Method to measure aircraft high-lift system brake response time

Patent metadata

Field	Value
Publication number	US-10336437-B2
Application number	US-201715587546-A
Country	US
Kind code	B2
Filing date	May 5, 2017
Priority date	May 5, 2017
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

A braking test for a high lift system. The system including a plurality of high lift surfaces movably arranged at a wing, a plurality of drive stations coupled with the high lift surfaces via a transmission shaft, a power drive unit coupled with the transmission shaft including an electric motor operably coupled with a brake, and a control unit operably coupled to the power drive unit. The control unit executing a method for testing the brake, including actuating an electric motor, acquiring a sensor output of a sensor coupled during the actuating of the motor and determining a motion of the motor, activating a selected brake under test, measuring an elapsed time until the brake has arrested the motion, and determining if the elapsed time is less than a threshold. Generating a brake failure signal for the selected brake if the elapsed time exceeds the threshold.

First claim

What is claimed is:

1. A method for testing a component in a high lift system of an aircraft, the high lift system comprising a central power drive unit for moving high lift surfaces arranged at a wing through providing rotational power by means of a transmission shaft to a plurality of drive stations operably coupled with the high lift surfaces; which power drive unit is operatively coupled to a controller and comprises at least one electric motor coupled with a selectively activated brake; the method comprising:
actuating the at least one electric motor for a predetermined period of time with all brakes in the system deactivated;
acquiring a sensor output of a sensor coupled with the controller during the actuating of the motor and determining a motion of at least one of the motor and the high lift surfaces based on the acquired sensor output;
activating a selected brake under test:
measuring an elapsed time until the selected brake has arrested the motion of at least one of the motor and the high lift surfaces;
determining if the that the elapsed time is less than a predetermined threshold value; and
generating a brake failure signal for the selected brake if the elapsed time exceeds the predetermined threshold value.

2. The method of claim 1 , further comprising moving the high lift surfaces to a selected position before activating the selected brake.

3. The method of claim 2 , wherein the selected position is at least one of a fully extended position and a neutral position.

4. The method of claim 1 , further comprising conducting at least one of a system functional test, power on reset built in test, and an initiated built in test.

5. The method of claim 1 , further comprising at least one of ensuring established preconditions for conducting the testing have been satisfied defining maximum torque for a selected brake under test, and releasing all system brakes.

6. The method of claim 1 , wherein the activating the brake is conducted a selected duration after the actuating the at least one electric motor.

7. The method of claim 6 , wherein the selected duration is at least long enough to ensure the at least one electric motor is moving at full speed.

8. The method of claim 1 , wherein the acquiring includes measuring at least one of a displacement and a speed of the high lift surface based on the actuation of the motor.

9. The method of claim 1 , wherein the predetermined threshold is application specific depending on the system, the actuator, and the brake under test.

10. The method of claim 1 further including repeating the method for another brake in the high lift system.

11. The method of claim 1 , wherein the method is conducted after landing of the aircraft while at least one of the high lift surfaces are in an extended position and the high lift surfaces are moved into a neutral position.

12. A high lift system of an aircraft, comprising:
a plurality of high lift surfaces movably arranged at a wing;
a plurality of drive stations coupled with the high lift surfaces;
a transmission shaft coupled with the plurality of drive stations;
a power drive unit coupled with the transmission shaft for moving the high lift surfaces, the power drive unit comprising at least one electric motor operably coupled and with a brake; and
a control unit, the control unit operably coupled to the power drive unit, the control unit configured to execute a method for testing a component in a high lift system of an aircraft, the method including: actuating the at least one electric motor for a predetermined period of time with brakes deactivated, acquiring a sensor output of a sensor coupled with the controller during the actuating of the motor and determining a motion of at least one of the motor and the high lift surfaces based on the acquired sensor output, activating a selected brake under test, measuring an elapsed time until the brake has arrested the motion, and determining if the elapsed time is less than a predetermined threshold value, and generating a brake failure signal for the selected brake if the elapsed time exceeds the predetermined threshold value.

13. The high lift system of claim 12 , further comprising the controller executing a previous step of moving the high lift surfaces to a selected position before activating the at least one brake.

14. The high lift system of claim 12 , further comprising the controller executing a step of conducting at least one of a system functional test, power on reset built in test, and an initiated built in test.

15. The high lift system of claim 12 , wherein the activating the brake is conducted a selected duration after the actuating the at least one electric motor.

16. The high lift system of claim 15 , wherein the selected duration is at least long enough to ensure the at least one electric motor is moving at full speed.

17. The high lift system of claim 12 , wherein the acquiring includes measuring at least one of a displacement and a speed of the high lift surface based on the actuation by the motor.

18. The high lift system of claim 12 , wherein the predetermined threshold is application specific depending on the system, the actuator, and the brake under test.

19. The high lift system of claim 12 , wherein the method is conducted after landing of the aircraft while at least one of the high lift surfaces are in an extended position and the high lift surfaces are moved into a neutral position.

20. The high lift system of claim 12 , wherein the high lift surfaces are at least one of trailing edge flaps and leading edge slats.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Mayer Timothy Michael
• Pérez Artemio
• Barger Victor

Classifications

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• H02K11/21

  Devices for sensing speed or position, or actuated thereby (specially adapted for machines having non-mechanical commutating devices H02K29/06, H02K29/14) · CPC title

• H02K7/102

  with friction brakes · CPC title

• H02P29/04

  by means of a separate brake · CPC title

• B60T2270/406

  Test-mode; Self-diagnosis · CPC title