A wheel-braking system architecture for an aircraft is provided. The architecture includes a friction brake; an electromechanical actuator associated with a power module connected to a digital communication module by a first driver module; and a controller having both a power supply unit for powering the power module by delivering a power supply voltage (Vc) thereto, and also a control unit connected to the digital communication unit in order to transmit a digital control signal to the digital communication module. The control unit can be connected to the driver unit by an analog wired connection in order to transmit that to a first analog braking order from which the first driver module drives the power module to produce a degraded power supply current for the actuator.

The present invention relates to an electronic control unit (ECU) structure of a brake system, and has an ECU board that is arranged, as an addition, in a symmetric or asymmetric structure in order to form redundancy in preparation for the breakdown of an ECU, and has sensors that are also arranged for implementation of the redundancy, and thus the brake system can be operated even if a part of the ECU breaks down.

The present invention relates to an electronic control unit (ECU) structure of a brake system. An ECU of a brake system, according to the present invention, has a redundancy configuration in which a first control unit, a first cover, and a second control unit are sequentially stacked so that the first control unit and the second control unit are spatially separated by means of the first cover, and thus the second control unit can perform the function of the first control unit without being influenced when the first control unit malfunctions.

Disclosed are a motor control device that can accurately estimate a rotor position based on a neutral point potential even when a load increases, and a brake control device that is driven by the motor control device. The motor control device 3 includes a three-phase synchronous motor 4 including a three-phase winding, an inverter 31 connected to the three-phase winding, a control unit 6 for controlling the inverter based on a rotor position of the three-phase synchronous motor, and a rotational position estimation unit 2 for estimating a rotor position θd based on a neutral point potential Vn of the three-phase winding. The rotational position estimation unit estimates a rotor position selectively using one or more of a plurality of detected values of the neutral point potential according to a pre-estimated value of the rotor position and a voltage application state to the three-phase winding.

A closed-loop stepper motor control system, drive device and automation device, wherein the system comprises a microprocessor (1) compatible with EtherCAT communication protocol functions, an external interface circuit (2) connected to the said microprocessor (1) and communication interface unit (3); the said microprocessor (1) is also connected to a drive circuit (4), current testing circuit (5), as well as an encoder feedback circuit (6); the said communication interface unit (3) is mutually connected to the said microprocessor (1) through the physical layer communication circuit (31); the said microprocessor (1) is also mutually connected to the power supply circuit (7) that provides stable power supply voltage.

A linear actuator (1) comprises a spindle nut arranged to be moved between two end positions on a spindle driven by a DC motor (2). An end stop switch (31) is arranged to be activated when the spindle nut is in an end position. In its activated state, the end stop switch disconnects the motor current and connects a first diode (33) across the DC motor for short circuiting the motor when the current is interrupted. A second diode (32) is connected over the end stop switch for enabling the DC motor to drive the spindle nut out of said end position. An additional component (43) in series with the first diode reduces noise problems caused by motor current circulating through this diode during pulse pauses while the spindle nut is driven out of an end position by a pulse width modulated voltage via a cable from a control box.

A linear actuator (1) comprises a spindle nut arranged to be moved between two end positions on a spindle driven by a DC motor (2). An end stop switch (31) is arranged to be activated when the spindle nut is in an end position. In its activated state, the end stop switch disconnects the motor current and connects a first diode (33) across the DC motor for short circuiting the motor when the current is interrupted. A second diode (32) is connected over the end stop switch for enabling the DC motor to drive the spindle nut out of said end position. An additional component (43) in series with the first diode reduces noise problems caused by motor current circulating through this diode during pulse pauses while the spindle nut is driven out of an end position by a pulse width modulated voltage via a cable from a control box.

The present invention relates to the structure of an electronic control unit (ECU) in a brake system, in which an ECU board that constitutes redundancy is additionally arranged in a symmetrical or asymmetric structure and a plurality of motor position sensors for redundancy are arranged, to prepare for malfunction of the ECU, to thus have an effect of operating the brake system normally by another motor position sensor even if one of the motor position sensors malfunctions.

A system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprises: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.

A system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprises: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.