A method of controlling an overly determined actuator system that has a first number of actuators (α.sub.i) which is greater than a second number of the actuators needed to perform a predetermined physical task. The method includes: automatically controlling the first number of actuators by a control unit (CU) for jointly performing the predetermined physical task; repeatedly checking a functional state of the first number of actuators to detect an actuator failure of any one thereof; in case of any detected actuator failure, generating at least one emergency signal (EM) representative of an adapted physical task to be performed by a remaining number of the actuators. The emergency signal is generated based on kinematics of the actuator system, on known physical capacities at least of the remaining actuators, and optionally on a computational performance model of the actuator system. The adapted physical task includes activating each of the remaining actuators below a predetermined threshold of maximum physical load on a respective actuator and activating the ensemble of remaining actuators in a way to prevent further damage to the actuator system. An emergency control system and an aircraft are also provided.

Systems and methods for voltage regulation of high voltage direct current systems are provided. In certain embodiments, a system includes a generator that generates alternating current (AC) voltage. The system further includes a power converter that converts the AC voltage into regulated direct current (DC) voltage. Also, the system includes a voltage regulator. In additional embodiments, the voltage regulator includes an AC voltage regulator that regulates the AC voltage generated by the generator. Also, the voltage regulator includes a DC voltage regulator that regulates the DC voltage produced by the power converter. Moreover, the voltage regulator includes a regulator selector that selectively activates one of the AC voltage regulator and the DC voltage regulator based on a current from the power converter and at least one of a voltage of the generator and a voltage of the power converter.

An AC to DC conversion device has first and second AC input terminals arranged to be coupled respectively to first and second terminals of a phase of an AC current generator, an H-bridge rectification device comprising two pairs of diodes, each pair being coupled to a respective one of the AC terminals to produce a DC output comprising a rectified back EMF waveform, and a waveform generator. The waveform generator comprises an output coupled to the DC output of the H-bridge rectification device, and is configured to input a unidirectional waveform to the DC output having the same magnitude and fundamental frequency as the rectified back EMF, phase shifted by a predetermined angle relative to the rectified back EMF waveform.

An aerial vehicle and system for automatically detecting an object (e.g., human, pet, or other animal) approaching the aerial vehicle is described. When an approaching object is detected by an object detection component, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the aerial vehicle. For example, if the object is detected entering a safety perimeter of the aerial vehicle, the rotation of a propeller closest to the object may be stopped to avoid harming the object and rotations of remaining propellers may be modified to maintain control and flight of the aerial vehicle.

An actuating device of a pump of a fuel pumping system of an engine, including a motor, a generator, an inverter, a switching member and a control member, the motor including a first rotor coupled to the pump and a first stator including at least one input stator winding, the generator including a second rotor coupled to a drive shaft of the engine, and a second stator including at least one output stator winding, the control member being configured to control the switching member in order to selectively connect each input stator winding: to a corresponding output stator winding if a speed of the engine is higher than or equal to a predetermined speed; to a corresponding output of the inverter, otherwise.

A propulsion channel for aircraft at least one first dual-fed polyphase asynchronous rotating electric machine configured to be mechanically coupled to a turbine engine. The propulsion channel further includes at least one second polyphase rotating electric machine electrically coupled to the first asynchronous rotating electric machine, and a control and storage module configured to control the first polyphase asynchronous rotating electric machine. The module is connected to the first dual-feed polyphase asynchronous rotating electric machine as well as to the at least second polyphase rotating electric machine. The at least second polyphase rotating electric machine includes a polyphase synchronous rotating electric machine with permanent magnet.

A high-integrity electromechanical actuator control system includes a system function controller, a plurality of actuator controllers, and at least one electromechanical actuator. Each actuator controller includes a first controller, a second controller, and a duty cycle computation circuit. The first controller receives digital actuator control commands supplied from two of the function control channels and supplies first digital duty cycle commands. The second controller receives digital actuator control commands supplied from two function control channels and supplies second digital duty cycle commands. The duty cycle computation circuit receives the first digital duty cycle commands and the second digital duty cycle commands, computes an average of the first and second duty cycle commands, and generates pulse width modulated (PWM) commutation control signals based on the computed average.

There is provided an induction machine (100) comprising a rotor (120); a stator (140); and a phase-shift oscillator (160). The stator comprises: a first winding (141); and a second winding (142), arranged at a first angle (101) relative to said first winding. The phase-shift oscillator comprises: a transistor (170), the transistor (170) being a high-electron mobility transistor, HEMT; and a phase-shift network (180). The first winding is connected to a first node (181) of the phase-shift network and wherein the second winding is connected to a second node (182) of the phase-shift network, wherein the phase-shift oscillator is configured to provide a first phase electric signal at the first node and a second phase electric signal at the second node, wherein a difference between the first and second phase corresponds to the first angle. There is also provided an electric aircraft propulsion system comprising the induction machine.

An aircraft provided with a power plant provided with at least one combustion engine mechanically connected to a drive system, the drive system comprising two electric machines each connected to the combustion engine by a kinematic chain, the two electric machines being electrically connected to at least one electrical power source. The aircraft comprises a management system controlling at least a mechanical power or an engine torque delivered by each of the two electric machines as a function of a current operating mode, the management system being configured, during a superior operating mode, to control the two electric machines in order for the two electric machines to deliver different and non-zero mechanical powers or engine torques.

There is provided an induction machine (100) comprising a rotor (120); a stator (140); and a phase-shift oscillator (160). The stator comprises: a first winding (141); and a second winding (142), arranged at a first angle (101) relative to said first winding. The phase-shift oscillator comprises: a transistor (170), the transistor (170) being a high-electron mobility transistor, HEMT; and a phase-shift network (180). The first winding is connected to a first node (181) of the phase-shift network and wherein the second winding is connected to a second node (182) of the phase-shift network, wherein the phase-shift oscillator is configured to provide a first phase electric signal at the first node and a second phase electric signal at the second node, wherein a difference between the first and second phase corresponds to the first angle. There is also provided an electric aircraft propulsion system comprising the induction machine.