Abstract: An energy protection device includes a plurality of sensors that detect a triggering situation requiring an energy protection and a control unit that actuates an energy protection function when the triggering situation is detected and also activates an autothrottle. When the control unit begins the energy protection function, an original engagement state of the autothrottle before the triggering is stored. Thus, when the aircraft returns to an operational flight domain not requiring the energy protection function, the control unit stops the energy protection function and sets an engagement state of the autothrottle based on the stored original engagement state.

Abstract: A method for producing a part made of a composite material, including a skin and at least one stiffener made of strips, which are in turn made of one or more plies of fibers impregnated with a non-polymerized resin. The method includes the steps of: producing a preform of the part by pulling the strips through a die for shaping and positioning the skin and the stiffeners, a polymerization core being provided between a first strip and a second strip prior to the passage thereof through the die; and pressing the resulting preform in a hot press for a duration dt while applying a pressure P and at a temperature T for polymerizing the resin of the strips in the hot press over a pressing length L that is shorter than the length of the panel.

Abstract: The structural integrity of a safe-life aircraft component on an aircraft is measured and assessed by a processing unit. The component includes a load-bearing metal element that is free from cracks. In the method, acoustic emissions generated in the metal element are converted into electronic signals. The acoustic emissions converted include relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks. The electronic signals are set to a processing unit. The processing unit processes over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made. Information providing a measure of the structural integrity of the aircraft component is outputted. Thus, deterioration of the structure of the component can be detected and monitored before a crack occurs.

Abstract: A method for making a rib for an aerofoil structure, the aerofoil structure including a skin component, the method including the steps of scanning the inner surface of the skin component to determine the surface profile thereof, providing a rib having a rib body and a rib foot protruding from the body, machining a foot surface profile into the rib foot, the foot surface profile being arranged to complement the skin inner surface profile where the rib foot is intended to abut the skin component.

Abstract: A sealing unit for sealing a gap between a pair of surfaces includes a nozzle for injecting sealant into the gap, rollers, an endless track round the rollers, and a curing device. The sealing unit is moved along the length of the gap. A sealant is injected into the gap from the nozzle and the track is rotated around the rollers as they are moved along the length of the gap. The track is pressed onto first and second surfaces so the sealant in the gap is constrained by the track to lie substantially flush with the first and second surfaces. The sealing unit is moved along the length of the gap at a rate such that the sealant becomes sufficiently cured when it is in contact with the track so that the track can be peeled away from the sealant as the track rotates round the second roller.

Abstract: An aircraft includes a hose that makes it possible to channel the pressurized air that is used in a sleeve (52) that delimits an annular chamber with the hose, with the sleeve (52) including at least one opening (54) that is delimited by an edge (58) that makes it possible to link the annular chamber and the outside of the sleeve (52), and a leak detection system that includes at least one loop (A) in the form of a threadlike element (56), characterized in that it includes a connecting device that includes a ring (60) that is connected at at least one connecting point (64) with a loop (A), and a flexible wall that delimits a hose (68) for channeling the air that extends from the edge (58) of the opening (54) up to the ring (60).

Abstract: The invention belongs to the field of single-effect hydraulic cylinders. It relates to a device that makes it possible to limit the pressure in the pressurization chamber of a single-effect cylinder when the rod thereof is in a particular range of longitudinal positions of safety, while respecting the operating safety of the device, that is, in the case that the power supply of the pilot valves of the distributors and of the hydraulic pump is cut, the rod of the cylinder remains in its position if this position does not lie within the safety position range.

Abstract: An aircraft slat assembly comprises a first slat and a second slat positioned adjacent thereto. The first and second slats are moveable between extended and retracted positions. The slats are connected by a joint, the joint being arranged to transfer a shear load from one slat to the other slat when the slats are urged into a configurations in which there would be differential extension/retraction of the slats, such as a skewed position.

Abstract: An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·?; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=

Abstract: The invention relates to a locking mechanism for a cargo door (1, 27) in a fuselage cell (3) of an aircraft. The cargo door (1, 27) is attached by a hinge (5) in the area of a recess (2) to open outwards. The locking mechanism comprises inter alia a number of fuselage cell fitments (9, 41) which are disposed in the area of a loading edge (8) of the cargo door (1, 27), and a corresponding number of cargo door fitments (7, 28, 61) which are fixed in the area of a lower edge (6) of the cargo door (1, 27).

Abstract: A method of design optimization, the method comprising producing a first computer model of a first geometry, producing a CFD mesh from the first computer model, using the CFD mesh from the first computer to produce a measure of the fluid dynamic performance of the first geometry, producing a new computer model of a new geometry, producing a CFD mesh from the new computer model, using the CFD mesh to produce a measure of the fluid dynamic performance of the new geometry, and “identifying an optimal geometry using the fluid dynamic performance measurements of the first and new geometries previously produced.

Abstract: A method for modifying a current sound-volume value assigned by an on-board system to an acoustic alert signal emitted on board an aircraft is provided. The method includes furnishing, on board the aircraft, the on-board system with at least one information item defining a modification of the current sound-volume value to a new sound-volume value in accordance with a predetermined rule.

Abstract: A fuel system comprising a fuel tank, a catalytic inerting device for producing oxygen depleted air (ODA) by reaction of fuel vapor from the fuel tank with air, and a separator device for separating carbon dioxide from the ODA gas before feeding the carbon dioxide depleted ODA gas to the fuel tank so as to render the fuel tank ullage atmosphere inert. Also, a method of reducing the carbon dioxide content of oxygen depleted air (ODA) produced by a catalytic inerting device for inerting a fuel tank ullage atmosphere, the method comprising separating carbon dioxide from the ODA gas before feeding the carbon dioxide depleted ODA gas to the fuel tank. The system may be installed in an aircraft.

Abstract: A drive system for rotating a wheel of an aircraft landing gear includes a motor operable to rotate a first drive pinion via a first drive path and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the first drive path. One of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form a ring. Each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively.

Abstract: A drive system for rotating a wheel of an aircraft landing gear includes a motor operable to rotate a first drive pinion via a first drive path and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the first drive path. One of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form a ring. Each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively.

Abstract: A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of projections extending from a bond surface of the first component, each projection having a base, a tapered tip and a tapered overhang beneath the tip, wherein the overhang has an undercut surface which is inclined and faces towards the local bond surface; bringing the components together so as to embed the projections in the second component; and hardening the second component after the array of projections has been embedded into it. Also, a joint so formed.

Abstract: A picocell in an aircraft for the wireless transmission of data between at least a mobile station in the aircraft and a base station in the aircraft in which a communications connection between the at least one mobile station in the aircraft and a subscriber in a terrestrial communications network is established via the base station. In order to enable passengers automatically the use of their mobile radio devices, when no risk of danger to the flying operation is to be expected, or otherwise to refer them to a corresponding ban, a flight control device is provided for detecting flight data and for setting up the picocell in dependence on the flight data.

Abstract: The present invention relates to a production method for a workpiece composed of a fiber-composite material, having the following steps: at least one support means is provided. A main material composed of a pre-impregnated fiber semi-finished product and/or of a secondary material are/is applied to the at least one support means in order to form at least two blank-mold areas, in such a manner that at least one of the at least two blank-mold areas has the main material, and at least one of the blank-mold areas has the secondary material. The blank-mold areas are pressure-bonded to one another to form a workpiece blank such that the at least one support means is provided on a surface of the workpiece blank. The at least one support means and the secondary material are removed from the workpiece blank in order to form the workpiece.

Abstract: The object of the invention is in particular a device for execution of applications (510) in an aircraft information-processing system (500), permitting the simultaneous execution of at least two distinct applications, the said information-processing system comprising shared calculation and storage resources. The device comprises software segregation means capable of creating at least two distinct information-processing environments (505), a partition of the said calculation and storage resources being allocated to each of the said at least two environments in such a way that the execution of one of the said at least two applications in one of the said at least two environments does not have any effect on the execution of the other of the said at least two applications executed in the other of the said at least two environments. Another object of the invention is a method for employing such a device.

Abstract: The device includes processor elements for determining an optimal flight trajectory, which is free of collision with obstacles, which respects constraints of energy, and which links the current position of the aircraft to a target point defined by an operator. The device minimizes additional crew work required to update and validate a new trajectory when an original flight plan needs to be modified to avoid moving obstacles such as storms or other aircraft.