Abstract: A method of opening a cargo door of an aircraft, the aircraft including a body with an opening into a cargo bay, and a cargo door which covers the opening when it is in a closed position. A cargo door is outwardly rotated with a first actuator from the closed position to a first open position. Then an actuator rod is installed by coupling a first end of an actuator rod to the body and coupling a second end of the actuator rod to the cargo door in the first open position. Then the cargo door is outwardly rotated with the actuator rod from the first open position to a second open position by increasing a distance between the first and second ends of the actuator rod.

Abstract: An actuation system for a cargo door of an aircraft. The cargo door covers an opening into a cargo bay when it is in a closed position. The actuation system includes a first actuator configured to outwardly rotate the cargo door from the closed position to a first open position, and a second actuator configured to outwardly rotate the cargo door from the first open position to a second open position.

Abstract: A fastening system for an aircraft to fasten at least one tank to contain liquid hydrogen, allowing easy access to the tank. The fastening system includes a longitudinal box, upper formers fastened to the upper end of the longitudinal box and lower formers fastened to the lower end of the longitudinal box, at least two upper formers including two fastening devices to each connect a fastening point of the tank to an upper former, at least one lower former including two second fastening devices to each connect a second fastening point of the tank to the lower former. The fastening system allows an operator to access the tanks that are capable of being fastened by the fastening system.

Abstract: A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.

Abstract: An aircraft floor grid transport system for assembling an aircraft fuselage barrel and method of calibrating the transport system are disclosed. The transport system includes a rectangular beam, a stabilizer device to be associated with referential positioning devices of an assembly platform and a plurality of fixing devices to be fixed to the floor grid, each of the fixing devices having a vertically adjustable length. The transport system makes it possible to handle the floor grid without deforming it in order to assemble a fuselage barrel.

Abstract: A method of monitoring friction associated with a plurality of aircraft wheels of an aircraft, the method including, for each of the plurality of aircraft wheels, obtaining wheel speed data associated with the aircraft wheel. The method includes determining, based at least in part on the wheel speed data, deceleration of the aircraft wheel during a time interval, and determining, based at least in part on the determined deceleration, a value indicative of friction associated with the aircraft wheel. The method includes providing, based at least in part on the determined value, a signal indicative of a level of friction associated with the aircraft wheel.

Abstract: An aircraft fuselage includes fore and aft sections, a barrier wall separating the sections and an opening therebetween, a rail attached to the barrier wall, a door moveable across the barrier wall between an open position offset from the opening and a closed position covering the opening, a first roller and a second roller rotatably fixed to the door and moveable on the rail along first and second paths to move the door, the rail including a first ramp engaging the first roller as it moves along the first path and to direct the first roller towards the barrier wall, and a second ramp engaging the second roller as it moves along the second path and to direct the second roller towards the barrier wall, the first roller configured to engage the first ramp as the second roller engages the second ramp to move the door towards the barrier wall.

Abstract: A method for optimizing a climb phase of an aircraft, implemented repeatedly during the climb phase, includes an acquiring step for acquiring current values of input parameters, a determining step for determining a current optimized DTflex value from the current values of the input parameters and from optimized DTflex values recorded in a database and a transmitting step for transmitting the determined current optimized DTflex value to a user system with a view to controlling the thrust of the aircraft, the method making it possible to continuously adapt, during the climb phase, the optimized DTflex value so it corresponds to current conditions of the aircraft to maximize its performance particular for fuel consumption.

Abstract: An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.

Abstract: A structure for an aircraft is disclosed including comprising at least one node which having first and second plates which are pressed against two opposite faces of a first reinforcement, and to which upstream and downstream reinforcements positioned on either side of the first reinforcement are connected. A connection system connecting the first and second plates is disclosed including at least one boss projecting from a surface of one of the plates pressed against the first reinforcement, for each boss, a housing recessed relative to a surface of the other plate pressed against the first reinforcement, configured to house the boss, and at least one fastening element, passing through the first reinforcement, connecting the first and second plates and spaced apart from the boss.

Abstract: An aircraft system for an aircraft is disclosed having a controller that is configured, during a take-off procedure, to initiate, prior to receiving a command to retract a landing gear, automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position, on the basis of a determination, made when a speed of the aircraft is determined by the controller to be equal to or greater than a first threshold speed, that a one engine inoperative condition is met.

Abstract: An aircraft with a unit to transmit information on ability/inability of pilots to fly the aircraft. Guidance avionics include guidance architecture and a flight controller to fly the aircraft. The guidance architecture has two dissimilar guidance chains and a selection unit connected thereto, to the flight controller and to the unit for measuring physical ability/inability, a first guidance chain to compute a main path for the aircraft towards a destination airport based on a current state of the aircraft by following a flight plan and to compute main guidance instructions for following the main path, a second guidance chain to compute an emergency path for the aircraft towards a diversion airport based on an initial portion of the common path with the main path and to compute emergency guidance instructions for following the emergency path. The selection unit receives the main and emergency guidance instructions and transmits either one to the flight controller.

Abstract: A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmembers parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

Abstract: An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.

Abstract: An aircraft propulsion assembly having an engine, a nacelle positioned around the engine, an annular duct delimited by the engine and the nacelle for a bypass flow of cold air, at least one bifurcation passing through the annular duct for connecting the engine and the nacelle and having a leading edge and a primary structure of a pylon housed in the bifurcation and configured to connect the engine to an aircraft wing. The propulsion assembly has at least one heat exchange device including a plate heat exchanger, having a hexagonal longitudinal section and positioned in the bifurcation. According to one configuration, the heat exchanger is a countercurrent heat exchanger.

Abstract: An output cone of an aircraft propulsive assembly extending in a general direction called longitudinal direction and including a front part and a rear part. The longitudinal assembly of the front part and rear part forms an acoustic treatment system with at least two degrees of freedom. Such a system allows for the treatment of several frequency ranges or of one wide frequency range by the treatment of several overlapping ranges.

Abstract: An aircraft landing gear is disclosed including a main leg, a foldable stay and a lock link configured to hold the foldable stay in position when the landing gear is extended. The foldable stay includes a first stay member and a second stay member, and the landing gear is configured such that the second stay member rotates in a first direction from a first position to a second position as the landing gear moves from a retracted configuration to an extended configuration. An end stop is arranged such that in the event the lock link fails, the second stay member rotates in the first direction from the second position to a third position in which the stay contacts the end stop thereby preventing further movement of the second stay member in the first direction and wherein the foldable stay goes over centre as the second stay member moves from the first position to the third position.

Abstract: An assembly method includes a succession of assembly steps of assembling fuselage components of the fuselage portion of the aircraft, for example the nose of the aircraft, to form a fuselage body, a mounting step of introducing, into the fuselage body thus formed, a floor module having at least a predetermined width, and which can be provided with items of equipment, and a fastening step of fastening the fuselage body to the floor module such that the floor module shapes the final shape of the fuselage body and the assembled fuselage portion is obtained, the floor module, which has at least a suitable predetermined width, making it possible, when it is incorporated into the fuselage body, to provide the fuselage body, which is slightly flexible, with its desired and definitive shape corresponding to the desired and definitive shape of the assembled fuselage portion.

Abstract: A guide system to enable installation of a cable tie on a supporting element by passing the cable tie through a first passage to traverse the supporting element, then through a second passage to come back to the same side of the supporting element, enabling the cable tie to surround one or more cables. The guide device includes a gutter with a guide surface with two curves, a first longitudinal curve enabling the surface to extend from a passage to the other passage and a second transverse curve forming a partial envelope for receiving the cable tie and guiding and holding the cable tie in the gutter. The device also has at least one protrusion with a wedging surface projecting from the surface of the gutter to come into contact with and wedge against the supporting element to lock the gutter in position in relation to the supporting element.

Abstract: A system includes at least one upper flexible skin intended to be fixed in the extension of an upper plane of the wing, a lower flexible skin intended to be movable in the extension of a lower plane of the wing and fixed along a trailing edge of the control surface, an actuator for generating a displacement of the lower flexible skin with respect to the lower plane. The displacement causes a curvature of the first, upper flexible skin and a curvature of the second, lower flexible skin having a concavity oriented in a same direction. The control surface system makes it possible to reduce the quantity of energy supplied by the actuator.