Active vibration suppression via power minimization

• US 8,538,590 B2
• Filed: 03/28/2010
• Issued: 09/17/2013
• Est. Priority Date: 04/13/2009
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Sun, Fanping, Chaudhry, Zaffir A.
• Primary Examiner(s): ORTIZ RODRIGUEZ, CARLOS R
• Application Number:
  US12/748,426
• Publication Number:
  US 20100262300A1
• Time in Patent Office: 1,269 Days
• Field of Search: 700/275, 700/280, 700/286, 700/297
• US Class Current: 700/280
• CPC Class Codes: B64C 2027/002 mounted between the rotor drive and the fuselage
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: F16F 15/002 characterised by the control method or circuitry control of mechanical oscillations per se G05D19/00

Abstract

A vibration suppressor system includes a control system operable to control power from a power system to an actuator system in response to a minimal actuation power algorithm. The minimal actuation power algorithm employs a real electric power consumption of the actuator system as a single control objective function to suppress a vibration of the structure.

Claims

1. A vibration suppressor system comprising:

an actuator system for applying a force to a structure;

a power supply operable to power said actuator system; and

a control system operable to control power from said power supply to said actuator system using a power algorithm configured to suppress a vibration of said structure independently from a vibratory feedback of the structure and based on a function that has a single control objective and that receives real electric power of said actuator system as input,

wherein said power algorithm is configured to regulate an actuator voltage that is supplied to said actuator system from the power supply based on a phase angle difference between an actuator current and said actuator voltage,

wherein said single control objective comprises a regulation of said actuator current to lead or lag said actuator voltage by the phase angle difference,

wherein said power algorithm is further configured to cause said actuator current to lead or lag said actuator voltage by the phase angle difference.

2. The system as recited in claim 1, wherein said actuator system includes a capacitive actuator.

3. The system as recited in claim 1, wherein said single control objective function includes regulation of said actuator voltage to said actuator system which forces said actuator current to lead said actuator voltage by a phase angle, φ

, of nearly φ

=+90°

.

4. The system as recited in claim 1, wherein said actuator system includes an inductive actuator.

5. The system as recited in claim 4, wherein said single control objective function includes regulation of said actuator voltage to said actuator system which forces said actuator current to lag said actuator voltage by a phase angle, φ

, of nearly φ

=−

90°

.

6. The system as recited in claim 1, wherein said control system minimizes the real electric power into said actuator system.

7. The system as recited in claim 6, wherein said real electric power of said actuator system is obtained from said power supply.

8. The system as recited in claim 1, wherein said structure includes a main gearbox of a rotary wing aircraft which interacts with said actuator system to suppress a vibration of said main gearbox.

9. A method of vibration suppression comprising:

controlling power to an actuator system for applying a force to a structure by using a power algorithm that suppresses a vibration of said structure independently from a vibratory feedback of the structure and suppresses the vibration based on function that has a single control objective and that receives real electric power of said actuator system as input,

wherein the power algorithm regulates an actuator voltage that is supplied to the actuator system from the power supply based on a phase angle difference between an actuator current and the actuator voltage,

wherein the single control objective comprises a regulation of the actuator current to lead or lag the actuator voltage by the phase angle difference,

wherein the power algorithm causes the actuator current to lead or lag the actuator voltage by the phase angle difference.

10. The method as recited in claim 9, further comprising:

minimizing the real electric power into the actuator system.

11. The method as recited in claim 9, further comprising:

regulation of said actuator voltage to the actuator system to force said actuator current to lead the actuator voltage by a phase angle of nearly φ

=+90°

.

12. The method as recited in claim 9, further comprising:

regulation of said actuator voltage to the actuator system to force said actuator current to lag the actuator voltage by a phase angle of nearly φ

=−

90°

.

13. The method as recited in claim 9, further comprising:

sweeping a control voltage amplitude from zero to an optimal amplitude such that a real power changes from a negative value to zero as the single control objective function.

14. The method as recited in claim 13, further comprising:

identifying a current phase lead to voltage change from 180 degrees to 90 degrees for a capacitive actuator system.

15. The method as recited in claim 13, further comprising:

identifying a current phase lag to voltage change from 180 degrees to −

90 degrees for an inductive actuator system.

16. The method as recited in claim 9, further comprising:

controlling a control actuator voltage amplitude to the actuator system to change a real and imaginary power input to the actuator system.