Aircraft motor drive control apparatus and aircraft actuator hydraulic system

Patent metadata

Field	Value
Publication number	US-9670917-B2
Application number	US-201313908790-A
Country	US
Kind code	B2
Filing date	Jun 3, 2013
Priority date	Jun 8, 2012
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A controller that performs pulse width modulation control of a three-phase inverter circuit includes a three-phase modulation voltage command value generation unit, a two-phase modulation voltage command value generation unit, a voltage command switching unit, and a PWM signal output unit. The voltage command switching unit switches a voltage command value to a two-phase modulation voltage command value when a determination value becomes larger than or equal to a first threshold value, and switches the voltage command value to a three-phase modulation voltage command value when the determination value becomes smaller than a second threshold value, which is smaller than the first threshold value.

First claim

What is claimed is:

1. An aircraft motor drive control apparatus for driving a three-phase motor mounted in an aircraft to drive a device installed in the aircraft, and controlling an operational status of the three-phase motor, comprising:
a three-phase inverter circuit that has switching elements and drives the three-phase motor; and a controller that performs pulse width modulation control of the three-phase inverter circuit, the controller comprising: a three-phase modulation voltage command value generation unit that generates a three-phase modulation voltage command value as a voltage command value for specifying a voltage to be applied to the three-phase motor;
a two-phase modulation voltage command value generation unit that generates, as the voltage command value, a two-phase modulation voltage command value for alternately fixing an on/off state of a switching element of one phase in the three-phase inverter circuit, and modulating on/off states of switching elements of the other two phases;
a voltage command switching unit for configuring a setting so as to switch the voltage command value from one of the three-phase modulation voltage command value and the two-phase modulation voltage command value to the other, based on a determination value that is used in determination, which is one of a value of a rotational speed of the three-phase motor and a value of a torque current component of the three-phase motor; and
a PWM signal output unit that generates a PWM signal for performing pulse width modulation control of the three-phase inverter circuit based on the voltage command value generated as the three-phase modulation voltage command value or the two-phase modulation voltage command value, and outputs the PWM signal to the three-phase inverter circuit,
wherein the voltage command switching unit sets the voltage command value to the three-phase modulation voltage command value until the determination value first reaches a predetermined first threshold value after the three-phase motor starts to rotate, switches the voltage command value to the two-phase modulation voltage command value when the determination value becomes larger than or equal to the first threshold value, and switches the voltage command value to the three-phase modulation voltage command value when the determination value becomes smaller than a predetermined second threshold value, which is smaller than the first threshold value, and
the voltage command switching unit switches the voltage command value from the three-phase modulation voltage command value to the two-phase modulation voltage command value at the time when a voltage difference between voltage command values for two of three phases in the three-phase modulation voltage command value becomes zero and when it is determined that a failure does not occur in the aircraft motor drive control apparatus and the three-phase motor, the failure being at least one of occurrence of overcurrent and an abnormal temperature increase.

2. An aircraft actuator hydraulic system that has a hydraulically operated actuator for driving a movable mechanism installed in an aircraft and supplies pressure oil to the actuator, comprising:
the actuator operating as a result of pressure oil being supplied from an aircraft central hydraulic power source, which is a hydraulic power source installed on an airframe side of the aircraft, and driving the movable mechanism;
a backup hydraulic pump capable of supplying pressure oil to the actuator when a loss or degradation of a function of the aircraft central hydraulic power source occurs;
a three-phase motor that drives the backup hydraulic pump; and
an aircraft motor drive control apparatus that drives the three-phase motor mounted in the aircraft to drive the backup hydraulic pump and controls an operational status of the three-phase motor,
wherein the aircraft motor drive control apparatus includes a three-phase inverter circuit that has switching elements and drives the three-phase motor, and a controller that performs pulse width modulation control of the three-phase inverter circuit,
the controller comprising:
a three-phase modulation voltage command value generation unit that generates a three-phase modulation voltage command value as a voltage command value for specifying a voltage to be applied to the three-phase motor;
a two-phase modulation voltage command value generation unit that generates, as the voltage command value, a two-phase modulation voltage command value for alternately fixing an on/off state of a switching element of one phase in the three-phase inverter circuit, and modulating on/off states of switching elements of the other two phases;
a voltage command switching unit for configuring a setting so as to switch the voltage command value from one of the three-phase modulation voltage command value and the two-phase modulation voltage command value to the other, based on a determination value that is used in determination, which is one of a value of a rotational speed of the three-phase motor and a value of a torque current component of the three-phase motor; and
a PWM signal output unit that generates a PWM signal for performing pulse width modulation control of the three-phase inverter circuit based on the voltage command value generated as the three-phase modulation voltage command value or the two-phase modulation voltage command value, and outputs the PWM signal to the three-phase inverter circuit,
wherein the voltage command switching unit sets the voltage command value to the three-phase modulation voltage command value until the determination value first reaches a predetermined first threshold value after the three-phase motor starts to rotate, switches the voltage command value to the two-phase modulation voltage command value when the determination value becomes larger than or equal to the first threshold value, and switches the voltage command value to the three-phase modulation voltage command value when the determination value becomes smaller than a predetermined second threshold value, which is smaller than the first threshold value, and
the voltage command switching unit switches the voltage command value from the three-phase modulation voltage command value to the two-phase modulation voltage command value at the time when a voltage difference between voltage command values for two of three phases in the three-phase modulation voltage command value becomes zero and when it is determined that a failure does not occur in the aircraft motor drive control apparatus and the three-phase motor, the failure being at least one of occurrence of overcurrent and an abnormal temperature increase.

3. The aircraft actuator hydraulic system according to claim 2 ,
wherein the three-phase motor is provided as a synchronous motor using a permanent magnet, and
at the time of an operation to stop the three-phase motor, the aircraft motor drive control apparatus stops an operation to output the PWM signal from the PWM signal output unit to the three-phase inverter circuit, interrupts supply of electric energy from the three-phase inverter circuit to the three-phase motor, and causes the three-phase motor to coast to stop.

4. The aircraft actuator hydraulic system according to claim 2 ,
wherein the backup hydraulic pump is provided as a variable displacement hydraulic pump,
the determination value is a value of a rotational speed of the three-phase motor, and
the aircraft motor drive control apparatus performs control so as to rotate the three-phase motor at a fixed rotational speed after starting rotation of the three-phase motor.

5. The aircraft actuator hydraulic system according to claim 3 ,
wherein the backup hydraulic pump is provided as a variable displacement hydraulic pump,
the determination value is a value of a rotat

Assignees

• Nabtesco Corp

Inventors

• Nakajima Kazushige
• Tsunematsu Tokuji
• Nakagawa Shingo

Classifications

• H02P6/24 Primary

  Arrangements for stopping · CPC title

• H02P23/20

  Controlling the acceleration or deceleration · CPC title

• F04B49/002

  Hydraulic systems to change the pump delivery · CPC title

• F04B17/03 Primary

  driven by electric motors · CPC title

• H02P23/0004

  Control strategies in general, e.g. linear type, e.g. P, PI, PID, using robust control · CPC title