Abstract: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

Abstract: A self-sealing fixing element is disclosed having a body with a bearing surface, and a bore with an opening in the bearing surface. A curable sealant layer is carried by the bearing surface and encircles the opening in the bearing surface. The curable sealant layer is formed from a sealant material which cures when exposed to atmosphere. A barrier layer overlays the curable sealant layer and can break apart when the fixing element is installed in order to expose the sealant layer to atmosphere. The curable sealant layer has a thickness which decreases away from the bore, and the barrier layer has a thickness which increases away from the bore.

Abstract: An aerofoil shaped body includes a plurality of longitudinal spars, an upper aerofoil cover, and a lower aerofoil cover. The spars and the covers are made of composite laminate material. One of the spars is integrally formed with one of the covers to form a spar-cover such that the composite laminate material of the spar extends continuously into the cover through a fold region created between the spar and the cover. The fold region has a fold axis extending substantially in the longitudinal direction, and the fold axis projected onto two orthogonal planes has curvature in both those planes.

Abstract: A method of manufacturing an object is disclosed. Material is extruded from an extrusion head onto a tool, the extrusion head having an extrusion axis along which the material flows as it exits the extrusion head. Relative movement is generated between the extrusion head and the tool as the material is extruded so that the material is deposited as a series of layers, wherein the material cures on or after deposition so that the layers are fused together. The extrusion and the relative movement are controlled so that the series of layers are shaped in accordance with a stored three-dimensional model of the object. At least some of the layers are non-planar layers.

Abstract: A magnetically levitated arrangement for contactless movement over a surface comprising a magnetizable reaction surface and a magnetically levitated unit arranged to interact with the reaction surface. The levitated unit has at least one pair of rotatable rotary magnet units, each unit rotatable about a rotation axis and having magnetic elements arranged with alternating poles and respectively substantially parallel to the rotation axis in a pole connection direction. Each rotary unit pair is formed to interact, due to rotation of the two rotary units in opposite directions relative to one another and relative to the reaction surface, in such a way with the reaction surface, that forces are generated holding the levitated unit at a distance from the reaction surface, and due to the opposite rotation directions of the rotary units of each pair, a directed drive force moving the levitated unit relative to the reaction surface is generated.

Abstract: A punching tool which comprises a body, a rod oriented in a first direction and comprising a free end configured to cooperate with the element to be punched, a guide sleeve containing a conduit extending from a first end face to a second end face and configured to rest against the part. The conduit comprises a first portion which opens at the first end face and is configured to house the body of the punching tool and to allow a translation movement of the body of the punching tool relative to the guide sleeve.

Abstract: Inter alia, an apparatus including a ramp, the ramp configured to enable variation of a cross section of a ram air passage of the apparatus. The ramp includes a first rigid member, a second rigid member and a flexible member coupled to the first rigid member and the second rigid member. The ramp is movably mounted at two ends. Moreover, a method of varying the cross section of the ram air passage of such an apparatus by moving the ramp of the apparatus is disclosed. Further, an arrangement including such an apparatus and a ram air channel communicating with the ram air passage is disclosed.

Abstract: A front fairing of a pylon of an aircraft includes a shroud, produced in a single piece, which extends over almost all the surface area of the front fairing and which is configured to occupy a closed position in which a peripheral edge of the shroud and a peripheral edge of the front fairing and/or of the nacelle are contiguous, and an open position in which the peripheral edge of the shroud is, at least partially, separated from the peripheral edge of the front fairing and/or of the nacelle. The front fairing includes at least one locking system to hold the shroud in closed position.

Abstract: An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.

Abstract: An aircraft including a wing 10 having a fixed wing 12 and a swing wing tip device 14 pivotably mounted about a pivot 16 at the tip of the fixed wing, wherein the swing wing tip device 14 is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations, where the span of the aircraft wing is reduced. The swing wing tip device 14 includes a receiving portion 48 arranged such that in the ground configuration, portions of the upper wing skin and lower wing skin of the fixed wing which are exposed in the flight configuration are at least partially received within the receiving portion 48 of the swing wing 14.

Abstract: The invention is a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has an input shaft having an axis of rotation spaced from an axis of rotation of an output shaft. The output shaft is operable to pivot about the axis of rotation of the input shaft. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract: An aircraft fuel system has a bottom wall, and a rib with a bottom edge joined to the bottom wall. The rib provides a boundary between first and second compartments. At least the first compartment is arranged to carry fuel. An open recess is in the bottom edge of the rib and a rib sealing arrangement between the bottom edge of the rib and the bottom wall prevents fuel from flowing across the bottom edge of the rib except at the open recess. The system has a pump and a conduit coupled at one end to the open recess and at another end to the pump. The open recess and the conduit provide a fuel flow path across the bottom edge of the rib from the first compartment into the pump. The flow path is sealed to prevent fuel flowing out of the flow path into the second compartment.

Abstract: A network access control method involves requesting access to a network via a wireless communication adapter for a personal electronic device. Then, an acoustic audio code output by an audio signaling device connected to the wireless communication adapter by wire is acoustically captured by the personal electronic device. A digital representation of the captured acoustic audio code is submitted from the personal electronic device to the wireless communication adapter via wireless communication. Subsequently, the wireless communication adapter authenticates the personal electronic device on the basis of the submitted digital representation of the captured acoustic audio code.

Abstract: An autarkic monument in an aircraft pressure cabin supplied with the required operating mediums in a decentralized fashion by carrying along these operating mediums in the monument in operating medium reservoirs is provided. Methods for the efficient energy conversion within this autarkic monument are also provided. The efficiency is achieved such that the energy conversion is, based on the operating mediums, optimized with respect to exergo-economic and/or exergo-ecologic aspects, and such that energy conversion processes are adapted to one another if several energy conversion processes take place.

Abstract: A component monitoring apparatus [100] including an input [110] to receive sensor data from a sensor arrangement [S1-S4]. The sensor data representative of a use of a respective component [105] during a monitoring interval. A memory [118] provided to store received sensor data and a life parameter associated with the component [105], an interface [126] provided to communicate with a remote device and a power cell [128] provided to power the apparatus [100]. The apparatus [100] arranged to: store in the memory [118] received sensor data, in response to a trigger, read the sensor data from the data memory [118] and transfer the sensor data to the remote device, and, in response to receipt of a data packet containing a life parameter associated with the usage of the component [100], store the life parameter to the memory [122].

Abstract: An adhesive retainer for fixing to a structure has at least one adhesive foot which has a supporting base region formed on the adhesive foot and is provided with receiving openings which extend like capillaries through the supporting base region into the interior of the adhesive foot. The receiving openings are configured to form an integral bond with the structure such that when the adhesive foot is placed on the structure covered for this purpose with a liquid, solidifiable bonding substance, the receiving openings receive bonding substance due to capillary ascension.

Abstract: A detection system comprises an analysis unit for analyzing successive images generated by a monitoring sensor to determine in an image a position of an axis representative of the displacement of the aircraft between two successive images, the so-called real position, a computation unit for computing, on the basis of data relating to a displacement of an aircraft between the generations of these two images and of the positioning of the monitoring sensor on the aircraft, a position in an image of an axis representative of the displacement of the aircraft, the theoretical position, an estimation unit for estimating the angular disparity between the real position and the theoretical position, and a comparison unit for comparing this angular disparity with at least one predefined tolerance value so as to detect a misalignment when this angular disparity is greater than this tolerance value.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented automatically by a processing unit: a) acquiring information relating to the runway; b) acquiring information relating to a current situation of the aircraft; i) determining a landing position of the aircraft on a central longitudinal axis of the runway, as a function of a trajectory determined between a current position of the aircraft and this landing position to comply with at least one constraint relating to a roll angle of the aircraft; j) determining a parameter relating to the landing position; k) determining a deviation between this parameter and a reference value; l) comparing this deviation with a predetermined threshold; and m) as a function of the result of the comparison carried out in step l), commanding, if appropriate, the signaling of an alert via the signaling system of the aircraft.

Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.

Abstract: A connection comprising a first duct, a second duct, a flexible tube which comprises a first end configured to cover part of the first duct, and a second end configured to cover part of the second duct, a first clamping system configured to clamp the first end of the flexible tube around the first duct, and a second clamping system configured to clamp the second end of the flexible tube around the second duct.