Abstract: A starting/generating system for an aircraft turbine engine, the starting/generating system comprising at least one brushless drive motor/generator, at least one control module and at least one power module, the power module being configured to supply/receive electric power from the brushless drive motor/generator, the control module being connected to the brushless drive motor/generator by a control cable in order to control its operation, in which system the power module is configured to be mounted in the housing of the non-pressurized zone so as to be located adjacent to the brushless drive motor/generator and the control module is configured to be mounted in a pressurized zone of the aircraft, the control module being connected to the power module by a two-way communication cable in order to control its operation.

Abstract: An electrical machine for use in an aircraft, including a rotor. The rotor includes a plurality of rotor poles, and a stator including a plurality of phases. Each respective phase occupies at least one elementary block and the at least one elementary block of each phase includes a set of conductors of the respective phase wound around a plurality of slots of the respective elementary block in a concentrated winding configuration. A mechanical shift angle between the respective concentrated windings of each pair of adjacent elementary blocks is greater than a rotor pole pitch. The rotor pole pitch is an angle between adjacent poles of the rotor.

Abstract: A propulsion and non-propulsive electrical generation system for an aircraft having at least one turbomachine and at least two pairs of rotors, the rotors of the same pair of rotors being symmetrically opposite on the aircraft with respect to the same center of symmetry, at least four motors each driving a rotor, at least one generator coupled to a turbomachine, an even number of power lines and at most equal to the number of rotors, each power line having at least one propulsion branch coupled to a motor, a battery coupled at the output to the propulsion branch, and an AC-DC converter coupled between an output of a generator and the propulsion branch.

Abstract: A propulsion and non-propulsive electrical generation system for an aircraft having at least one turbomachine and at least two pairs of rotors, the rotors of the same pair of rotors being symmetrically opposite on the aircraft with respect to the same center of symmetry, at least four motors each driving a rotor, at least one generator coupled to a turbomachine, an even number of power lines and at most equal to the number of rotors, each power line having at least one propulsion branch coupled to a motor, a battery coupled at the output to the propulsion branch, and an AC-DC converter coupled between an output of a generator and the propulsion branch.

Abstract: A starting/generating system for an aircraft turbine engine, the starting/generating system comprising at least one brushless drive motor/generator, at least one control module and at least one power module, the power module being configured to supply/receive electric power from the brushless drive motor/generator, the control module being connected to the brushless drive motor/generator by a control cable in order to control its operation, in which system the power module is configured to be mounted in the housing of the non-pressurized zone so as to be located adjacent to the brushless drive motor/generator and the control module is configured to be mounted in a pressurized zone of the aircraft, the control module being connected to the power module by a two-way communication cable in order to control its operation.

Abstract: A power supply and control system of a plurality of electrically controlled actuators on board an aircraft and an actuation system for an aircraft including the electrically controlled actuators and a system for their power supply and their control. The system includes: P electrical power supply units each capable of generating a power signal for powering an actuator, Q control units, each configured for executing at least one servo control algorithm driving a power module of an actuator, and a network communication module connecting each control unit to a computer network for communicating with each actuator.

Abstract: An actuating system for an aircraft having an electromechanical actuator (25) comprising a non-volatile memory (60) wherein stored data (61) including configuration data (62) specific to the electromechanical actuator is stored. The system also includes a control unit (22) using the configuration data to implement a servo-control loop, the output signal of which is a digital signal controlling the electric motor of the electromechanical actuator and at least one digital transmission channel (50) connecting the control unit and the electromechanical actuator.

Abstract: Actuating system for an aircraft comprising: an electromechanical actuator (25) comprising a non-volatile memory (60) wherein stored data (61) including configuration data (62) specific to the electromechanical actuator is stored; a control unit (22) using the configuration data to implement a servo-control loop, the output signal of which is a digital signal controlling the electric motor of the electromechanical actuator; at least one digital transmission channel (50) connecting the control unit and the electromechanical actuator.

Abstract: An electromechanical actuator comprising an actuator member and an electric motor (2) adapted to drive the actuator member. The electric motor (2) comprises a rotor portion (4), a stator portion (5) comprising a yoke-forming body (9) and a set of coils received in slots (12) in the body (9), and at least one electrical module (17). The electrical module is adapted to generate an electrical power supply current (Ia) for the electric motor (2), which current flows in the set of coils. The electrical module (17) is carried by the body (9).

Abstract: A method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated. The method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator.

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: An electromechanical actuator comprising an actuator member and an electric motor (2) adapted to drive the actuator member. The electric motor (2) comprises a rotor portion (4), a stator portion (5) comprising a yoke-forming body (9) and a set of coils received in slots (12) in the body (9), and at least one electrical module (17). The electrical module is adapted to generate an electrical power supply current (Ia) for the electric motor (2), which current flows in the set of coils. The electrical module (17) is carried by the body (9).

Abstract: A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

Abstract: The invention relates to a device for braking/driving an aircraft wheel mounted to rotate on an undercarriage axle, the device comprising: a stack of disks comprising disks that are constrained in rotation with the wheel and that alternate with disks that are constrained in rotation with a torsion tube; a support member mounted to rotate on the axle and constrained in rotation with the torsion tube; braking actuators carried by the support member for selectively pressing the disks together; and a drive member for selectively driving the support member in rotation; the support member carrying a secondary of a transformer having a primary arranged facing the support member while being stationary in rotation, the secondary being electrically connected to the actuators and the primary being adapted to being connected to a non-DC voltage source.

Abstract: The invention provides an aircraft wheel-and-brake set, the wheel including a rim mounted to rotate on an axle of the aircraft about an axis of rotation, and the brake including a stack of disks extending into the rim in service, and a support carrying brake actuators facing the stack of disks in order to selectively press said disks together, wherein the support carries at least one rotary drive member for driving the wheel in rotation, which drive member is carried in such a manner that it extends outside said wheel.

Abstract: The invention relates to a method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated, characterized in that the method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator.

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: A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

Abstract: The invention relates to a device for braking/driving an aircraft wheel mounted tO rotate on an undercarriage axle, the device comprising: a stack of disks comprising disks that are constrained in rotation with the wheel and that alternate with disks that are constrained in rotation with a torsion tube; a support member mounted to rotate on the axle and constrained in rotation with the torsion tube; braking actuators carried by the support member for selectively pressing the disks together; and a drive member for selectively driving the support member in rotation; the support member carrying a secondary of a transformer having a primary arranged facing the support member while being stationary in rotation, the secondary being electrically connected to the actuators and the primary being adapted to being connected to a non-DC voltage source.

Abstract: The invention provides an aircraft wheel-and-brake set, the wheel including a rim mounted to rotate on an axle of the aircraft about an axis of rotation, and the brake including a stack of disks extending into the rim in service, and a support carrying brake actuators facing the stack of disks in order to selectively press said disks together, wherein the support carries at least one rotary drive member for driving the wheel in rotation, which drive member is carried in such a manner that it extends outside said wheel.