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: 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: 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: 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: 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: 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 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.

Abstract: A carrying system for receiving containers in a vehicle includes at least one container, at least one electrical consumer arranged in the container, at least one primary winding in a first core and at least one secondary winding in a second core. The secondary winding is arranged in the container, and the primary winding can be attached on the vehicle side in such a manner that movement of the container to a receiving position results in alignment of the primary winding and the secondary winding. The primary winding and the secondary winding are adapted for inducing in the secondary winding an alternating voltage that is applied to the electrical consumer.

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: 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: 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: 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 method for the attachment of an arrangement for the attachment of a system to a structure at least partially, wherein a first element of the arrangement is bonded to the structure, wherein the first element is created by injecting at least one material into a mould carried by a robotic system to a target position of the arrangement on the structure which is closed at one side by pressing it against the structure, and after the first element is cured, a second element of the arrangement is coupled directly or indirectly to the first element, and a robotic system for executing such a method.

Abstract: An attachment structure for an equipment unit of an aircraft includes a first attachment device extending in a longitudinal direction of the aircraft, wherein the first attachment device is attached to a stringer and to a frame and wherein the first attachment device has a first engagement element and a second attachment device attachable to the equipment unit, wherein the second attachment device has a second engagement element adapted for engaging into the first engagement element, such that a force from the equipment unit in the longitudinal direction on the second attachment device is transferred via the second engagement element to the first engagement element and via the first attachment device to the stringer and the frame.

Abstract: A method for coupling a first and a second stiffening element for a skin of an aircraft or spacecraft, wherein the first stiffening element has a cross-sectional profile with first and second web portions extending from a flange portion of a predefined width toward the skin includes forming a coupling zone of the first stiffening element wherein the second web portion is at least partially removed to expose an inner surface of the first web portion, and a step of fastening a coupling element, for coupling the stiffening elements, to the coupling zone of the first stiffening element.

Abstract: A deployment mechanism is disclosed for deploying a deployable member supported on tracks relative to a base member and comprising a brake system operable in response to relative skewing of the tracks.

Abstract: A fastening device includes a first annular flange connected to an air intake, a second annular flange connected to a powerplant pressed against the second annular flange and fastening elements that allow the annular flanges to be linked. For at least a first fastening element, a blade is fitted between the first fastening element and the first annular flange, the blade including at least a central part linked to the first fastening element, radially mobile relative to the first annular flange, and at least one offset part for which at least radial centripetal displacement is limited relative to the first annular flange, the central part and the offset part being offset relative to one another along the direction of the circumference.

Abstract: The invention relates to a method for controlling the deceleration on the ground of a vehicle. The method obtains, from the crew of the vehicle or from an outside operator, parameters relating to its current position and its current speed. Then it determines a reference position and speed of the vehicle, the reference position being a theoretical position to be reached by the vehicle. Finally it determines, from indicated parameters and from reference parameters, a deceleration command with a view to ending up at a target position at a preselected speed.

Abstract: A device (10) for simulating an alternator is connected to an alternator control circuit (20) and supplies a voltage on an electrical network (30). This device comprises: a circuit for receiving an excitation current (Iexc) generated by the control circuit (20); a switch (15) able to apply voltage to the network (30) and controlled on the basis of the excitation current (Iexc). A method of controlling such a device and a simulation system comprising such a device also are described.