Abstract: A system for activating the distress beacon determines a positional difference between a theoretical position of the aircraft determined from data of the flight plan and a real position of the aircraft determined from the navigation and monitoring equipment installed in the aircraft. This system delivers an instruction to arm the distress beacon when one or more conditions are met, among which is the condition that the positional difference exceeds a predetermined value.

Abstract: An aeroplane includes an escape opening passing through an external skin and an internal bulkhead. The escape opening is closed off by an external escape hatch having an external opening controller. The aeroplane further includes an internal escape hatch that closes off said escape opening flush with the internal bulkhead, and kept closed by at least one catch movable between a locked state and unlocked state, a first opening controller that controls the passage from the locked state to the unlocked state of the catch being accessible from inside the aeroplane, and a second opening controller that controls the passage from the locked state to the unlocked state of the catch being positioned such that the actuation of the external opening controller of the external escape hatch or the passage of the external escape hatch from the closed position to the open position causes the second opening controller to be actuated.

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: A method of mounting at least one pressure port in a skin of an aircraft, where the port is made with a hollow tube implanted in the skin, optimizes conditions whereby each of the tubes is made flush with the skin so that static or dynamic pressure measurements are accurate and reliable. The method includes a step of leveling each of the tubes and a step of painting the skin. To achieve satisfactory leveling conditions for the tubes on each occasion, the leveling step is independent of the layer of paint deposited on the skin.

Abstract: An aeroplane includes an external skin and an internal bulkhead delimiting a cabin, and an escape opening passing through the external skin and the internal bulkhead. The escape opening is closed off by an external escape hatch disposed flush with the external skin. The aeroplane also includes an internal escape hatch that closes off the escape opening disposed flush with the internal bulkhead, and pressure regulating means capable of automatically triggering an opening of the internal escape hatch or a part of the internal escape hatch when a pressure differential on both sides of the internal escape hatch exceeds a determined value.

Abstract: The device includes a receiving unit for receiving at least a start point of an unspecified termination segment, an orientation of the unspecified termination segment and a start point of a following segment, a first computation unit for calculating a median plane passing through the start point of the following segment and perpendicular to this following segment, a second computation unit for calculating an operational distance, called calculated operational distance, as a function of the position of the start point of the unspecified termination segment relative to the median plane, using geometric data, and a transmission unit for providing at least one user means with the calculated operational distance.

Abstract: An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an auxiliary monitoring unit configured to perform a monitoring to detect an absence of activation of a protection mode by at least one of the engines of the aircraft although an activation command has been transmitted, and a disconnection unit to automatically disconnect the autothrust in case of the detection of such a situation, a disconnection of the autothrust resulting in the triggering of the protection function being stopped.

Abstract: A device for assisting in the production of wiring harnesses. The device includes a board, with a groove that makes it possible to receive cables. The device further includes an arrangement for transporting a cable, including a nozzle making it possible to position the cable in the groove of the board. Further, a control is configured and arranged to drive the displacement of the cable transport arrangement. Also, flexible and resilient holding elements are provided for holding cables in the groove. The holding elements deform to allow the nozzle to pass when the nozzle positions a cable in the groove and then revert to their initial form to hold the cable in the groove.

Abstract: Energy protection device for an aircraft. The device (1) comprises units (12, 14, 15) for automatically deactivating an energy protection function, if a return of the aircraft to an operational flight domain is detected after the activation of this protection function, and for automatically managing an autothrust (2), if at least one of the following conditions is satisfied: a relaxing of a control member is detected, and the angle of attack of the aircraft is below a predetermined threshold.

Abstract: An onboard avionic system for communication between an aircraft and the ground comprising a service unit connected to various aircraft equipment and a radio communications unit providing communication between the avionic system and a communications system on the ground via a radio channel. The system comprises a configuration unit having a control unit, a geolocation unit and a database in which are recorded, data relative to the use of the radio channels which are available in a flight zone, as well as data relative to the radio conditions for the available radio channels. The configuration unit, on the basis of the aircraft geolocation data supplied by the geolocation unit, of radio condition data of the current channel, and of database data, determines if the current channel should be changed or not and, if so, determines the new channel to be used and commands the change to the new channel.

Abstract: The automatic installation and uninstallation of software modules on equipment on an aircraft. For each reference of an obtained list of references of software modules to be installed or uninstalled, resolution rules linked to an operation associated with the software module in question are identified. The rules comprise at least one reference to an operation of installing or uninstalling at least the software module in question and a list of actions to be performed. For each reference on the obtained list, a list of references of operations to be carried out is determined depending on the obtained list and the identified resolution rules. A list of actions to be performed is determined depending on the list of references of operations to be carried out and the identified resolution rules. At least one referenced action on the list of actions to be performed is executed by calling a specific software agent.

Abstract: An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.

Abstract: A method for monitoring the coordinated execution of sequenced tasks by an electronic card including at least one first processor (PP1) and a second processor (PP2) synchronized to the same clock of determined time period, includes: recording in memory means by the first processor (PP1) of a first identifier (ID1) characterizing the time period (T1) in the course of which the first sequenced task has been executed; recording in the memory means by the second processor (PP2) of a second identifier (ID2) characterizing the time period (T1) in the course of which the first accessory task (N1) has been executed; comparing by the first processor (PP1) the first identifier (ID1) and the second identifier (ID2); and signaling by the first processor (PP1) in the case of failure of the comparison so as to signal a defect of coordination of the processors (PP1, PP2).

Abstract: The invention relates to an aircraft (10) having a system for measuring a static reference pressure in flight, which system comprises: a pressure sensor (22) connected to the rear portion of the aircraft by a cable (16) and associated with a pressure intake (24) that is located, in flight, in an undisturbed zone downstream from the aircraft, the pressure signal (22) being suitable firstly for measuring a pressure coming from the pressure intake (24) and secondly for transmitting a signal representative of the measured pressure, e.g. an electric signal, to the aircraft; and a system (34) on board the aircraft, which system is suitable for determining a pressure measurement firstly from the transmitted signal and secondly from a position of the pressure sensor (22) relative to the aircraft (10). Pressure is measured dynamically while the aircraft is climbing or descending.

Abstract: A pilot assistance device includes information sources for determining automatically, in real time, a current vertical load factor of the aircraft, a computation unit for computing automatically, in real time, a flight director value using the current vertical load factor and a target vertical load factor representing a vertical load factor desired for the aircraft in the parabolic flight, the flight director value being computed in such a way as to be equal to a reference value when the current vertical load factor becomes equal to the target vertical load factor, and a display unit for presenting automatically, in real time, on a load factor scale, displayed on a screen of the cockpit of the aircraft, an indicator representative of the flight director value, computed by the computation unit, and an indicator indicating the reference value.

Abstract: An aircraft includes at least one wall delimiting a first zone (I) of the aircraft which is thermally insulated from the outside of the aircraft and a second zone (E) contained within the aircraft which is not thermally insulated with respect to the outside of the aircraft and a heat exchanger inside which a heat transfer fluid circulates, wherein the wall includes at least one duct inside which the heat transfer fluid circulates so as to act as a heat exchanger.

Abstract: A preferred method of the invention is executed by code stored on a non-transient medium to control a portable computing device with a touchscreen. The code generates graphical interfaces includes an application that allows a user to capture necessary data for reporting data to permit quick and efficient diagnoses of repairs by a repair service to a part or sub-assembly of an aircraft. The data acquisition is controlled and guided with reference to actual aircraft specifications that are updated by an aircraft part supplier, such as an aircraft manufacturer.

Abstract: Redundant storage devices in particular suitable for so-called SSD electronic disks. A data storage system is proposed based on a plurality of redundant physical storage disks in which the read/write commands intended to be sent to the redundant disks are subjected to a transfer function before being sent to at least one of the disks so that the actual commands sent to at least two disks are different. The values returned by the disks that received the commands that had undergone the transfer function are subjected to the inverse transfer function. Thus, a design error in the control module of the disks will be detected, since the control modules of the disks will not be called identically.

Abstract: A method, apparatus and computer program product for modeling the non-linear structural response of a component. The non-linear structural response is modeled using a two-step global-local finite element analysis method, which employs a linear global analysis step, a linear intermediate analysis step and a non-linear local analysis step. The boundary conditions applied in the intermediate step are derived in part from the linear global analysis and the boundary conditions applied in the local analysis are derived in part from the global and intermediate analyses.

Abstract: A method for monitoring the coordinated execution of sequenced tasks by an electronic device including a main electronic card including at least one main processor synchronized to a main clock and at least one auxiliary electronic card including at least one auxiliary processor synchronized to an auxiliary clock, includes emitting by the main processor of a coordination marker to the auxiliary processor at the start of each main time period; emitting by the auxiliary processor of a response word formed on the basis of the last coordination marker received to the main processor at the end of each auxiliary time period; validating by the main processor of the response word received with respect to the first coordination marker emitted; and signaling by the main processor if the response word received is not valid so as to signal a defect of coordination of the auxiliary processor.