Abstract: To produce an insulated current sensor for slaving power devices in the field of avionics, use is made of a magnetic core through which there passes an element traversed by a current to be measured. The magnetic core comprises a secondary winding across the terminals of which are connected an oscillator and a measurement device. The cooperation of the oscillator and of the measurement device makes it possible to circumvent all the traditional drifting of current sensors.

Abstract: The device for locking an engine (1) on a pylon (2) comprises a front attachment region (12) at the location of the separation between two compressors (5) and (6) and a rear attachment system (13) positioned at the rear of the turbines (9), close to the center of gravity (C). Further the rear attachment system (13) is more flexible than the other either by its own design or by being suspended from the pylon by a more flexible portion (21). This device is advantageous for reducing the level of vibrations transmitted to the aircraft (24) by the engine (1). The extension of the pylon is reduced relatively to customary designs and disk shots have less to be feared. The invention symmetrically applies to “towed” engines, the fan of which is at the front rather than at the rear.

Abstract: The disclosed embodiments relate to a defogging or de-icing system for an optical instrument including a protection housing. According to the disclosed embodiments, the system includes: a porthole covered on at least one face thereof with a heat conducting film provided at the edge of the useful area of said porthole, the porthole being mounted on the protection housing, heating members placed in contact with the film for heating said film, and a power supply circuit for the heating members.

Abstract: A method of managing an electrical power supply outage on board an aircraft, including the following operations: —detection of an electrical power supply outage, —measurement of a duration of the power supply outage by measuring a discharge time of a capacitor and comparing this measured duration with a threshold duration, —saving a long outage indication when the duration of the outage is greater than a threshold duration. The disclosed embodiments also relates to a system implementing this method and including: —a circuit for detecting an electrical power supply outage, —a circuit for measuring a duration of the power supply outage, and—a circuit for managing indications able to manage emissions of signals according to the measured duration of the power supply outage.

Abstract: Method for automatic script generation for testing the validity of operational software of a system onboard an aircraft and device for implementing the same. The aspects of the disclosed embodiments relate to a script generation method for testing the validity of operational software of a system onboard an aircraft, wherein it includes the following steps: a) identifications by a developer of valid test cases in an interactive manner by positioning an entry point and a stop point respectively at the start and at the end of a function of the operational software being tested. b) observing and recording states of variables of said function via the position of the stop point and the entry point. c) automatically generating a test script firstly by analyzing the states of variables observed during the identification of the test cases and secondly by generating a test script in the form of a source code. d) automatically executing in a test execution environment, tests for the generated test script.

Abstract: A method for debugging the program of operational software of an onboard system, including flagging the program by positioning flags along an execution path for dividing the aforementioned execution path into adjacent functional intervals; normal execution of the program; acquiring an execution condition of the program by flag condition vectors; when an error is detected, searching a faulty functional interval based on the flag condition vectors, reverse execution of the program in the aforementioned faulty functional interval, and determination and correction of the error.

Abstract: The invention relates to a method of routing the physical links of a avionics platform inside an aircraft. A physical link connects a plurality (N) of equipment units and is composed of one or more branches, where each branch of said link connects a sender equipment unit to a receiver equipment unit. The proposed method makes it possible to minimize the total cabling length of the platform and, where applicable, to choose among various positions of the equipment units inside the aircraft and/or various routing graphs.

Abstract: A turbojet engine for an aircraft that includes an engine provided in a nacelle and at least one heat exchanger for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting the aforementioned partially-cooled hot flow into the aforementioned propulsion system, wherein at least one heat exchanger is a radial heat exchanger extending in the lower portion of the turbojet engine at a lower branching of the turbojet engine.

Abstract: A method for processing the volume of information handled during the debugging phase of an operational software onboard an aircraft includes: dividing the execution path of the operational software into functional intervals by placing progression points at each function of the program; placing control points associated with each progression point; normal execution of the program that includes: storing the execution state of the program at the location of each progression point, wherein the storage of an execution state results in the suppression of the execution state previously stored for said progression point; upon the detection of an error, searching the progression point corresponding to a faulty function; searching for a software start execution state; regenerating the start execution state; correcting the error in the faulty function; and re-executing the program.

Abstract: A method for assembling a part of a metal material and a part of a composite material, the junction of the two parts being achieved through a fastener having a substantially constant section and received in a first hole formed in the part of a metal material and a second hole formed in the part of a composite material. According to the disclosed embodiments and before assembling the aforementioned parts, the method includes: an expansion step for generating a field of compression stresses at the periphery of the first hole and locally in the material constituting the part of a metal material using an expansion tool; a single boring step for making the first hole and the second hole with a diameter Øfinal substantially larger than the diameter of the fastener in order to leave a gap between the inner walls of the holes and the outer surface of the fastener; and an assembling step for placing the fastener inside the holes for maintaining together the metal part and the composite part.

Abstract: The invention relates to a method for optimisation of the avionics platform of an aircraft, intended to implement a set of avionics functions. The association between the platform's functional architecture elements (functions, functional links) and the elements of its equipment architecture (equipment, network paths, direct physical links) are formalised by sets of constraints in the form of linear inequalities of decision variables. Certain segregation or co-location functional constraints are also envisaged. Optimisation of the avionics platform is achieved through the minimisation of cost functions which are linearly dependent on said decision variables. This minimisation under constraints is achieved in an effective manner by the Simplex algorithm.

Abstract: The invention concerns a method for assisting the construction and validation of an avionics platform. It uses, on the one hand, a functional description of the platform using avionics functions, software modules suitable for executing these functions, and functional link occurrences between these modules and, on the other hand, a material description of this platform using calculation or communication items of equipment and physical links between these equipment. The method according to the invention enables to generate paths between the various items of equipment by using direct physical links and/or physical links belonging to one or more network(s), and subsequently to associate at least one such path to be each functional link occurrence. It also enables to associate to each software module an item of equipment adapted to host it.

Abstract: The invention relates to a method of computer simulation of the aerodynamic behaviour of an aircraft (10) in flight close to the ground. This method is used to identify the slope effect relative to the ground effect. To achieve this, a uniform boundary condition comprising a predetermined speed (UP) with a non-zero tangential component and a non-zero normal component is imposed on a plane (21) modelling the ground; and a discrete numerical model of the Navier-Stokes equations is solved by computer on a volume mesh with said boundary condition imposed on said plane (21), so as to obtain a numerical solution for a fluid flow inside a computational domain defined by said mesh.

Abstract: The present invention relates to a display device for a glass cockpit of an aircraft, intended to provide video streams to a plurality of viewing screens of said glass cockpit, said aircraft being partitioned into a secured area, a so-called avionic world (AW), and a non-secured area, a so-called open world (OW), said system comprising at least one first port intended to receive first data to be displayed from a system (210, 310, 410) belonging to the avionic area and at least one second port intended to receive second data to be displayed from a system (220, 320, 420) belonging to the open world, the display device comprising: predetermined hardware resources allocated to the processing of the second data; a processor (241, 341, 441), belonging to the avionic area, adapted to controlling the hardware resources used by said processing and interrupting this processing if said hardware resources used exceed said allocated resources.

Abstract: The invention relates to a seat for a vehicle, that includes a headrest with a headstall for supporting the head of a passenger in the seat, wherein the occupant may or may not wear a protection helmet depending on the circumstances. The headstall can assume at least three stable positions: a first position for the cervical support of the head of the seat passenger in which the headrest provides a cervical support function with or without wearing a helmet; a second position for the occipital support of the head of the seat passenger in which the headrest provides an occipital support function without wearing a helmet; a third position for the occipital support of the head of the seat passenger in which the headrest provides an occipital support function while wearing a helmet.

Abstract: A fire extinguisher device for aircraft has a hanger structure (4) and a reservoir (3) of extinguishing agent, said reservoir being hung beneath said hanger structure by metal fittings (300, 301a, 301b) held by fasteners to said hanger structure. Said extinguisher is characterized in that the reservoir (3) has means of suspension (31) and the hanger structure (4) has carriers (41) complementary to the means of suspension (31), said means of suspension and said carriers being such that when the fasteners are withdrawn, the reservoir (3) is in a position called the “intermediate position,” in which the metal fittings (300, 301a, 301b) are free and the reservoir (3) is suspended by interaction of the means of suspension (31) and the carriers (41). The invention also relates to a method for fastening such an extinguishing device.

Abstract: A method for simulating a real on-board system for testing an operating software program. The disclosed embodiments include preparation of a test to be carried out on the operating software program, by adding and/or removing control functions to/from a library; execution of the operating software program of the real on-board system in a simulated environment; simulation of a dedicated peripheral by activating functions from the library; transmission of the test results from the dedicated peripheral to the results folders stored on the host platform and recording of the aforementioned results.

Abstract: The invention refers to a blade (2) for an aircraft turbomachine receiving part comprising a root (8), and an airfoil part (14) prolonging this root. According to the invention, the airfoil part (14) includes a mechanical fuse (60) located at a distance from the bottom of the blade, along the length direction of the airfoil part (14), between 0.25 and 0.5 times the length of said airfoil part (14) along this length direction.

Abstract: The invention concerns an aircraft turbomachine propeller comprising a plurality of blades (1) each comprising a root (20) mounted on a hub (2) rotating about the rotation axis of the propeller (I-I), and its purpose is to reduce the risks of loss of the entire blade (1) following an impact by a foreign body. To achieve this, at least one blade (1) comprises a means (30) of retaining the blade in an outwards radial direction, said retaining means (30) being engaged in a housing (5) of said blade (1) opening radially inwards at the root of the blade (20), and fixed in translation in said outwards radial direction.

Abstract: The invention relates to a current return network element (1) for aircraft particularly with high conductivity. The purpose is achieved by using a plurality of electrically conducting strips (2) intersecting each other and made from a single piece, at a spacing from each other so as to form a plurality of openings (4) between them.