AIRCRAFT WITH TRANSIENT-DISCRIMINATING PROPELLER BALANCING SYSTEM

• US 20090306829A1
• Filed: 10/11/2007
• Published: 12/10/2009
• Est. Priority Date: 10/11/2006
• Status: Active Grant

• Current Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Original Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Inventors: Hildebrand, Steve F., Altieri, Russell E., Winzenz, Wayne
• Granted Patent: US 8,360,728 B2
• Time in Patent Office: Days
• US Class Current: 700/279
• CPC Class Codes: B64C 11/008 characterised by vibration absorbing or balancing means
• CPC Class Codes: G01M 1/36 by adjusting position of masses built-in the body to be tested

Abstract

A system for balancing an aircraft propeller system receives a vibration signal from the aircraft propeller system and determines whether the vibration signal indicates a transient vibration condition. If it is determined that the vibration signal does not indicate a transient condition, the system enables a balance correction controller. The controller generates a balance correction signal based on the vibration signal, and balances the aircraft propeller system in response to the balance correction signal if the balance correction controller is enabled.

Claims

1. A method of balancing an aircraft propeller system comprising:

receiving a vibration signal from the aircraft propeller system;

determining whether the vibration signal represents a transient vibration condition;

enabling a balance correction controller if it is determined that the vibration signal does not represent a transient vibration condition;

generating a balance correction signal at the balance correction controller based on the vibration signal; and

balancing the aircraft propeller system in response to the balance correction signal.

2. The method of claim 1 wherein the balance correction signal is communicated to an automatic balance correction mechanism the balance correction mechanism comprising at least one balance correction rotor, and the balance correction signal causes the rotor to move to balance the aircraft propeller system.

3. The method of claim 1 wherein determining whether the vibration signal represents a transient vibration condition includes monitoring an aircraft operation environmental signal.

4. The method of claim 1, wherein said determining whether the vibration signal represents a transient condition comprises:

low pass filtering the vibration signal based on a cutoff frequency;

calculating a difference of the vibration signal and the filtered vibration signal;

and comparing the difference to a predetermined threshold.

5. The method of claim 4, wherein said determining whether the vibration signal represents a transient condition further comprises:

determining if an absolute value of the difference is less then the predetermined threshold over a finite time period.

6. An aircraft with an aircraft propeller system and a propeller balancing system comprising:

a balance correction mechanism coupled to the aircraft propeller system;

a vibration sensor coupled to the aircraft propeller system for generating a vibration signal;

a transient detector coupled to said vibration sensor; and

a balance controller coupled to said balance correction mechanism, said vibration sensor, and said transient detector;

wherein said transient detector enables said balance controller when the vibration signal does not indicate a transient condition.

7. The balancing system of claim 6, wherein said balance controller, if enabled, is adapted to generate a balance correction signal based on the vibration signal, and wherein said balance correction signal activates said balance correction mechanism to balance the aircraft propeller system.

8. The balancing system of claim 7, wherein said balance correction mechanism comprises a plurality of adjustable rotors and at least one permanent magnet.

9. The balancing system of claim 8, wherein said balance correction mechanism comprises at least two solid mass imbalance rotors each having an imbalance mass concentration.

10. The balancing system of claim 6, wherein said transient detector is adapted to determine that the vibration signal does not represent a transient condition by:

low pass filtering the vibration signal based on a cutoff frequency;

calculating a difference of the vibration signal and the filtered vibration signal; and

comparing the difference with a predetermined threshold.

11. The balancing system of claim 10, wherein said transient detector is adapted to further determine that the vibration signal does not represent a transient condition by:

determining if an absolute value of the difference is less then the predetermined threshold over a finite period of time.

12. An aircraft with a power source, said power source including a rotating member, said aircraft comprising a balancing system with a balance correction mechanism coupled to the rotating member, said balancing system comprising:

a vibration sensor for generating a vibration signal;

a transient detector coupled to said vibration sensor; and

a balance controller coupled to said vibration sensor;

wherein said transient detector enables said balance controller if the transient detector determines that the vibration signal does not represent a transient vibration condition.

13. The aircraft of claim 12, wherein said balance controller, if enabled, is adapted to generate a balance correction signal based on the vibration signal, and wherein said balance correction signal causes at least a portion of said balance correction mechanism to move to balance the rotating member.

14. The aircraft of claim 13, wherein said balance correction mechanism comprises a plurality of rotors and at least one magnet.

15. The aircraft of claim 14, wherein said balance correction mechanism comprises at least two solid mass imbalance rotors each having an imbalance mass concentration.

16. The aircraft of claim 12, wherein said transient detector is adapted to

determine that the vibration signal does not represent a transient condition by:

low pass filtering the vibration signal based on a cutoff frequency;

calculating a difference of the vibration signal and the filtered vibration signal; and

comparing the difference with a predetermined threshold.

17. The aircraft of claim 16, wherein said transient detector is adapted to determine that the vibration signal does not represent a transient condition by:

determining if an absolute value of the difference is less then the predetermined threshold over a predetermined time duration.

18. A vibration control system for a machine with a rotating member, said vibration control system including an electromagnetically actuated correction mechanism coupled to the machine, said vibration control system comprising:

a vibration sensor for generating a vibration signal;

a transient detector coupled to said vibration sensor; and

a controller coupled to said vibration sensor;

wherein said transient detector enables said controller if the transient detector determines that the vibration signal does not represent a transient vibration condition.

19. The vibration control system of claim 18, wherein said controller, if enabled, is adapted to generate a correction signal based on the vibration signal, and wherein said correction signal causes at least a portion of the electromagnetically actuated correction mechanism to move to reduce a detected vibration.

20. The vibration control system of claim 19, wherein said correction mechanism comprises a plurality of rotors and at least one magnet.

21. The vibration control system of claim 18, wherein said transient detector is adapted to determine that the vibration signal does not represent a transient condition by:

low pass filtering the vibration signal based on a cutoff frequency;

calculating a difference of the vibration signal and the filtered vibration signal;

and comparing the difference with a predetermined threshold.

22. A method of controlling an aircraft propeller vibration, said method comprising:

providing an electromagnetically actuated vibration correction mechanism, receiving an aircraft propeller vibration signal;

determining whether the propeller vibration signal represents a transient vibration condition;

enabling a controller if it is determined that the vibration signal does not represent a transient vibration condition;

generating a balance correction signal at the enabled controller based on the vibration signal; and

using the balance correction signal to electromagnetically actuate said correction mechanism if the controller is enabled.

23. The method of claim 22 further comprising sending the balance correction signal to the correction mechanism.

24. The method of claim 22, wherein said determining whether the vibration signal represents a transient condition comprises:

low pass filtering the vibration signal based on a cutoff frequency;

calculating a difference of the vibration signal and the filtered vibration signal; and

comparing the difference with a predetermined threshold.

25. The method of claim 24, wherein said determining whether the vibration signal represents a transient condition further comprises:

determining if an absolute value of the difference is less then the predetermined threshold over a predetermined time duration.