Abstract: A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members.

Abstract: An aircraft system with assisted taxi, take-off and climbing, comprising: a main air vehicle capable of performing autonomously the cruising and landing phases of a flight, an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during the taxing and take-off phases of a flight. Main and auxiliary air vehicles are adapted to be detachably connectable, so that the auxiliary air vehicle can assist the main air vehicle when both are attached to each other during taxing, take-off and climbing. The auxiliary air vehicle is an unmanned air vehicle and it is further configured to fly and land when it is detached from the main air vehicle. Aircraft operations cost and aircraft production cost are reduced, by optimizing the design (sizing) and capabilities of some systems of an aircraft.

Abstract: A nacelle for a jet engine having a selectively operated reverse thruster which redirects air flow to a cascade during a reverse thrust operation, the nacelle including a fancowl panel configured as a stationary partial cover for a jet engine; and a translating cowl panel configured to move transversely during a reverse thrust operation so as to expose a cascade for emitting reverse thrust airflow. In exemplary embodiments, a moveable automatic translating panel, or a rotatable hinge panel, or an extension portion of the fancowl is used to preserve clearance with an aircraft wing in a nacelle clearance area.

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Abstract: A pilot's seat offering an evacuation device. The seat comprises a ladder fixed to the rear of the back and covered by a detachable cover associated with the seat and deployable between a storage position retracted inside the cover and a deployed evacuation position, in which case the cover is detached. Thus, the evacuation device is incorporated harmoniously into the seat which offers a solid base for the evacuation ladder.

Abstract: A method and a system for estimating the state of wear of a cutting tool mounted on a machine tool. The system includes an acquisition module configured to acquire, for a determined duration of machining, values of an operating signal specific to the cutting tool mounted on the machine tool, and a microprocessor configured for calculating current values of a set of wear indicators from the values of the operating signal, and determining the state of wear of the cutting tool as a function of the current values of the set of indicators using a predetermined wear model modeling the state of wear of the cutting tool in function of learning values of the set of wear indicators.

Abstract: A central airfoil box comprising two beams, each beam having a wall pierced with a first bore centered on a first axis, a connecting rod comprising, for each wall, a yoke joint having two flanks arranged on either side of the wall and pierced with a bore. Each yoke joint is fixed to the wall by a fixing system. The fixing system comprises a bearing lodging in the first bore, and being pierced with a second bore centered on a second axis parallel and offset to the first axis, a cylindrical shoulder, secured to and coaxial with the bearing and bearing against the wall, an outer perimeter of the shoulder having a plurality of splines, at least one block fixed to the wall around the first bore and configured to lodge in one of the splines, and a shaft lodging in the second bore and the yoke joint bores.

Abstract: An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

Abstract: A flap system driving a leading-edge flap between retracted and extended positions comprises a leading-edge flap having first and second flap joints, first and second scissor links, a first connecting link, and an actuator. The actuator couples with either the first scissor link or first connecting link. The first scissor link is rotatable supported on a first fixed point by a first support joint. An end of the first scissor link opposite the first support joint couples with the first flap joint. The first connecting link is rotatably supported on a second fixed point by a second support joint. An end of the first connecting link opposite the second support joint rotatably couples with an end of the second scissor link. An opposite end of the second scissor link couples with the second flap joint. The first and second scissor links are rotatably coupled to form a scissor arrangement.

Abstract: An aircraft wing (10) comprising a fixed wing (14) and a movable wing tip device (12). The wing tip device is movable between a flight configuration and a ground configuration, whereby in the ground configuration the span of the wing is reduced compared to the flight configuration. A locking mechanism (30) is provided to lock the wing tip device in the flight configuration, the locking mechanism includes a receiving socket (34) with a first latch and a second latch, and a locking pin (32). In the locked configuration, the locking pin is inserted into the receiving socket such that the first latch and second latch prevents removal of the locking pin from the receiving socket.

Abstract: A fastening system has a fastening element and at least one fastening device having a flanged housing, a closure element, a hollow-sphere element and a spherical insert. The hollow-sphere element pivots about a first pivoting axis relative to the flanged housing, while the spherical insert pivots about a second pivoting axis in the hollow-sphere element. First engagement means in an opening of the spherical insert are of complementary design to second engagement means of the fastening element. The first and second engagement means are designed such that, in a first rotational position, the fastening element can be inserted freely into the opening and, in a second rotational position, the first and second engagement means engage in one another.

Abstract: A battery cell includes an anode, a cathode, and a separator between the anode and the cathode, wherein at least one of the anode or the cathode includes at least a carbon fiber ply comprising carbon fibers, the carbon fiber ply having a thickness of less than 90 micrometers. Also disclosed are a battery and an aircraft including such battery cell, and a method for manufacturing such battery cell.

Abstract: A locking system for locking a cowl to a fixed structure including first and second parts, the first part including a first hook moveable on the cowl and a first shaft fixed to the fixed structure in which the first hook is moveable between locked and unlocked positions, in which the second part includes a handle actuateable between closed and open positions, a second hook and a second shaft fixed to the fixed structure or to another cowl symmetric with the cowl, in which the second hook is moveable between locked and unlocked positions and in which the second hook is mounted where passage of the handle from the closed to open positions causes the second hook to pass from the locked into the unlocked position and vice versa, and in which the locking system also includes a transmission system to move the first hook from the locked into the unlocked position when the handle passes from the closed into the open position, and vice versa.

Abstract: A method for generating an optimum vertical trajectory of a flight trajectory of an aircraft in the descent/approach phase. The trajectory is defined between a current state and a target state of the aircraft on the basis of a speed profile of the aircraft as a function of a curvilinear abscissa of the aircraft along a flight plan. The profile corresponds to a transition between the current and target states and is broken down into successive segments each corresponding to a different aerodynamic configuration that the aircraft may adopt during the descent/approach phase. The method is based on defining a set of flight strategies, each strategy of the set being defined using for each segment of the speed profile flight parameters chosen randomly in ranges of values compatible with the aerodynamic configuration corresponding to that segment. Optimum vertical trajectory is generated on the basis of the strategy of the set.

Abstract: A propulsion assembly for an aircraft comprising a pylon and a bypass turbomachine having a fan duct in which an air flow flows. The turbomachine further comprises an air intake system with a cold bleed air device for bleeding some of the air flow from the fan duct, the device comprising a sliding scoop comprising an upstream face that is open to allow the air to pass and a lower side that has an air outlet opening connected to an exchanger. The scoop is able to slide between an open position in which the scoop extends at least in part into the fan duct and in which part of the air flow in the fan duct rushes into the scoop via the upstream face thereof, and a closed position in which the scoop does not extend into the fan duct and has its upper side closing off the cutout.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates. An engagement command is issued to an actuator at an engagement time, and the actuator operates the actuator in response to the engagement command to move the pinion from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time operating the actuator to move the pinion further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position.

Abstract: A refuelling system is disclosed having a fuel conduit, a variable-position valve for controlling a rate of flow of fuel leaving the conduit, and a controller. The controller is configured to receive from a sensor arrangement a measurement of an electrostatic condition in a fuel tank being fuelled by the system. The controller is configured to control the variable-position valve to control the rate of flow of fuel based at least in part on the measurement received from the sensor arrangement.

Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.

Abstract: An aircraft landing gear 2 is disclosed having a first arm 6a configured to have one or more wheels 8a mounted at one end, the first arm 6a being configured for mounting to a pivot 10a. The landing gear 2 includes a second arm 6b configured to have one or more wheels 8b mounted at one end, the second arm 6b being configured for mounting to a pivot 10b. The landing gear 2 further includes a first link 18a pivotally coupled to the first arm 6a, a second link 18b pivotally coupled to the second arm 6b; and a main link 20 pivotally coupled to each of the first and second links 18a, 18b and to a shock absorber 22 arranged to provide a biasing force via (i) the main linkage 20 and the first link 18a which opposes rotation of the first arm 6a about the pivot 10a and (ii) the main linkage 20 and the second link 18b which opposes rotation of the second arm 6b about the pivot 10b.

Abstract: A system for producing a component from a fibre composite material includes a moulding tool, a control unit and a plurality of mutually independent material application units, each of which includes a material store for providing fibres, a material delivery apparatus for delivering fibres from the material store and a drive device, and is configured, with the aid of the drive device, to follow a predetermined path on the moulding tool, while delivering fibres as required. The control unit controls the material application units by specifying a plurality of individual paths, so that they move autonomously along the paths. The control may, in particular, be carried out by optical projection onto the moulding tool.