A control device includes: a prediction unit configured to predict the harmonic current at each of prediction points comprised in a predetermined prediction target period after current time, based on control information of the motor in at least a next carrier cycle of the inverter, and a command value determination unit configured to output, to the active filter unit, a current command value for generating a compensation current having a polarity opposite to a polarity of a harmonic current at a prediction point, at a timing corresponding to the prediction point comprised in the next carrier cycle in the prediction target period, based on a prediction result of the prediction unit. Each of the prediction points is provided at a predetermined time interval since start time of the prediction target period. The time interval is longer as the next carrier cycle is longer.

An object of the present invention is to sufficiently suppress a vibration and noise generated in a motor.

A motor control device includes a first inverter circuit and a second inverter circuit of a redundant system, the first inverter circuit and the second inverter circuit controlling a motor, and a control unit that controls the first inverter circuit and the second inverter circuit. The first inverter circuit converts the DC power into the AC power based on a PWM signal generated by using a first carrier signal. The second inverter circuit converts the DC power into the AC power based on a PWM signal generated by using a second carrier signal. The control unit shifts phases of the first carrier signal and the second carrier signal by using, as a reference, pulsation of an electromagnetic force caused by a magnetic circuit of the motor.

A system for providing electric motor control to a plurality of motor loads. The system comprises a plurality of motor controllers that are configurable into different arrangements of motor controllers. The system further comprises a central controller that is operable to individually set a phase and/or frequency of respective PWM carrier signals for the motor controllers, wherein the central controller is configured to set the phase and/or frequency of the PWM carrier signals for the motor controllers within a respective arrangement of motor controllers differently depending on the configuration of the motor controllers within the arrangement.

A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

A control apparatus for driving a three-phase rotary electric machine that generates torque including magnet torque and reluctance torque is provided. AC current supplied to two winding groups of the rotary electric machine have the same amplitude and the mutually different phases defined as 30±60×n[deg]. The control unit calculates d-axis current and q-axis current of 6 (2k+1)th order component superposed on a fundamental wave component on dq coordinate, to reduce a peak of the first order component in the phase current, thereby controlling the three-phase rotary electric machine. The control unit calculates current such that an amplitude of the q-axis current of the 6 (2k+1)th order component is larger than an amplitude of the d-axis current of the 6 (2k+1)th order component.

This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of components, such as a power source for powering an electric motor, of the electric or hybrid aircraft. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of components, such as a power source for powering an electric motor, of the electric or hybrid aircraft. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Technical solutions are described for a motor control system, such as one used in a steering system, the motor control system including multiple controllers. In an example, the motor control system includes a first arbitration module associated with a first controller, and a second arbitration module associated with a second controller. The first arbitration module generates a first arbitrated input signal based on a first input signal directed to the first controller, and a second input signal directed to the second controller. The second arbitration module generates a second arbitrated input signal based on the first input signal and the second input signal. The first controller generates a first control output using the first arbitrated input signal, and the second controller generates a second control output using the second arbitrated input signal.

An underground exploration apparatus 100 that explores underground using electromagnetic waves includes a radar unit 1 for underground exploration including an antenna and a transceiver, three omni-directional movement type wheels 2a to 2c that are rotatably fixed to three wheel shafts arranged at 120 degrees intervals and can move the underground exploration apparatus in any direction by changing rotation directions and rotation speeds of the three wheels, three motors 3a to 3c that rotate the three wheels 2a to 2c in predetermined directions at predetermined speeds, a terminal 10 that controls the radar unit 1 and the three motors 3a to 3c. The terminal 10 includes a calculation unit 23 that calculates an external force applied to the underground exploration apparatus 100 using measurement data measured by three encoders 4a to 4c, three torque sensors 5a to 5c, an acceleration sensor 6, and a gyroscopic sensor 7, and a first control unit 26 that rotates the three motors 3a to 3c according to the external force.

An underground exploration apparatus 100 that explores underground using electromagnetic waves includes a radar unit 1 for underground exploration including an antenna and a transceiver, three omni-directional movement type wheels 2a to 2c that are rotatably fixed to three wheel shafts arranged at 120 degrees intervals and can move the underground exploration apparatus in any direction by changing rotation directions and rotation speeds of the three wheels, three motors 3a to 3c that rotate the three wheels 2a to 2c in predetermined directions at predetermined speeds, a terminal 10 that controls the radar unit 1 and the three motors 3a to 3c. The terminal 10 includes a calculation unit 23 that calculates an external force applied to the underground exploration apparatus 100 using measurement data measured by three encoders 4a to 4c, three torque sensors 5a to 5c, an acceleration sensor 6, and a gyroscopic sensor 7, and a first control unit 26 that rotates the three motors 3a to 3c according to the external force.