Abstract: The invention relates to: Control circuit (1) for an electrical device (2), said control circuit (1) receiving as input a discrete electrical control signal (CMD), the control circuit (1) comprising a source (11) of voltage (±V) configured so as to supply the circuit according to a negative or positive voltage; a switch (12) normally closed in the absence of any discrete electrical control signal (CMD) and configured so as to isolate the electrical device from the voltage source as a function of the electrical control signal (CMD), said switch being connected between the voltage source and the electrical device (2); the switch (12) being sensitive to the discrete electrical control signal (CMD) for just one sense of voltage.

Abstract: A flight control system of an aircraft including a first processing unit, a second processing unit, communication means configured to establish a first two-way digital link and as second two-way digital link between the first processing unit and the second processing unit. The second link is redundant with the first link, and the first link and second link are likely to be active concomitantly. The system further includes backup communication means enabling data exchanges between the first processing unit and the second processing unit in the case of a failure in the first link and second link. The backup communication means includes an array of sensors or actuators and/or a secure onboard network for the avionics.

Abstract: The invention relates to an overspeed protection device of an aircraft engine.

Abstract: The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: •—sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, •—receiving, from

Abstract: An embodiment circuit includes a first voltage divider coupled between a first voltage level and a ground potential. The circuit further includes an error amplifier having a first input terminal coupled to a node between a first resistive element and a second resistive element of the first voltage divider. The circuit further includes a second voltage divider coupled between a second voltage level and a reference voltage, wherein a second input terminal of the error amplifier is coupled to a node between a third resistive element and a fourth resistive element of the second voltage divider, and wherein an output voltage of the error amplifier is configured to control a potential difference between the first voltage level and the second voltage level.

Abstract: An embodiment circuit includes a first voltage divider coupled between a first voltage level and a ground potential. The circuit further includes an error amplifier having a first input terminal coupled to a node between a first resistive element and a second resistive element of the first voltage divider. The circuit further includes a second voltage divider coupled between a second voltage level and a reference voltage, wherein a second input terminal of the error amplifier is coupled to a node between a third resistive element and a fourth resistive element of the second voltage divider, and wherein an output voltage of the error amplifier is configured to control a potential difference between the first voltage level and the second voltage level.

Abstract: The invention concerns a system on a chip (100) comprising a set of master modules which includes a main processing module (101a) and a direct memory access controller (DMA) (102a) associated with said module (101a), and at least one secondary processing module (101b) and a DMA (102b) associated with said module (101b), and slave modules; each master module being configured for connection to a clock source, a power supply, and slave modules which include a set of proximity peripherals (105a,b), at least one internal memory (104a,b) and a set (106) of peripherals and external memories shared by the master modules; said clock source, power supply, proximity peripherals (105a,b) and a cache memory (103a,b) of a master processing module and its DMA being dedicated to said master processing module and not shared with the other processing modules of the set of master modules; and said at least one internal memory (104a,b) of each master processing module and its DMA being dedicated to said master processing module,

Abstract: The present invention concerns a flight control system of an aircraft comprising: —a first processing unit (1), —a second processing unit (2), —communication means configured to establish a first two-way digital link (3) and a second two-way digital link (4) between the first processing unit (1) and the second processing unit (2), said second link (4) being redundant with the first link (3), and said first link (3) and second link (4) being likely to be active concomitantly, said system further comprising backup communication means enabling data exchanges between the first processing unit (1) and the second processing unit (2) in the case of a failure in the first link (3) and second link (4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14).

Abstract: The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: •—sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, •—receiving, from

Abstract: The invention relates to: Control circuit (1) for an electrical device (2), said control circuit (1) receiving as input a discrete electrical control signal (CMD), the control circuit (1) comprising a source (11) of voltage (±V) configured so as to supply the circuit according to a negative or positive voltage; a switch (12) normally closed in the absence of any discrete electrical control signal (CMD) and configured so as to isolate the electrical device from the voltage source as a function of the electrical control signal (CMD), said switch being connected between the voltage source and the electrical device (2); the switch (12) being sensitive to the discrete electrical control signal (CMD) for just one sense of voltage.

Abstract: The invention relates to an overspeed protection device of an aircraft engine

Abstract: A method of displaying, for a system for anti-collision monitoring of an aircraft, the limits of flight margins in relation to obstructions located in a flight zone, and a device for displaying the limits of operational flight margins and the limits of alert zones, is provided. The operational flight margins in the flight zones not initially envisaged, and the limits of the alert zones around the trajectory of the aircraft, are presented.

Abstract: The invention concerns a bandwidth control method in an on-chip system comprising at least one main master module, at least one secondary master module, at least one slave module and a bus connected to each module on a communication link, the bus comprising interconnection means to make at least one common slave module communicate with at least one main master module and with at least one secondary master module via at least one common path portion, the method comprising the following steps carried out for each common slave module: first detection of a first request to access the common slave module, issued by a main master module, definition of a blocking time Dj associated with the common slave module, blocking, during blocking time Dj, of any data transfer on the at least one common path portion between a secondary master module and the common slave module.

Abstract: The invention in particular concerns a method for filtering access to an on-chip system comprising at least one master module, at least one slave module and a bus, the bus comprising at least one slave port, at least one master port and means for interconnection between at least one of the slave ports and at least one of the master ports, the method being characterised in that it comprises the following steps implemented when an access request is routed from a master module connected to a slave port to a slave module connected to a master port: intercepting an item of source information on the link between the master port and the slave module before the slave module receives the request, searching for the item of source information in at least one access control list controlling access to the slave module, blocking the request such that the slave module is unaware of the requested access if the item of source information is not found in the at least one access control list.

Abstract: The invention concerns a method for monitoring transactions in an on-chip system comprising at least one main master module, at least one secondary master module, at least one slave module and a bus connected to each module, the bus comprising interconnection means to make at least one common slave module communicate with at least one main master module and with at least one secondary master module, the method comprising the following steps implemented during each transaction between a secondary master module and a common slave module: starting a counter upon initial detection of a transaction start signal, waiting for a final detection of a transaction end signal within a predefined time T, closing the transaction if the time tc that has elapsed since starting the counter is greater than predefined time Tmax, and reinitialising the counter.

Abstract: The invention relates to a method for aiding the taxiing of an aircraft comprising a plurality of onboard propulsion means and which is able to move over an airport zone according to at least one specific taxiing procedure making it possible to reduce fuel consumption, the method being characterized in that it implements the following steps during the phase of taxiing of the aircraft on an airport: Checking of the taxiing conditions for the implementation of the said taxiing procedure and calculation of the implementation parameters of the procedure, Calculation of the taxiing performance data resulting from the implementation of the taxiing procedure, Display of the taxiing directives and performance related to the taxiing procedure, Monitoring of the parameters of the avionics systems during the implementation of the taxiing procedure. The invention applies to taxiing plan formulation systems and/or aircraft monitoring systems.

Abstract: The invention relates to a method of alert calculation for an aircraft obstruction proximity warning system including a step for detecting a hazardous flight situation capable of triggering an alert as a function of a data signal representing the change in height below the aircraft, including, prior to the step of detection, a step for converting the data signal representing the change in height as a function of information representative of the vertical profile of the obstructions below the aircraft.

Abstract: An embodiment of a voltage regulation circuit includes a DC-DC converter configured to control a first current provided from a source to a load via a first output, and a linear regulator configured to control a second current provided from the source to the load via a second output. The voltage regulation circuit further includes a single control loop configured to receive an output voltage across the load and a first reference voltage. The single control loop is further configured to generate a single error signal between the output voltage across the load and the first reference voltage and to control the DC-DC converter and the linear regulator using the single error signal such that when the single error signal is outside of a predetermined range the DC-DC converter provides the first current to the load and the linear regulator provides the second current to the load simultaneously.

Abstract: The invention is situated in the field of displaying on board an aircraft geostationary elements of the navigation database on a screen having different display resolutions for the purpose of this data display, and its subject is a method for simplifying the display of stationary elements of this onboard database. This method is characterized in that it consists in precalculating a “decluttering” during the process of producing the onboard database by meshing the Earth with a Cartesian grid oriented along the latitudes and longitudes of the Earth, and by allowing only the most pertinent obstacle to appear in each rectangle of this grid.

Abstract: Described are a collision prevention device and a method for a vehicle in motion on the ground. The collision prevention device includes means for localizing obstacles; means for acquiring obstacle localization data; means for localizing the equipped vehicle; a collision prevention computer, and presentation means for presenting warnings to a driver of the equipped vehicle.