Abstract: Aircraft flight management devices, systems, computer readable media, and related methods are provided. The present subject matter includes devices, systems, computer readable media, and related methods of providing flight management control during abnormal events and/or situations requiring diversion from the present mission. In some aspects, a system for providing flight management may include a computing platform with a processor, a memory, and a flight management application module (FMAM) configured to receive data from multiple servers. The FMAM may also calculate one or more aircraft ranges and/or diversion routes based upon the received data. In some aspects, systems and devices disclosed herein may be configured to provide diversion assistance by selectively displaying information including the map, one or more of the aircraft ranges, a vertical display, and information regarding one or more airports.

Abstract: A switched-mode power supply device includes a charger (10) to be connected on one side to a direct current electrical network, or rectified alternating current electrical network (RC), a power reserve (11) connected to a second side of the charger (10), and DC-DC output converters (12) delivering regulated output voltages (VS). The output converters (12) are connected by an input to the first side of the charger (10). The charger (10) is a current bidirectional, voltage unidirectional converter which, in a first phase, enables the power reserve (11) to be recharged and maintained charged from the network, where the output converters (12) are powered by the network (RC) and, in a second phase, in the presence of a power brown-out of the network (RC), enables the power reserve (11) to be discharged to power the output converters (12).

Abstract: A device for exciting a landing gear of an aircraft while it is on the ground. The device includes an oblong bracing foot, a movable support on which the oblong foot is mounted and an arrangement for setting the gear into vibration.

Abstract: A device for forming a microstructured coating on a substrate. The device includes a microstructured band that can be moved by rolling without slipping on the substrate and going around main pressure application elements assembled on a chassis, and secondary pressure application elements assembled on the chassis so as to be in contact with an inner face of the band in a zone of a strand of the band delimited by said main pressure application elements, this zone being exposed to the action of a curing apparatus that accelerates curing of a curable material designed to form said coating. A method for forming a microstructured coating using the above-mentioned device.

Abstract: An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use.

Abstract: The invention relates to a method for transmitting data, characterized in that it includes a step of transmitting in-flight data between a first aircraft and at least a second aircraft, the data transmitted being data stored in at least one black box on board the first aircraft.

Abstract: The invention pertains to a method and apparatus for verifying the consistency of the values given by an angle of attack probe of an aircraft. The method and apparatus verifies the proper operation of the angle of attack probe by using the aircraft's vertical load factor measurement provided by an accelerometer to estimate the angle of attack and then comparing the estimated angle of attach with the measure angle of attack.

Abstract: A mould including: a central core having a side wall with a plane external surface; an internal mould element having an internal surface facing the external surface of the central core, with surfaces inclined to the vertical in order to form an angle of clearance, and a substantially vertical external surface; an external mould element fitted against the internal mould element and having a substantially vertical internal surface facing the external surface of the internal mould element; at least one of the facing surfaces being designed to receive a substantially vertical lateral preform so that the internal mould element and the external mould element are suitable for clamping said lateral preform.

Abstract: This aircraft nose structure comprises frames (2, 4, 6), a lower windshield frame member (12) and an upper windshield frame member (14) which are adapted to receive a windshield. The lower windshield frame member (12) has an arcuate shape with two branches which are connected together by a tie-rod (26).

Abstract: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Abstract: An engine attachment pylon for mounting an aircraft engine to an aircraft structure while minimising vibrations induced into the engine attachment pylon during flight and operation of the engine. The engine attachment pylon according to the present invention comprises a rigid box like structure housing a resonator which is tuned to attenuate tension and compression vibrations, experienced by the engine attachment pylon. The engine attachment pylon is primarily used in combination within another identical engine attachment pylon, both being linked together on a vertical plane within the fuselage by a hinge like junction, and each engine attachment pylon being raised approximately 30° from the horizontal axis of the fuselage.

Abstract: Interactive dialog devices and methods can be installed on an aircraft for communication between an operator of the aircraft and a guidance system of the aircraft. A dialog device can include a global screen configured for displaying guidance information related to each of a navigation display, a vertical display, and a primary flight display. The global screen can include at least one graphic object which is produced in the form of an interaction element which represents a control feature that can be grasped and moved by an operator to modify a value of at least one guidance target of the guidance system associated with one or more of the navigation display, the vertical display, or the primary flight display.

Abstract: A composite panel with protected parallel stiffeners has a multiply front face coming to an edge and extending between two lateral flanks of outside plies, symmetrically relative to a median plane (Pm). A device for protecting each stiffener includes a structural section that caps the stiffener symmetrically relative to this median plane (Pm). This structural section includes a so-called upper section formed above the edge and configured to envelop a space above the edge, a so-called lower section framing the lateral flanks by means of longitudinal walls (Pi) fastened to these flanks, and an intermediate section bearing at least partially on the edge via transverse walls (Pb) so as to minimize the propagation of impact forces to the lower section.

Abstract: An aircraft ground or sea approach anomaly detection method. The method includes the steps of characterizing a flight phase of the aircraft, determining a prohibited flight envelope, defining a set of prohibited vertical speeds of the aircraft for given altitudes in relation to the ground or the sea, as a function of the flight phase of the aircraft characterized, and detecting a ground approach anomaly of the aircraft as a function of a current vertical speed and altitude in relation to the ground or the sea of the aircraft, in relation to the prohibited flight envelope determined.

Abstract: Interactive dialog devices and methods are provided for use by an operator of an aircraft with a guidance system of the aircraft. The dialog devices and methods can include an interaction on a screen that can represent, on the one hand, a playback element indicating the value of a guidance target of the guidance system of the aircraft, and on the other hand, a control element that can be grasped or selected and moved on a display along a path, such as for example a curve, by an operator to modify the value of the guidance target.

Abstract: A device for carrying out a test on a fluid circuit of an aircraft including a test unit which includes, at the inlet, at least one means of connection to a pressurized gas supply connected to means for regulating the pressure of the gas provided by the supply as a function of the test to be carried out and, at the outlet, at least two connection means connected to the means for regulating the pressure of the gas, wherein at least two connection means have different dimensions tailored to a range of pressures or a given pressure.

Abstract: A method for disassembling two ultrasonically welded elements, one of the elements comprising, at a surface opposite the other element, an energy director that concentrates the heating during ultrasonic welding and forms a material junction between the two assembled elements after the ultrasonic welding. The method includes the steps of positioning a wire between the two assembled elements, so as to be secant to the energy director, said wire having suitable mechanical characteristics allowing it to cut the junction formed by the energy director and moving the wire between the two assembled elements so as to cut said junction.

Abstract: A system for controlling energy of a vehicle, for example an aircraft, comprising a control interface able to be in at least one first and one second state, the first state being an instruction state in which the interface generates at least a first instruction for speed of variation of a current energy of the vehicle and the second state being a resting state in which it gives no instruction, the interface furthermore being configured to return into the second state after having been brought into the first state.

Abstract: The invention is aimed at a method simulating the aerodynamic flow around an aircraft, so as to detect the aerodynamic loads exerted on a predetermined surface of the aircraft. The method includes a phase of determining a value denoted QA of global dynamic pressure at the level of the predetermined surface of the aircraft. The method includes steps of carrying out simulations of aerodynamic flow around the predetermined surface of the aircraft for given environmental conditions, on the basis of a mesh produced around the shape of the aircraft, determining a local dynamic pressure qA around the predetermined surface of the aircraft, and then calculating the global dynamic pressure QA.

Abstract: A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them.