System and method for controlling aircraft wing flap motion

Patent metadata

Field	Value
Publication number	US-10315753-B2
Application number	US-201615084076-A
Country	US
Kind code	B2
Filing date	Mar 29, 2016
Priority date	Mar 29, 2016
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

A system and method for controlling one or more flaps of a wing of an aircraft include a first flap moveably secured to a first wing of the aircraft. The first flap is moveable between an extended position and a retracted position. First and second actuators are coupled to the first flap. A flap control unit is in communication with the first and second actuators. The flap control unit is configured to operate the first and second actuators to move the first flap between retracted and extended positions, monitor a first electrical signal provided to the first actuator, monitor a second electrical signal provided to the second actuator, and determine that the first and second actuators are synchronized by monitoring the first and second electrical signals.

First claim

What is claimed is:

1. A system for controlling one or more flaps of a wing of an aircraft, the system comprising:
a first flap moveably secured to a first wing of the aircraft, the first flap being moveable between an extended position and a retracted position;
a first actuator coupled to the first flap;
a second actuator coupled to the first flap; and
a flap control unit in communication with the first and second actuators, wherein the flap control unit is configured to:
operate the first and second actuators to move the first flap between retracted and extended positions;
monitor a first electrical signal provided to the first actuator;
monitor a second electrical signal provided to the second actuator; and
determine that the first and second actuators are synchronized by monitoring the first and second electrical signals.

2. The system of claim 1 , wherein the flap control unit is configured to determine that the first and second actuators are synchronized when the first and second electrical signals are equal.

3. The system of claim 1 , wherein each of the first and second electrical signals is one of a voltage or a current.

4. The system of claim 1 , wherein the flap control unit determines that the first and second actuators are synchronized without the use of a sensor.

5. The system of claim 1 , wherein the first actuator is a first stepper motor, and wherein the second actuator is a second stepper motor.

6. The system of claim 1 , wherein the first and second actuators are not mechanically linked together through a linking device.

7. The system of claim 1 , wherein the first flap is a leading edge flap or a trailing edge flap.

8. The system of claim 1 , further comprising:
a second flap moveably secured to the first wing of the aircraft, the second flap being moveable between an extended position and a retracted position;
a third actuator coupled to the second flap;
a fourth actuator coupled to the second flap,
the flap control unit is further configured to:
operate the third and fourth actuators to move the second flap between retracted and extended positions;
monitor a third electrical signal provided to the third actuator;
monitor a fourth electrical signal provided to the fourth actuator; and
determine that the third and fourth actuators are synchronized by monitoring the third and fourth electrical signals.

9. The system of claim 1 , further comprising at least one power bus coupled to the first and second actuators, wherein the at least one power bus provides power signals to the first and second actuators from a source of power.

10. The system of claim 1 , further comprising at least one control bus that couples the flap control unit to the first and second actuators, wherein the flap control unit provides control signals to the first and second actuators through the at least one control bus.

11. A method of controlling one or more flaps of a wing of an aircraft, the method comprising:
receiving a command signal that is input by an operator of the aircraft;
operating first and second actuators coupled to a first flap of the wing of the aircraft based on the command signal to move the first flap between retracted and extended positions;
monitoring a first electrical signal provided to the first actuator;
monitoring a second electrical signal provided to the second actuator; and
determining that the first and second actuators are synchronized based on the monitoring operations, wherein the determining operation comprises determining that the first and second actuators are synchronized when the first and second electrical signals are equal.

12. The method of claim 11 , wherein each of the first and second electrical signals is one of a voltage or a current.

13. The method of claim 11 , wherein the monitoring and determining operation occur without the use of a sensor.

14. The method of claim 11 , wherein the first actuator is a first stepper motor, and wherein the second actuator is a second stepper motor.

15. The method of claim 11 , wherein the first and second actuators are not mechanically linked together through a linking device.

16. The method of claim 11 , wherein the first flap is a leading edge flap or a trailing edge flap.

17. The method of claim 11 , further comprising:
operating third and fourth actuators coupled to a second flap of the wing of the aircraft based on the command signal to move the second flap between retracted and extended positions;
monitoring a third electrical signal provided to the third actuator;
monitoring a fourth electrical signal provided to the fourth actuator; and
determining that the third and fourth actuators are synchronized based on the monitoring operations.

18. The method of claim 11 , further comprising:
providing power signals to the first and second actuators through at least one power bus; and
providing control signals to the first and second actuators through at least one control bus.

19. A system for controlling one or more flaps of a wing of an aircraft, the system comprising:
a first flap moveably secured to a first wing of the aircraft, the first flap being moveable between an extended position and a retracted position;
a second flap moveably secured to the first wing of the aircraft, the second flap being moveable between an extended position and a retracted position;
a first stepper motor coupled to the first flap;
a second stepper motor coupled to the first flap, wherein the first and second stepper motors are not mechanically linked through a linking device;
a third stepper motor coupled to the second flap;
a fourth stepper motor coupled to the second flap; and
a flap control unit in communication with the first and second stepper motors, wherein the flap control unit is configured to:
operate the first and second stepper motors to move the first flap between retracted and extended positions;
operate the third and fourth stepper motors to move the second flap between retracted and extended positions;
monitor a first electrical signal provided to the first stepper motor;
monitor a second electrical signal provided to the second stepper motor;
monitor a third electrical signal provided to the third stepper motor;
monitor a fourth electrical signal provided to the fourth stepper motor;
determine that the first and second stepper motors are synchronized when the first and second electrical signals are equal, wherein the flap control unit determines that the first and second stepper motors are synchronized without the use of a sensor; and
determine that the third and fourth actuators are synchronized by monitoring the third and fourth electrical signals.

20. The system of claim 19 , further comprising:
at least one power bus coupled to the first, second, third, and fourth stepper motors, wherein the at least one power bus provides power signals to the first, second, third, and fourth actuators from a source of power; and
at least one control bus that couples the flap control unit to the first, second, third, and fourth stepper motors, wherein the flap control unit provides control signals to the first, second, third and fourth stepper motors through the at least one control bus.

Assignees

• Boeing Co

Inventors

• Mccormick Patrick
• Peck James L

Classifications

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B64D2045/001

  for indicating symmetry of flaps deflection · CPC title

• B64C13/50 Primary

  using electrical energy · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C13/0425

  for actuating trailing or leading edge flaps, air brakes or spoilers · CPC title