a radome, wherein the radome comprises a composite panel exhibiting a double curvature forming a dome, the panel comprising at least one damaged zone, comprises the steps of closing an interior space of the panel using a cap to form a repair chamber. The surface of the panel forms the repair chamber containing the damaged zone. Another step is heating the space inside the repair chamber to form a heating chamber allowing the curing expected for repairing the damaged zone.

Abstract: A method of automatic positioning a seat in an apparatus comprising two cameras located on either side of the seat, each one in a position able to acquire images of a face of a user seated on the seat. The seat comprises at least one motor, each motor acting on a position of the seat along a predefined axis. The method comprises: for each camera: obtaining a position of a predefined image zone in which at least one eye of a user of the apparatus should be located; acquiring an image of a user seated on the seat; detecting at least one eye of the seated user in the image acquired; and obtaining a relative position between each eye detected and the predefined zone. By using each relative position obtained, at least one motor is actuated until each predefined zone contains at least one eye of the seated user.

Abstract: A new and improved system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes: a first adapter member having a first mating portion that is adhesively bonded with a profile of a first component of the structure in more than one plane, and a first attachment portion connected to the first mating portion; a second adapter member having a second mating portion that is adhesively bonded with a profile of a second component of the structure in more than one plane, and a second attachment portion connected to the second mating portion; and a connector member to securely interconnect the first and second attachment portions of the first and second adapter members.

Abstract: An aircraft landing gear comprising a wheel rotatably mounted on an axle, a first gearing element that rotates with the wheel, a second gearing element configured to mesh with the first gearing element such that rotation of the first gearing element causes rotation of the second gearing element, wherein the second gearing element is connected to a generator, such that rotation of the second gearing element causes the generator to generate electrical energy, further comprising a heat dissipation device connected to the generator wherein the heat dissipation device comprises an electrical heating element connectable to the generator to receive generated electrical energy and convert it to heat energy, and a fluid receptacle adjacent the heating element, such that fluid in the receptacle can be heated. An aircraft landing gear further comprising a cavitation braking device, an aircraft and a method of braking.

Abstract: A method and equipment for installing a tapped insert in a cylindrical bore, the equipment including a tool body comprising a threaded end portion, the threaded end portion being adapted to a threaded inner wall portion of a cylindrical body of the tapped insert; a screw of diameter lower than a diameter of an inner bore of the tool body, the comprising at one end a thread complementary to the inner tapped aperture of the core of the tapped insert; and a positioning ring installed to slide on the tool body, the tool body and the positioning ring comprising complementary sliding means adapted to enable relative sliding of the positioning ring on the tool body in a longitudinal direction and to maintain the positioning ring on the tool body in a defined longitudinal transverse section.

Abstract: System and method to generate automatically a compact application code suitable for taking advantage of the intrinsic power of processors. The system can generate the application code executable by a processor from a formal specification associated with an application, the formal specification including operators, and the system including an analyzer to code each operator of the formal specification by a corresponding operation code followed by a minimum number of input code(s) and output code identifying input and output parameters associated with the operator, thus automatically generating a compact application code suitable for being stored in a memory associated with the processor and for being executed by an interpreter of the processor.

Abstract: A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; c) determining, as a function of said information, at least one deviation between at least one parameter relating to a landing position of the aircraft on the landing runway and a reference relating to a central longitudinal axis of the landing runway; d) comparing this deviation with a predetermined threshold; and e) as a function of the result of the comparison carried out in step d), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.

Abstract: A system for testing bonded joints that comprises a swing tool, an actuator, pressure measuring device and a first fixing arrangement. The actuator of the system is configured to apply a compression force or a traction force on the swing tool in order to separate two elements, and the pressure measuring device is configured to measure the force applied on the swing tool. A method for testing bonded joints using the system is also provided.

Abstract: A cable guide arrangement for use in a luggage bin, in particular an aircraft luggage bin, comprises a shaft bearing element and a shaft element rotatably mounted in the shaft bearing element and through which there passes an opening extending along a central axis of the shaft element. The cable guide arrangement further comprises at least one cable guide element connected to the shaft bearing element or to the shaft element and comprising a first and a second guide portion. The first guide portion is configured to deflect a cable, extending in the radial direction with respect to the central axis of the shaft element, with a defined bending radius in the direction of the central axis of the shaft element. The second guide portion is configured to guide the cable parallel to the central axis of the shaft element through the opening extending through the shaft element.

Abstract: A device for visually scaring animal species, in particular bird species includes means for generating at least one visual signal including at least one image, varying in size over time, which simulates approach via an increase in the size of the image. For example, the visual signal includes one of the following images: eyes, a disc, and a spiral.

Abstract: An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is located on a wall other than a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall.

Abstract: A raceway and method of forming a raceway is disclosed in which one or more intumescent layers are disposed on the raceway.

Abstract: A connection box for a system of an aircraft is provided, which includes a plurality of connection boxes, with a holder for holding a line connector for the supply of the system of the aircraft, wherein the system includes, in addition to this connection box, a further connection box with a holder for holding a line connector for the supply of the system of the aircraft. The connection box is configured to receive the further connection box in such a way that both connection boxes can be mounted under an opening in the floor of the aircraft so that both connection boxes are accessible from the opposite side of the floor through the opening in the floor.

Abstract: A process for manufacturing a vehicle cabin part (1) to fit in a gap (9) between a first component (5) and a second component (7) including: providing different sealing bodies (3?) each having a first lateral face (11?) conforming to an inner surface (17?) of the first component (5?) and a second lateral face (13?) spaced a certain distance (15?) from the first lateral face (11?); select one of the sealing bodies having a certain distance that fits the gap (9) between the first component (5) and the second component (7); insert the selected sealing body (3) into the gap (9) such that the first lateral face (11) at least partially adjoins the inner surface (17) of the first component (5) and the second lateral face (13) at least partially adjoins the outer surface (21) of the second component (7) facing the first component (5).

Abstract: A seating arrangement in a cabin of an aircraft includes a floor with a first surface area, a furnishing item with a respective boundary surface, which extends in a vertical direction from the cabin floor, and toward which is directed a first surface area, at least two folding seats, and optionally a partitioning system. The folding seats are arranged on the boundary surface of the furnishing item, and set up to be swiveled into a neutral position and use position, wherein an individual located in the first surface area can sit on the at least two folding seats in the use position. At least one of the at least two folding seats is not designed as a flight attendant seat.

Abstract: The rudder bar includes two actuation arrangements, each provided with two pedals, each actuation arrangement having a frame provided with two rails arranged on either side of said frame and being in the form of a concave curve, and, associated with each one of said rails, a movable carriage, each one of said movable carriages bearing one of said pedals, each one of said movable carriages being configured such that it can be moved on the associated rail, for a direction command, under an action exerted by at least one foot of a pilot on at least one of said pedals.

Abstract: An aircraft with an auxiliary power unit attached to the aircraft fuselage via an attachment system. The auxiliary power unit is placed inside the aircraft fuselage structure. The attachment system comprises a plurality of structural wires that link the auxiliary power unit to the aircraft fuselage structure. An attachment device is located at the end of each structural wire to connect the structural wire to the aircraft fuselage structure. Each attachment device comprises a metallic plate adjacent to the aircraft fuselage structure and a layer of damping elastomeric material adjacent to the metallic plate. The metallic plate is placed between the layer of damping elastomeric material and the aircraft fuselage structure. The attachment device is joined to the aircraft fuselage structure by attachment fasteners.