Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes a catalytic converter, at least one hydrogen supply means, at least one air supply means, at least one outlet for oxygen depleted air, and a control unit coupled with the catalytic converter. The catalytic converter is couplable with the hydrogen supply means and is adapted for producing water under consumption of hydrogen from the at least one hydrogen supply means and oxygen. The catalytic converter is further couplable with the at least one air supply means for additionally producing oxygen depleted air. Further, the control unit is adapted for selectively operating the catalytic converter based on a demand of water and oxygen depleted air.

Abstract: To be able to transmit higher forces when retaining movable components on board an aircraft, a retaining system includes a support structure with a first retaining area and a second retaining area having a movable locking element, and a movable component with a locking receptacle forming a locking device with the locking element, and a retaining device. The movable component is movably attached to the first retaining area with the retaining device, and the movable component can be locked on the second retaining area with the locking device. The at least one movable locking element can be moved between an open setting (SOFF) and a locked setting (SVER), wherein the at least one movable locking element engages with the locking receptacle in the locked setting, so that the movable component is temporarily immovably retained, and allows the movable component to move in the open setting.

Abstract: In order to facilitate the thermoacoustic insulation of an aircraft portion, a thermoacoustic insulation module for an aircraft comprises a mat and a load-bearing structure detachably attached to the mat and supporting the mat in a curved shape, with an axis of curvature parallel to a longitudinal direction of the mat. A thermoacoustic insulation method for insulating an aircraft portion comprises a step of inserting the thermoacoustic insulation module into the aircraft portion, followed by a step of detaching the mat from the load-bearing structure, followed by a step of attaching the mat to an aircraft structure delimiting the aircraft portion, followed by a step of removing the load-bearing structure from the aircraft portion.

Abstract: A method and device for generating an optimum vertical path intended to be followed by an aircraft. The device comprises at least one database relating to fixed and moving obstacles, a data entering unit, a data processing unit implementing iterative processing to generate an optimum vertical path between an initial state and a final state as a function of flight strategies, that optimum vertical path being generated in such a manner as to be free of any collision with surrounding obstacles and to conform to energy constraints, and a data transmission link for transmitting that optimum vertical path to at least one user system.

Abstract: A method of rotatably couple a wing tip device (4) to a fixed wing (3) by a rotational joint (101) having an outer race (8) and an inner race (9) that is received in the outer race (8) one of the inner and outer races comprises a male member (76) and the other is a two-part assembly comprising a first part (9a) and a second part (9b) that together form a female member (72), the method brings the first and second parts together to form the female member (72) about the male member (76) such that the male member (76) is received in the female member (72) and fixing the first and second parts (9a, 9b) such that the race that is rotationally fixed relative to the wing tip device (4) is axially and radially retained relative to the race that is rotationally fixed relative to the fixed wing (3).

Abstract: An actuating apparatus for a polyphase motor includes five phase terminals for connecting of in each case one phase of the polyphase motor, a high terminal for applying a supply voltage (UB), a low terminal for applying a reference potential of the supply voltage (UB), a control device, wherein the control device is adapted, in four of the five phase terminals, to impress a pulse-width-modulated voltage pattern by connecting the phase terminals to the high terminal or the low terminal so that in the first phase terminal, an evaluation signal which is dependent on the angle of rotation of the polyphase motor is produced, and wherein the control device is adapted to determine the angle of rotation and/or a commutation condition of the polyphase motor from the evaluation signal.

Abstract: An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

Abstract: In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines.

Abstract: A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes inducing compressive residual stresses in a first area of the first joint region for preventing cracks by applying parallel crack retarding regions formed as stripes in the first area, drilling fastener holes in the first and second areas of the first. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint.

Abstract: A rail arrangement for an inner space of an aircraft has a first portion having first rails for receiving passenger seats and having second rails which extend transversely relative to the first rails for receiving fittings. The rails are secured to a floor structure which is arranged in the inner space. The securing of the fittings is consequently decoupled from the floor structure.

Abstract: A slide includes a carriage, a guide, and interposed pads allowing the carriage to be moved in translation in a longitudinal direction by relative sliding of the pads on contact surfaces distributed symmetrically on both sides of two planes: a horizontal plane parallel to the longitudinal direction and the transverse direction and a median plane parallel to the longitudinal direction and the vertical direction. The contact surfaces are oriented so as to form with the horizontal plane an angle between 30° and 70° inclusive. This allows a more homogeneous distribution of contact pressures, which tends to center the carriage in its guide, and the wear of the pads is more even between the pads. Such a slide also has an important advantage for the control and monitoring of the wear of the pads.

Abstract: An installation arrangement comprising a first carrier element configured to fasten an overhead luggage compartment thereto. The first element includes a main body comprising a tubular opening, a barrel-shaped component arranged inside the tubular opening, the component comprising a through hole extending substantially perpendicular to a component longitudinal axis, and a fastener to fasten a portion of the overhead luggage compartment to the main body of the first carrier element. A second carrier element of the arrangement is a rotary joint connectable to an installation rail, the rotary joint being movable around a longitudinal axis of the installation rail and an axis perpendicular to that longitudinal axis. The installation arrangement also comprises a rod configured to be coupled with the second carrier element and to fit inside the through hole, wherein the rod is connectable to the first carrier element when the rod is arranged inside the through hole.

Abstract: A device for managing configurations of an aircraft between an initial point and a final point comprises a computation module to determine at least one first evolution curve considering the aircraft to have assumed a first configuration and wherein the first evolution curve includes the first point and a final evolution curve considering the aircraft to have assumed at least one final configuration and wherein the final evolution curve or curves includes the final point, a computation module to compute at least one second point corresponding to the intersection of the first evolution curve or curves and the final evolution curve or curves, and a transmission module configured to transmit a signal representing the coordinates of the second point or points to a user device.

Abstract: The display system for an aircraft cockpit comprises a display computer configured to control the display, on a display device worn rigidly attached to a user's head, according to a first display mode comprising at least one piece of flight assistance information for the aircraft, and a masking device, associated with a cockpit side window, controllable between a transparent and opaque states. The display system comprises an extended display mode, in which the display computer is configured to determine whether a direction corresponding to the user's head orientation has an intersection with a region of interest of the side window, in the absence of an intersection, controlling the display according to the first display mode, and when there is an intersection, controlling the masking device opaque state and controlling the display according to a second display mode comprising a virtual display screen on a side window display area.

Abstract: A system for producing a component from a fibre composite material includes a moulding tool, a control unit and a plurality of mutually independent material application units, each of which includes a material store for providing fibres, a material delivery apparatus for delivering fibres from the material store and a drive device, and is configured, with the aid of the drive device, to follow a predetermined path on the moulding tool, while delivering fibres as required. The control unit controls the material application units by specifying a plurality of individual paths, so that they move autonomously along the paths. The control may, in particular, be carried out by optical projection onto the moulding tool.

Abstract: A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. The sealing device includes a flexible sealing body, which seals the intermediate space between the high lift body and the wing structure in extended positions of the high lift body.

Abstract: A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations.

Abstract: A control unit and a method for controlling a wireless data transmission between a wireless terminal and access points of a communications network in a transportation device, as well as a computer program for executing the method. The wireless terminal is assigned to two or more of the access points in such a way that one communications channel is available between the wireless terminal and the access points for wireless data transmission between the wireless terminal and the access points. A control unit is used, in the case of transmission from the access points towards the wireless terminal, to select at least one of the access points for wireless transmission to the terminal and/or in the case of transmission from the terminal towards the access points, to determine a message for further use in the communications network based on the messages received from the terminal by the access points.

Abstract: A system for managing short-circuits in an aircraft meshed electrical energy distribution network, comprising nodes connected to one another by inter-node links forming a mesh of the network. A system node comprises a switch, a current limiter, circuitry elements to measure the current intensity circulating on the link and circuitry elements to measure a voltage drop on the link, and a control unit configured to acquire a link current measurement, compare the measurement with a predetermined current threshold and, if the measurement exceeds this threshold, command the current limiter to limit the link current, acquire a link voltage drop measurement, determine a time associated with the value of the voltage drop and check whether the voltage drop is still present after a time period equal to the time obtained, and if the voltage drop is still present then, command the opening of the switch corresponding to this link.

Abstract: A test bench for generating aerodynamic loads on an actuator to be tested includes a force actuator configured to generate at least one dynamic load, the test bench being configured to transmit the dynamic load produced by the force actuator to the actuator to be tested, and a controller for controlling the dynamic load generated by the force actuator depending on a pressure, measured by a pressure sensor, inside one of the chambers of the force actuator.