Abstract: A turbojet engine including an engine, a fan casing and a nacelle including a fixed structure and a thrust-reversing system having a mobile assembly with a mobile cowl and a frame, in which the mobile assembly is translationally mobile on the fixed structure between an advanced position and a retracted position to define a window between the secondary jet and the outside of the nacelle, inner doors and outer doors, a runner translationally mobile between a first position and a second position, in which each door is mounted articulated by a rear edge on the runner between a stowed position and a deployed position, an actuator for ensuring the translational displacement of the runner from the first position to the second position and an actuator for ensuring the displacement of the frame from the advanced position to the retracted position.

Abstract: An aircraft includes first and second zones, and a sealing system, interposed between a doorframe and a door providing access to the second zone, including: a peripheral seal secured to the door, a stop secured to the doorframe, and including a body in the form of at least one plate which extends around the perimeter of the doorframe, parallel to the door when the door is in the closed position, a peripheral groove positioned on the stop in such a way that the peripheral seal closes off the peripheral groove around the perimeter of the opening when the door is in the closed position, and at least one passage configured to cause the peripheral groove and the first zone to communicate.

Abstract: An actuating system comprising a hydraulic actuator provided with a cylindrical cavity containing a piston configured to slide within the cylindrical cavity and a rod. The piston separates the cylindrical cavity into a first actuating chamber and a second actuating chamber. A first servo valve comprises a sheath including a first slider configured to slide within a cavity of the sheath on the basis of command signals from a command system. The cavity of the sheath comprises a first command chamber and a second command chamber on either side of the first slider. The first actuating chamber is fluidically connected to the first command chamber, and the second actuating chamber is fluidically connected to the second command chamber.

Abstract: A Samer rod has length adjustable along a longitudinal axis. A first element extends along the axis between a first coupling end and an engagement section end, and a second element extends along the axis between a second coupling end and a receiving end. A receiving hole extends along the axis, inside the first element, away from the receiving end to the second coupling end. The engagement section has an outer row of teeth extending parallel to the axis with evenly spaced teeth extending perpendicular to the axis in the circumferential direction of the engagement section. The receiving hole has an inner row of teeth extending parallel to the axis with evenly spaced teeth extending perpendicular to the axis in the circumferential direction of the receiving hole wall. The spacing of the teeth of the two rows in the direction of the axis corresponds to one another.

Abstract: A network for an aircraft including a master device and slave devices connected in daisy-chain arrangement series. Each slave device has a unique identifier. The master transmits polling data packets along the slave devices, each including only one identifier. Polling data packets are transmitted in successive sequences, each including for each slave device only one polling data packet and including the polling data packets in a predetermined order. Each slave device includes a first data interface for connection in an upstream direction, a second data interface for connection in the downstream direction, and a processing unit to compare for each received polling data packet the identifier thereof with the identifier of the respective slave device, and output a response data packet to the master device if the two identifiers match, and forward the polling data packet to the second interface at least if the two identifiers do not match.

Abstract: A device for assisting the piloting of a rotorcraft in order to pilot a rotorcraft during an approach stage preceding a stage of landing on a rotorcraft landing area. Such a device includes in particular a camera for taking a plurality of images of the environment of the rotorcraft along a line of sight, looking at least along a forward direction Dx of the rotorcraft, and processor for identifying in at least one image from among said plurality of images at least one looked-for landing area.

Abstract: An electrically powered propulsion system for a spacecraft includes a first center of gravity at a first time of operation and a second center of gravity at a second time of operation, where the second center of gravity is different from the first center of gravity. The electrically powered propulsion system includes a thruster realignment mechanism and at least two thrusters coupled to the thruster realignment mechanism. Each of the at least two thrusters has an individual thrust vector. The thruster realignment mechanism is adapted such that, in a first position, the individual thrust vectors of the at least two thrusters pass through the first center of gravity and that, in a second position, the individual thrust vectors of the at least two thrusters pass through the second center of gravity. The thruster realignment mechanism holds the first position in the event all of the at least two thrusters are without any failure.

Abstract: A fixed wing aircraft has a wing with an aerofoil cross-section defining an upper and lower geometric surfaces which meet at a geometric leading edge of the wing. The wing has an upper and lower aerodynamic surfaces while in flight. The upper aerodynamic surface and the lower aerodynamic surface meet at an aerodynamic leading edge at the intersection with an attachment line dividing the air that passes over the upper aerodynamic surface from the air that passes over the lower aerodynamic surface. The lower geometric surface adjacent the geometric leading edge has a roughness strip with a step height of at least 50 microns over the lower geometric surface. The roughness strip is located on the lower aerodynamic surface of the wing when the aircraft is flown at a load factor of 1 g and is located on the upper aerodynamic surface when the load factor is above 1.2 g.

Abstract: A system and method for providing in-flight weather information to compute an optimized vertical flight profile are disclosed. In one embodiment, on-board weather information is obtained from one or more aircraft at regular intervals during flight. Further, weather information is identified for a predicted flight trajectory of an aircraft from the obtained on-board weather information. For example, the aircraft is preceding the at least one aircraft. Furthermore, a subset of the identified weather information is dynamically provided to a flight management system (FMS) in the aircraft, during flight, to compute the optimized vertical flight profile.

Abstract: A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

Abstract: A cap for forming a sealed cavity around an end of a fastener is disclosed having a cap body with an annular base terminating at an inner cap rim which surrounds an opening into a central cavity and lies in an inner cap plane around a majority of a circumference of the annular base. A skirt provides an annular pocket between the skirt and the annular base. The skirt has a first part which is integrally formed with the cap body from a first material and terminates at an edge, and a second part which is formed from a second material and extends from the edge of the first part of the skirt to a skirt rim which lies in or below the inner cap plane around a majority of a circumference of the skirt.

Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.

Abstract: A drive system for an aircraft landing gear is disclosed having a wheel rotatable about a wheel axis, a driven gear arranged to be attached to the wheel and capable of rotating the wheel about the wheel axis, a drive train comprising an input gear rotatable by an input shaft, an intermediate gear meshed with the input gear and rotatable by an intermediate shaft, and a support member arranged to support the input shaft and intermediate shaft. The support member is arranged to pivot about the input shaft between a neutral configuration in which the drive train is disengaged from the driven gear and a driven configuration in which the drive train is engaged with the driven gear to enable the drive train to rotate the driven gear. The drive system includes brake capable of being engaged with the input shaft to prevent rotation of the input shaft relative to the support member and of being disengaged from the input shaft to permit rotation of the input shaft relative to the support member.

Abstract: An aircraft fuel vent pipe with a pipe body containing a duct which extends along a duct axis between an open end and a closed end. A burst disc closes the closed end of the duct. One or more devices are provided in the duct, the device(s) being positioned or shaped to enable the burst disc to be visually inspected by looking along the duct through its open end, and to modify a sectional profile of the duct transverse to the duct axis so that the sectional profile of the duct changes between different stations along the duct axis. The one or more device(s) inhibit the formation of standing acoustic waves in the duct.

Abstract: A method of detecting collisions between an equipped mobile object travelling around an airport installation and at least one obstacle. The method comprises the following steps. Determining the real-time positions of the equipped mobile object in a reference frame tied to the airport installation. Reading at least one item of information contained in at least one marker fixed to the equipped mobile object. Determining an outline of the equipped mobile object on the basis of the read item of information contained in the marker. Positioning the outline determined in the reference frame tied to the airport installation. Triggering an alert if the distance between the outline of the equipped mobile object and the obstacle is less than a given threshold.

Abstract: A tooling for holding a set of preformed parts to be friction-welded together to construct a generally plane hollow structure is provide. The tooling includes a framework for receiving the preformed parts inside the framework for welding together to form the hollow structure. The framework includes shape-holder members which are shaped to correspond and contact the outer surfaces of the preformed parts. At least one anvil is disposed inside the framework. A reversible clamp is installed inside the framework and movable into a clamping position in which the clamp inflates to apply opposing thrust in at least two directions such that thrust is applied in a lateral direction to the anvil and applied in a second direction to the inside surface of the preformed parts disposed. The set of preformed parts is held in a welding position with the clamp and framework while a welding operation is performed.

Abstract: A deflector assembly for the rope/cable hanging from a hoist mounted on an aircraft (A). The deflector assembly has an adjoined anchorage that includes a socket face that internally has a sliding bearing in which is housed an innermost end, so that the innermost end is slidably guided relative to the adjoined anchorage to have one degree of freedom along a linear translation axis (LT). A remote anchorage has a support bracket for demountably mounting the remote anchorage to the fuselage. The rotorcraft can be chosen among: helicopters, hybrid rotary aircrafts, UAV rotorcrafts and inhabitable rotorcrafts including remote piloting functions.

Abstract: A supply system with a plurality of consumers, which can be supplied with a minimum volumetric flow by the supply system to ensure their operational function, wherein the supply system exhibits a network of lines with a plurality of lines, which are each hooked up to the consumers, and a pump connected to the lines for generating a volumetric flow of supply fluid in the lines, wherein the supply system incorporates a network of lines in which consumers are fluidically connected in parallel in relation to the pump arrangement, and wherein each consumer has allocated to it at least one flow control valve functionally placed upstream from the respective consumer in the cooling circulation as viewed from the position of the pump in the direction of flow.

Abstract: A system including a set of computation modules configured to be utilized for computation of gains of at least one piloting law relative to at least one piloting axis of the aircraft and a data capture unit for capturing in at least one computation unit associated with a given piloting axis of the aircraft first values illustrating aerodynamic coefficients of the aircraft and second values defining delay and filter characteristics of the control chain relative to the given piloting axis, the computation unit being configured to compute the gains of the piloting law utilizing at least a part of the set of computation modules and the computation unit computing inputs intended for at least one actuator of a control surface adapted to control the aircraft relative to the given piloting axis in accordance with a corresponding current control value.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprising the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position and a target landing position on the landing runway; g) comparing this maximum roll angle with a predetermined limit; and h) as a function of the result of the comparison carried out in step g), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.