Abstract: A mirror arrangement (10) for monitoring a passenger cabin of an aircraft is disclosed, comprising at least one mirror element (40) for reflecting light and a mirror mount (20) for fastening the at least one mirror element (40) inside the passenger cabin, the mirror mount (20) comprising a holder (22), to which the at least one mirror element (40) is fastenable and which is displaceable relative to the passenger cabin.

Abstract: A tool for tuning the pitch of blades on a model propeller with pivoting blades, the tool comprising a mount for the model propeller and a calculation module. The mount allows the propeller to be positioned such that the axis of the propeller coincides with a fixed reference axis of the mount and to place each blade of the propeller, successively, in a measurement position. The calculation module determines the angle between a chord of a blade in the measurement position and a fixed reference plane of the tool, the fixed reference plane being orthogonal to the fixed reference axis, based on optical sightings by the calculation model on a suction face of the blade in the measurement position.

Abstract: The invention relates to a rest compartment arrangement in an aircraft, comprising a rest compartment and at least one monument, wherein the rest compartment is arranged above a cabin floor and comprises a passage that extends from a rest compartment floor in the direction of the cabin floor. When compared to the state of the art, the invention is characterized in that the at least one monument comprises at least one wall which above a seat region situated therein forms a recess to accommodate the passage. As a result of this, monuments can be positioned in a space-saving manner underneath the passage in the cabin without this resulting in reduced comfort, because the recess above the seat region is not perceived to be distracting by the passenger.

Abstract: A device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance.

Abstract: An autonomous water module is provided for aircraft, preferably a water module embodied as a water trolley, and to a monument for aircraft, which includes, but is not limited to a device for receiving said type of water module, and finally, an aircraft equipped with said type of autonomous water module and/or said type of monument. The autonomous water module includes, but is not limited to a container having the standard dimensions of a trolley, and the container includes, but is not limited to a fresh-water tank, a device for dispensing fresh water, and a device for discharging gray water.

Abstract: An acoustic treatment panel includes, from the inside to the outside, a reflective layer (50), at least one alveolar structure (52), and at least one acoustically resistive structure (54) that forms an aerodynamic surface, whereby the panel is connected at one edge to at least one second panel (46), characterized in that it includes, at the edge overlapping with the at least one second panel, a reinforcement (60) that is inserted between the reflective layer (50) and the acoustically resistive structure (54) forming the aerodynamic surface, whereby the reinforcement (60) ensures the uptake of forces between the layer (50) and the structure (54).

Abstract: A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.

Abstract: A trailing-edge flap system is described. The trailing-edge flap system includes a trailing-edge flap and a movement device. The movement device includes at least a translatory mover for the translation of the trailing-edge flap and at least a rotational mover for the rotation of the trailing-edge flap.

Abstract: An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating de-icing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.

Abstract: The invention relates to a device for welding a stiffener to a skin. The stiffener has a stiffener foot with a bearing surface parallel to the skin surface and a stiffener flange projecting away from the plane of the bearing surface. The device includes a metallic support includes a seating surface matching the shape of the receiving side; a groove which accommodates a flange of the stiffener inserted in the groove; an insulative supporting structure for positioning a bearing surface against the receiving side; and a conformal panel for applying pressure forcing said bearing surface against said receiving side. A heater temporarily raises the temperature of bearing surface of the stiffener and the adjacent receiving side of the skin to above the melting point of the matrix when pressure is applied thereby welding the stiffener to the skin.

Abstract: A method of monitoring the performance of an aerodynamic surface of an aircraft. The aircraft is operated during a non-perturbed measurement period such that the flow of air over the surface is at least partially laminar. A parameter is measured which is indicative of the drag of the surface during the non-perturbed measurement period to provide non-perturbed drag data. Air flow is perturbed temporarily over the surface in a perturbed measurement period so that it undergoes a transition from laminar flow to turbulent flow. The parameter is also measured during the perturbed measurement period to provide perturbed drag data. The degree of laminar flow during the non-perturbed measurement period can then be estimated in accordance with the difference between the perturbed drag data and the non-perturbed drag data. An ice protection system can be used to perturb the air flow.

Abstract: The invention relates to an aircraft wing panel, for example, a trailing edge upper panel'1 which is joined to the wing skin (20) by means of spigots (19) which project and engage with slots (13). Preferably, the slots are provided in lips (10, 11, 12) which extend from the leading edge (5) of the panel and the spigots (19) are fastened to and extend from the wing skin (20).

Abstract: An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use.

Abstract: A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.

Abstract: A routing support (64) for a conduit line fastened in openings and the line includes a plurality of conduits connected end-to-end along a longitudinal axis. The routing support (64) incorporates an outer body (66) with a structure (68) for fastening the body in an opening. The routing support also includes a housing structure to accommodate the ends of two conduits in an end-to-end arrangement and the structure may include two separate structures (one for each conduit end (72)) or a single common structure (accommodating respective ends of the two conduits). The routing support also includes a flexible interface (74) connecting the housing structure (70) to the outer body (66). In addition, the flexible interface (74) and the outer body (66) and the housing structure (70) are integral. Embodiments include a line for transporting fuel with this routing support, and an aircraft wing in which such a line/support transports fuel.

Abstract: A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.

Abstract: A wing assembly for an aircraft comprising a spar, a wing cover and a rib; wherein the spar has a web portion and a flange portion joined by a radius corner; wherein a gap is formed at an interface between the spar, the wing cover and the rib; wherein the assembly further comprises a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap. Also a method for sealing a gap in an aircraft wing assembly.

Abstract: A device for forming a microstructured coating on a substrate. The device includes a microstructured band that can be moved by rolling without slipping on the substrate and going around main pressure application elements assembled on a chassis, and secondary pressure application elements assembled on the chassis so as to be in contact with an inner face of the band in a zone of a strand of the band delimited by said main pressure application elements, this zone being exposed to the action of a curing apparatus that accelerates curing of a curable material designed to form said coating. A method for forming a microstructured coating using the above-mentioned device.

Abstract: An aircraft (11) with at least an inflatable device (41) installed in a cavity (21) in its external surface which is equipped with a door (25) for opening/closing said cavity (21) is provided. The inflatable device (41), comprising a cushion (45) and a gas generator is configured for filling the cavity (21) with the cushion (45) when it is inflated with the gas supplied by said gas generator, without protruding from the cavity (21) for reducing the downstream air flow disturbances generated by said cavity (21) when the door (25) is open. The inflatable device (41) includes control means for inflating the cushion (45) in predetermined circumstances, being the door (25) open. The invention is particularly applicable to the cavities of the Main Landing Gear (31) for avoiding power losses to a Ram Air Turbine (51) placed behind it.

Abstract: In a method for operating an aircraft cooling system a cooling medium is guided through a cooling circuit, which is connected to a refrigerating machine and to at least one cooling station associated with a cooling energy consumer, to supply cooling medium cooled by the refrigerating to the cooling station. A temperature of the cooling medium upstream of the cooling station and a temperature of the cooling medium downstream of the cooling station are detected. The mass flow of cooling medium supplied to the cooling station is controlled in dependence on a thermal output of the cooling energy consumer and in dependence on a difference between the temperature of the cooling medium upstream of the cooling station and the temperature of the cooling medium downstream of the cooling station.