Abstract: Embodiments of the disclosure include methods and devices in which a flight parameter vector for an aircraft is automatically estimated and then compared to a threshold to determine whether the flight parameter vector is accurate. The detection device estimates a coefficient vector in an observation window, calculates an estimated flight parameter value, and minimizes an error associated with the observation window when calculating the estimated flight parameter value of the flight parameter vector. Comparisons may be performed by a failure detector or a flight control computer to determine failures impacting the flight parameter vector.

Abstract: The invention relates to a seat back for an aircraft comprising a structural column bearing a plurality of devices for supporting an occupant of the seat, these devices being distributed along the structural column and oriented transversely relatively to the structural column so as to each protrude on either side of this column. This solution can reduce the mass and dimensions, while providing satisfactory comfort for the occupant.

Abstract: A method for producing a central wing box having an upper panel, a lower panel, a front spar and a rear spar, the upper edges of said spars approximately parallel to an axis Y being connected by the upper panel, and the lower edges of said spars approximately parallel to the axis Y being connected by the lower panel. The method includes producing at least one panel and at least one spar from composite material in one piece.

Abstract: A priority valve assembly includes a fluid supply line, a first fluid discharge line, and a second fluid discharge line, both of which are to be supplied with fluid via the fluid supply line. A priority valve throttles a fluid flow from the fluid supply line into the second fluid discharge line to prioritize the supply of fluid to the first fluid discharge line over the supply of fluid to the second fluid discharge line if a control parameter which is characteristic for an inlet fluid pressure (pE) in the fluid supply line falls below a first predetermined threshold value (p2). The priority valve reduces the throttling of the fluid flow from the fluid supply line into the second fluid discharge line if the control parameter falls below a second predetermined threshold value (p4) which is smaller than the first predetermined threshold value (p2).

Abstract: A work area is provided for members of a flight crew that includes, but is not limited to a central module, which borders an area adapted for being closed intended for use by crewmembers to change clothes. The central module is arranged in the tail area of the aircraft cabin, and can be used for stowing trolleys. The area is closed by lateral doors, and can be used as a passageway when the doors are open.

Abstract: A method of manufacturing a structure, in particular an aircraft fuselage of composite materials comprising a skin (2) and V-section members fastened to the skin (2) referred to as stiffeners (4). The method comprises a step of positioning punches on a mandrel in order to form channels between the punches. The channels are disposed in at least two networks (6a, 6b, 6c), each channel of the same network (6a, 6b, 6c) meeting at least one channel of another network at a node (8). The method also comprises a step of positioning preforms for stiffeners in the channels such that at least two stiffeners (4) meet at said node (8) and a step of injecting resin so as to assemble the stiffeners (4). A structure made as a single piece is thereby obtained.

Abstract: An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).

Abstract: A fastening device includes a fastening needle system, which is guided in a base body of the fastening device. The fastening needle system is configured to be led through a drilling hole of one or more components. By exercising a pulling force onto the fastening needle system, the components can be fastened between the front portion of the fastening needle and the base body. A fastening system may include the fastening device and a fastening pliers.

Abstract: This relates to an aircraft providing visual signalling of an aircraft. An aircraft for providing visual signalling is provided with at least one multifunctional light unit comprising at least one light source for outboard light emission, which unit is provided on sideway facing areas of the aircraft. The sideway facing areas comprise lateral facing sideway surface areas and/or forward and backwards facing surface areas of the aircraft. The at least one multifunctional light unit is configured to provide i) directional signalling of the aircraft, or ii) status signalling of the aircraft, wherein the status signalling relates to at least one of the group of status of the aircraft, status of the current flight mission, and status of the traffic situation; and/or iii) identification signalling of the aircraft.

Abstract: The present application is concerned with methods of determining optimised fibre paths for complex composite components manufactured from multiple layers of composite material, particularly such components manufactured using an automated fibre placement (AFP) process. One aspect provides a method of determining an optimised fibre path for a geometrical feature of a composite component comprising a plurality of layers of composite material, each layer of composite material comprising a plurality of unidirectional fibres embedded in a matrix. The method includes manufacturing a test piece by: laying up a plurality of composite plies to form a planar charge, each composite ply comprising a plurality of unidirectional fibres embedded within a matrix; and shaping the planar charge by forming it over a mandrel using a hot drape forming process, the shaped charge having a shape corresponding to the geometrical feature of the composite component.

Abstract: An equipping system is provided for equipping an aircraft galley. The equipping system includes a box, which is accommodatable in the aircraft galley to be equipped, as well as a transport cart for equipping the aircraft galley. The system includes a base element, which has a bottom surface and a loading surface opposite of the bottom surface, a plurality of wheels fastened to the bottom surface of the base element, a handle attached to the base element, and a securing mechanism adapted to prevent the box from sliding off the transport cart while it is being transported on the transport cart. The handle is shaped and attached in such a position to the base element that the base element of the transport cart, in the unloaded state of the transport cart, is stackable onto a base element of a further transport cart.

Abstract: The object of the invention is an electrical harness having a plurality of electrically conductive elements held one against another in a braided sheath obtained by braiding strands around the electrical conductor elements, the strands being joined and forming a web around the electrical conductor elements when held against each other, wherein it includes a device to space comprising at least one portion with a peripheral surface at the level of which channels are provided wherein an electrical conductor fits, said portion having a section such that it allows to obtain spaced strands at the level of said device to space when the sheath is being braided around the electrical conductor elements.

Abstract: The invention discloses a method for prevention of porosity in composite material parts (1), which is applied when the curing stage of the part (1) is being carried out on a female tool (2). In the curing stage, an adhesive (4) is placed on at least one of the areas of the radii (5) of the composite material part (1), so that the possible subsequent appearance of porosity in said areas of the composite material part (1) is prevented. Thus, the adhesive (4) acquires the fluidization temperature before the resin of the composite material and it is displaced filling the holes generated during the placement of the part (1) on the female tool (2), in the area of the radii (5) of the part (1), during the coupling between the part (1) and the female tool (2).

Abstract: A switched-mode power supply device including a charger connected on one side to a direct current electrical network, or rectified alternating current electrical network, a power reserve connected to a second side of the charger, and DC-DC output converters delivering regulated output voltages. The output converters are connected by an input to the first side of the charger. The charger is a current bidirectional, voltage unidirectional converter which, in a first phase, enables the power reserve to be recharged and maintained charged from the network, where the output converters are powered by the network and, in a second phase, in the presence of a power brown-out of the network, enables the power reserve to be discharged to power the output converters. A reverse blocking module is connected to the first side of the charger to disconnect the charger and the output converters from the network during the second phase.

Abstract: An adjustment system of an aeroplane, having: at least one adjustable flap on each of the wing of an aeroplane, adjustable with an adjustment device, a drive device for purposes of driving the adjustment devices, and a load sensor for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction.

Abstract: A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.

Abstract: An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.

Abstract: A processing unit for providing aircraft information to passengers of an aircraft, a system comprising the processing unit, an aircraft comprising the system, a method for providing aircraft information to passengers of an aircraft, as well as a computer program for performing the method. The processing unit comprises: a receiving component for receiving cockpit video data representing one or more cockpit video images of at least a section of the cockpit of the aircraft; and a processing component for processing the received cockpit video data such that the processed cockpit video data is retrievable on demand to provide the one or more cockpit video images to the passengers of the aircraft.

Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).

Abstract: The invention pertains to a method for manufacturing a FRC/FRP-component component from rovings by means of a molding tool with a mold surface, featuring the steps of: applying rovings formed of dry fibers onto the mold surface by depositing the rovings under tension with predetermined orientations between deflection devices by means of an application device, applying binder material onto the tensioned rovings; consolidating the arrangement of fiber strands and binder material by applying heat and pressure in order to produce a preform for the component to be manufactured; separating the preform from the deflection devices and removing the preform from the molding tool; and carrying out an injection process or infusion process in order to manufacture the component after separating the preform from the deflection devices; as well as to a molding tool and a device for implementing the method.