Abstract: The invention relates to an oxygen mask for supplying oxygen to a person, which can be modified for use on differently sized faces. The oxygen mask has a holding frame, which has a first cross-brace and a second cross-brace, a substantially gas-impermeable material arranged on the holding frame and which can be stretched between the first cross-brace and the second cross-brace, a headband connected to the holding frame, an exhalation valve arranged on the material and penetrating the material, and an oxygen supply line for providing oxygen to an inside of the oxygen mask, wherein the first cross-brace and the second cross-brace are arranged in two lateral holders, which are opposite each other, wherein at least the first cross-brace is flexible and wherein the distance of the lateral holders to each other is adjustable at least between a first and a second distance.

Abstract: A wing leading edge assembly is disclosed including a leading edge panel and a cover panel located over the structural component. The cover panel has a thermoplastic layer with an inner surface. A thermoplastic fastening member extends through the structural component and is welded to the inner surface so that the structural component is fastened between the inner surface and the fastening member.

Abstract: An aerodynamic aircraft component includes a fixed aerodynamic part, which has a first contact surface, and a movable aerodynamic part, which has a second contact surface and is mounted to the fixed aerodynamic part for movement relative to the fixed aerodynamic part between a first position, in which the first and second contact surfaces are spaced apart, and a second position, in which the second contact surface contacts the first contact surface. The fixed aerodynamic part includes one of a magnet device and a piece of magnetic material and the movable aerodynamic part includes the other of the magnet device and the piece of magnetic material. The magnet device and the piece of magnetic material are arranged such that a magnetic force between the magnet device and the piece of magnetic material urges the second contact surface in contact with the first contact surface.

Abstract: A turbofan having a nacelle including a slider translationally mobile to open a window between a duct and the exterior, a plurality of blades, each rotationally mobile on the slider, and a maneuvering system moving each blade and comprising for each blade, a shaft rotationally mobile on the slider and onto which the blade is fixed, an arm having a first end fixed to the shaft, an arc coaxial with the longitudinal axis, mounted rotationally mobile on the slider about the longitudinal axis, a rectilinear rod fixed by its base to the arc, the rectilinear rod inserted into a through-bore of a stock, wherein the stock is mounted translationally free relative to the rectilinear rod, and the stock is mounted rotationally free on the arm at its second end about a rocking axis parallel to the rotational axis, and an actuation system producing arc rotation in two opposite directions.

Abstract: A method of manufacturing stiffened structural panel for an aircraft including a main sheet made of composite material with unidirectional fibers, and a stiffening structure secured to the main sheet and made of a composite material comprising a resin and chopped fibers, the stiffening structure including on the one hand a base adhering to one of the two lateral faces of the main sheet, and a network of stiffeners in the form of a grid projecting from the base. The method includes a step of compression molding the stiffening structure from a block formed of a prepolymer reinforced with chopped fibers.

Abstract: A cable routing system is disclosed including a routing fixture and an exit fitting. The routing fixture defines a channel for a cable. The channel is engaged by the exit fitting and a cable in the channels exits through an exit channel defined by the exit fitting. The exit channel is directed away from the channel in the routing fixture. The resulting assembly allows low profile cable runs that can conform to a structural surface and in which cables can be broken out easily, without a requirement to cut the cable. A clamp may be provided to further secure the exit fitting to the routing fixture. A method of installation involves installing a cable into a routing channel before installing the exit fitting. The cable routing system can be used in an aircraft, including space constrained areas such as within an aircraft wing.

Abstract: A locking apparatus for locking the rotational position of a fastener component which is rotatable about an axis relative to a structure. The locking apparatus includes a collar and a rigid arm. The collar is configured to engage with the fastener component such that relative rotation of the collar and the fastener component is substantially prevented. The arm has a first end configured to engage with the collar such that rotation of the collar relative to the first end is substantially prevented, and a second end configured to engage with the structure such that rotation of the arm relative to the structure is substantially prevented. The collar has an inner surface having a first finite order of rotational symmetry about the axis, and an outer surface having a second, larger, finite order of rotational symmetry about the axis.

Abstract: A regulation system to regulate the flow rate of a hot air duct which comprises a shutter, an upstream air intake, a downstream air intake, a regulator and an actuator of the shutter with a first inlet connected to an outlet of the regulator and a cooling system comprising an outer radiator, a housing and a heat pipe housed in the housing and discharging the heat between the housing and the outer radiator, wherein the air streams coming from the upstream air intake and from the downstream air intake pass through the housing. Such a regulation system allows a better discharging of the heat by the action of the heat pipes.

Abstract: A fire-fighting system for an aircraft, the fire-fighting system having a reservoir having an exterior envelope which delimits an interior volume of the reservoir and an interior wall which extends inside the exterior envelope and separates the interior volume into a first chamber and a second chamber which are separate from one another and are each filled with an extinguishing fluid. A network of pipes, and a valve system are provided which are arranged so as to allow, in succession, the extinguishing fluid to flow from the first chamber to the network of pipes, and then the extinguishing fluid to flow from the second chamber to the network of pipes. Such a fire-fighting system allows simpler installation in the aircraft, the fitting of a single network of pipes and hence a saving in terms of weight and volume.

Abstract: A system for automatically adapting operating parameters of a galley device on the basis of provided supply items for on-board catering for a vehicle, in particular an aircraft, includes a galley device that has an identification device that is designed to identify a supply item; and a control device for controlling the galley device, wherein the control device is designed to provide operating parameters for the identified supply item and to operate the galley device in accordance with the operating parameters.

Abstract: An acoustic reflector for a microphone to measure flyover noise generated by an aircraft. The microphone is configured to measure flyover noise generated by an aircraft flying on a preset path. The acoustic reflector includes at least a central portion having the shape of an ellipse having a major axis and a plurality of peripheral portions distributed around the central portion. The acoustic reflector allows edge effects to be attenuated at the low frequencies of the noise to be measured.

Abstract: An air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.

Abstract: Connections of sub-elements formed at least partly from fiber composite materials of a component for an aircraft with relatively low manufacturing complexity and the same or improved reliability and improved sealing, by providing different seam connections between the sub-elements. For this purpose, at least an edge region, formed from fiber composite material, of the first sub-element is formed to give a foldover that engages with an edge region of the other sub-element. Preferably, the forming is effected especially with use of thermoplastic materials while heating preferably the entire edge region.

Abstract: A smoke and fire source detection system including a flexible printed circuit board with a film substrate and an electrical conductor layer formed on the film substrate, which includes a two-dimensional conductor path pattern. The flexible printed circuit board includes a first end portion with an electronic control device and a data and energy supply interface coupled to the electronic control device, a second end portion with an ground connection, a data and energy supply conductor path formed in the electrical conductor layer between the data and energy supply interface of the first end portion and a ground connection of the second end portion, and one or more sensor module portions which are arranged at different longitudinal extension positions along the flexible printed circuit board between the first end portion and the second end portion and which each include a temperature sensor and/or smoke detector.

Abstract: A method and a system for estimating the state of wear of a cutting tool mounted on a machine tool. The system includes an acquisition module configured to acquire, for a determined duration of machining, values of an operating signal specific to the cutting tool mounted on the machine tool, and a microprocessor configured for calculating current values of a set of wear indicators from the values of the operating signal, and determining the state of wear of the cutting tool as a function of the current values of the set of indicators using a predetermined wear model modeling the state of wear of the cutting tool in function of learning values of the set of wear indicators.

Abstract: A system comprising a trolley which comprises a platform and wheels attached beneath the platform, an air intake of an aircraft engine, where the air intake rests on the platform so as to have its narrowest part at the top and its widest part at the bottom, and an inflatable protection item in the form of a closed envelope which is placed around the widest part of the air intake. A system of this kind makes it possible to protect the air intake from collisions that it might experience during movement of the trolley, and to increase safety by avoiding collisions between operators and the air intake.

Abstract: A retractable vortex generator system for an aircraft. The system comprises a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing the boundary layer of an air current, and driving means configured for rotating the plate between a first and a second position. In the first position at least part of the contour of the plate protrudes through the slot, and in the second position the plate is retracted within the slot.

Abstract: A method for manufacturing an aircraft rear section including a tail cone and a vertical tail plane, the method includes: providing pre-cured frames (1) each of which includes a section of the tail cone (2) and a section of the vertical tail plane (3); providing pre-cured stringers (4); placing the pre-cured stringers (4) each in respective positions within the pre-cured frames (1); placing a skin (5) around an external surface of the pre-cured frames (1); and curing the pre-cured frames (1), the pre-cured stringers (4), and the skin (5), forming the final aircraft rear section.

Abstract: An aircraft door arrangement, comprising a door pivotable between closed and open positions, a frame section in a door opening region, and an articulation arrangement connecting the door and frame section. First and second arms are mounted on the frame section, rotatable about first and second axes, respectively. Third and fourth arms are mounted on the door, rotatable about third and fourth axes, respectively. The second arm, at a first position, is rotatably coupled to the fourth arm about a fifth axis, and at a second position, closer to the second axis, is rotatably coupled to the third arm about a sixth axis. The third arm, at a third position, is rotatably coupled to the first arm about a seventh axis, and at a fourth position, closer to the third axis, is rotatably coupled to the second arm about the sixth axis. All axes are oriented substantially parallel.

Abstract: A window element for an aircraft comprises a window frame which has a frame reveal forming an opening, and a receptacle adjoining the frame reveal, an inner window pane which is configured to be inserted into the receptacle, a holding frame which is configured to be inserted into the receptacle and to fix the inner window pane in the receptacle, and a cover which has an opening and is configured to be attached to the window frame and to conceal the window frame around the frame reveal. An encircling inner edge of the cover that forms the opening of the cover lies radially substantially outside an encircling inner edge of the receptacle.