Abstract: A device for actuating an aircraft undercarriage leg includes an electronic controller and an actuator. The actuator includes a three-phase electric motor connected to the electronic controller. The device is arranged to authorize gravity deployment of the aircraft undercarriage leg. The motor includes a stator having at least first and second star-coupled three-phase windings. The electronic controller includes a first control channel connected to the first three-phase winding, and a second control channel connected to the second three-phase winding. Each of the control channels includes a controller that generates a high-level control instruction, a driver that generates a low-level driver instruction from the high-level control instruction, and a braking circuit that brakes the motor during the gravity deployment of the leg by using energy produced by the motor. The device is arranged to use the control channels as a function of the availabilities of the components of each channel.

Abstract: Electric motor comprising a rotor and a stator (2), the stator comprising a body (3) forming a frame and a windings assembly (4, 5) housed in slots of the body. The electric motor comprises at least one rod (16, 23) used to connect, to one another, at least two fixed assembled parts of the electric motor, the rod extending into a housing (9) formed in the body over the entire length thereof in order to emerge on each side of the body.

Abstract: A device for measuring a relative rotation speed and/or a relative angular position between a first rotating element (2) and a second rotating element (3). The device includes a structure for generating a magnetic field rotating at a magnetic rotation speed representing a rotation speed of the first rotating element and a sensor (5) mounted to rotate and adapted to produce from the rotating magnetic field a measurement signal representing the relative rotation speed and/or the relative angular position. The device also has a processor (11) positioned on the static part and intended to acquire the measurement signal. A transmitter is adapted to transmit the measurement signal to the processor from the sensor.

Abstract: Electric motor comprising a rotor and a stator (2), the stator comprising a body (3) forming a frame and a windings assembly (4, 5) housed in slots of the body. The electric motor comprises at least one rod (16, 23) used to connect, to one another, at least two fixed assembled parts of the electric motor, the rod extending into a housing (9) formed in the body over the entire length thereof in order to emerge on each side of the body.

Abstract: A device for measuring a relative rotation speed and/or a relative angular position between a first rotating element (2) and a second rotating element (3). The device includes a structure for generating a magnetic field rotating at a magnetic rotation speed representing a rotation speed of the first rotating element and a sensor (5) mounted to rotate and adapted to produce from the rotating magnetic field a measurement signal representing the relative rotation speed and/or the relative angular position. The device also has a processor (11) positioned on the static part and intended to acquire the measurement signal. A transmitter is adapted to transmit the measurement signal to the processor from the sensor.

Abstract: The invention provides an emergency power network for aircraft, for powering actuator motors (4) connected to the network, the network comprising a power bus (11) adapted to convey three-phase AC power generated by at least one DC/AC converter (12) that is powered by a DC source of the aircraft, the converter being fitted with modulator means for modulating the voltage and/or the frequency of the three-phase power generated thereby.

Abstract: The invention relates to a method of limiting a current idc supplied by a DC power supply, the method comprising: interposing a switching stage between the power supply and a load, the switching stage including a controllable switch in series with a freewheel diode; and periodically controlling the switch so that for each period of duration T, the following averaged quantity 1 T ? ? o t ? i _ · ? t is calculated in which i is a current that is an image of the power supply current idc, the averaged quantity being reset to zero at the beginning of each period, with the switch being caused to be closed so long as said averaged quantity remains below a predetermined current threshold ithresh, and with the switch being caused to be open, otherwise.

Abstract: The invention relates to an actuator including an electrical machine. The electrical actuator (100) comprising: a polyphase machine (101); at least one connection member (143) for powering the actuator from at least one network (146) delivering alternating current; and first and second buses (106, 107) connected in parallel between each connection member (143) and the machine (101) for applying frequency control thereto. Each inverter (111, 131) comprises a plurality of arms each having two controlled switches, each phase of the machine (101) being connected both to the two switches of an arm of the first inverter (111) and also to the two switches of an arm of the second inverter (131). The actuator further comprises controlled connection and disconnection means interposed between each bus (106, 107) and each connection member. The invention is applicable to actuators used in aviation.

Abstract: The invention relates to a method of limiting a current idc supplied by a DC power supply, the method comprising: interposing a switching stage between the power supply and a load, the switching stage including a controllable switch in series with a freewheel diode; and periodically controlling the switch so that for each period of duration T, the following averaged quantity 1 T ? ? o t ? i _ · ? t is calculated in which i is a current that is an image of the power supply current idc, the averaged quantity being reset to zero at the beginning of each period, with the switch being caused to be closed so long as said averaged quantity remains below a predetermined current threshold ithresh, and with the switch being caused to be open, otherwise.

Abstract: The invention relates to a power distribution architecture for an aircraft for powering aircraft electromechanical actuators, the architecture comprising at least one power distribution member for distributing power to such and such an electromechanical actuator connected to the architecture, the architecture receiving power from at least one power supply bus of the aircraft. According to the invention, a DC network of voltage that is variable in controlled manner is interposed between the power supply bus of the aircraft and the power distribution members.

Abstract: The invention relates to an actuator including an electrical machine. The electrical actuator (100) comprising: a polyphase machine (101); at least one connection member (143) for powering the actuator from at least one network (146) delivering alternating current; and first and second buses (106, 107) connected in parallel between each connection member (143) and the machine (101) for applying frequency control thereto. Each inverter (111, 131) comprises a plurality of arms each having two controlled switches, each phase of the machine (101) being connected both to the two switches of an arm of the first inverter (111) and also to the two switches of an arm of the second inverter (131). The actuator further comprises controlled connection and disconnection means interposed between each bus (106, 107) and each connection member. The invention is applicable to actuators used in aviation.

Abstract: The invention provides an emergency power network for aircraft, for powering actuator motors (4) connected to the network, the network comprising a power bus (11) adapted to convey three-phase AC power generated by at least one DC/AC converter (12) that is powered by a DC source of the aircraft, the converter being fitted with modulator means for modulating the voltage and/or the frequency of the three-phase power generated thereby.

Abstract: The invention relates to an aircraft undercarriage including a steerable bottom portion and a steering member suitable for turning the steerable bottom portion in response to a steering order. According to the invention, the steering member comprises a plurality of electromechanical steering actuators each having at least one main electric motor, and the actuators are disposed on the undercarriage so as to enable all of them to co-operate simultaneously with the steerable bottom portion in order to steer it, each of the electro-mechanical steering actuators including controllable coupling means for selectively placing the actuator either in a coupled state in which it is coupled with the steerable bottom portion , in which the main electric motor of the actuator is suitable for causing the steerable bottom portion to turn; or else in an uncoupled state in which it is uncoupled from the steerable bottom portion and in which the main electric motor of the actuator is isolated from the steerable bottom portion.

Abstract: The invention relates to a power distribution architecture for an aircraft for powering aircraft electromechanical actuators, the architecture comprising at least one power distribution member for distributing power to such and such an electromechanical actuator connected to the architecture, the architecture receiving power from at least one power supply bus of the aircraft. According to the invention, a DC network of voltage that is variable in controlled manner is interposed between the power supply bus of the aircraft and the power distribution members.

Abstract: The invention relates to a power distribution architecture for an aircraft for powering aircraft electromechanical actuators, the architecture comprising at least one power distribution member for distributing power to such and such an electromechanical actuator connected to the architecture, the architecture receiving power from at least one power supply bus of the aircraft. According to the invention, a DC network of voltage that is variable in controlled manner is interposed between the power supply bus of the aircraft and the power distribution members.

Abstract: The invention relates to an aircraft undercarriage including a steerable bottom portion and a steering member suitable for turning the steerable bottom portion in response to a steering order.

Abstract: The power supply apparatus (10) comprises an input (12), first and second outputs (14, 16) and conversion circuit (18) for conversion of the electric current which are connected between the input (12) and the outputs (14, 16). The conversion circuit (18) comprises a transformer (20) comprising a primary winding (20A) supplied by the input electric current and first and second secondary windings (20B, 20C) respectively supplying the first and second outputs (14, 16) by way of first and second shaping circuits (22, 24). The first shaping circuit (22) comprises a regulating circuit (48) adapted to act on the electric current feeding the primary winding (20A). The regulating circuit (48) is adapted to effect regulation in dependence on a signal from the first shaping circuit (22). The second shaping circuit (24) comprises autonomous circuitry (86, 88) for regulating the current provided by the second output (16).

Abstract: The power supply apparatus (10) comprises an input (12), first and second outputs (14, 16) and means (18) for conversion of the electric current which are connected between the input (12) and the outputs (14, 16).