Abstract: An electrical flight control system for controlling an aircraft, the flight control system comprising at least one subassembly for acquiring a piloting command in order to acquire the piloting command from an operation of an associated piloting member that can be operated by a pilot of the aircraft along at least one piloting axis, the flight control system comprising at least three position sensors per piloting axis generating position information of the piloting member and being in communication with the at least one acquisition subassembly. Each acquisition subassembly comprises at least three simplex computers each having a single calculation channel connected to one of the at least three position sensors.

Abstract: An electric flight control system comprising an actuation subassembly, having three external duplex computers for controlling an electric actuator. The electric actuator has three stators electrically connected to three respective switching devices, the switching devices being electrically connected to a same internal simplex computer of the electric actuator, each switching device being connected to a respective external duplex computers, each switching device being configured to connect the internal simplex computer or respective external duplex computer to the associated stator, the internal simplex computer being self-monitored and communicating with the three external duplex computers.

Abstract: An electrical flight control system for controlling an aircraft. The flight control system comprises a plurality of functional subassemblies each having at least one primary computer and at least one dissimilar secondary computer, at least one functional subassembly being a simplex/duplex subassembly comprising at least three identical simplex primary computers and at least one duplex secondary computer, each duplex secondary computer of a simplex/duplex subassembly comprising an independent and synchronized control calculation channel and a monitoring calculation channel, each simplex primary computer of a simplex/duplex subassembly having a single calculation channel, and wherein, except in the event of failure, the three primary computers of a simplex/duplex subassembly form two virtual pseudo-duplex computers.

Abstract: A mechanical flight control system of an aircraft provided with an actuator and a force-measuring device, the actuator comprising at least one electric motor and one duplex calculator per motor, each duplex calculator comprising a control channel, a monitoring channel and two input interfaces, the force-measuring device comprising a plurality of measurement channels each comprising a sensor, an electronic module and an output interface connected to one of the input interfaces. the electronic module is connected to the sensor in order to generate an analog measurement signal and is configured to digitize the analog measurement signal, at least one of the measurement channels applying a delta-sigma modulation, and then to convert it into a digital transfer signal carrying a transfer value representative of a force in the mechanical flight control system.

Abstract: A control device comprising a lever provided with a magnetic dipole and able to move, at least in rotation, relative to a support about an axis. The control device includes a measuring device configured to measure a magnetic field generated by the magnetic dipole, and a monitoring system for monitoring the integrity of the control device. The monitoring system is configured to signal an anomaly using an alarm when a first norm of a first vector difference between the current magnetic field and a first reference magnetic field relating to an estimated orientation of the lever, is greater than a first magnetic field threshold for a duration greater than a duration threshold.

Abstract: An architecture for transmitting data within an avionics system fitted to a vehicle, the architecture comprising a first field bus and a first avionics bus. According to the invention, the architecture comprises at least two primary channels each comprising: a primary field interface enabling communication between each primary channel via the first field bus, the field interfaces being interconnected with the first field bus; and a first avionics interface compatible with the first avionics bus. The architecture comprises at least one primary computer provided with a second avionics interface in communication via the first avionics bus with only one first avionics interface among the first avionics interfaces.

Abstract: A control device comprising a lever provided with a magnetic dipole and able to move, at least in rotation, relative to a support about an axis. The control device includes a measuring device configured to measure a magnetic field generated by the magnetic dipole, and a monitoring system for monitoring the integrity of the control device. The monitoring system is configured to signal an anomaly using an alarm when a first norm of a first vector difference between the current magnetic field and a first reference magnetic field relating to an estimated orientation of the lever, is greater than a first magnetic field threshold for a duration greater than a duration threshold.

Abstract: A redundant and dissimilar system for monitoring the status of contactors of an aircraft control stick. This monitoring system comprises at least one electrical power source, at least one processor and several circuits for monitoring the status of the switches of the contactors. Each monitoring circuit comprises and electrical power source, a switch for each contactor, the switches of a contactor being connected to each other, and an electronic assembly provided with receivers arranged in series with each other. Each switch is arranged in parallel with at least one receiver so as to short-circuit the at least one receiver when the switch is in the closed state. Each processor measures and analyses an electrical feature of the electronic assembly, such as a mains voltage VE as the terminals of the electronics assembly, in order to determine the status of each switch.

Abstract: A redundant and dissimilar system for monitoring the status of contactors of an aircraft control stick. This monitoring system comprises at least one electrical power source, at least one processor and several circuits for monitoring the status of the switches of the contactors. Each monitoring circuit comprises and electrical power source, a switch for each contactor, the switches of a contactor being connected to each other, and an electronic assembly provided with receivers arranged in series with each other. Each switch is arranged in parallel with at least one receiver so as to short-circuit the at least one receiver when the switch is in the closed state. Each processor measures and analyses an electrical feature of the electronic assembly, such as a mains voltage VE as the terminals of the electronics assembly, in order to determine the status of each switch.

Abstract: A haptic device comprising a base and at least one shaker branch. Said at least one branch is connected to the base by mobility means conferring a degree of freedom on the branch to move in rotation about a pivot axis relative to the base. An exciter member comprises electrical exciter means configured to cause said at least one branch to shake by moving in rotation about the pivot axis from a rest position to an activated position, and resilient return means tending to maintain each branch in the corresponding rest position.

Abstract: A haptic device comprising a base and at least one shaker branch. Said at least one branch is connected to the base by mobility means conferring a degree of freedom on the branch to move in rotation about a pivot axis relative to the base. An exciter member comprises electrical exciter means configured to cause said at least one branch to shake by moving in rotation about the pivot axis from a rest position to an activated position, and resilient return means tending to maintain each branch in the corresponding rest position.