ACTIVE VIBRATION SUPPRESSION VIA POWER MINIMIZATION

• US 20100262300A1
• Filed: 03/28/2010
• Published: 10/14/2010
• 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.
• Granted Patent: US 8,538,590 B2
• Time in Patent Office: Days
• 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 system to said actuator system by employing a real electric power consumption of said actuator system as a single control objective function to suppress a vibration of the structure.

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

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 an actuator voltage to said actuator system which forces an actuator current to lead said actuator voltage by a phase angle 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 consumption of said actuator system is obtained from said power supply.

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

, of nearly φ

=+90°

.

8. The system as recited in claim 8, wherein said structure includes a main gearbox of a rotary wing aircraft which interacts with said actuator system to suppress said 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 employing a real electric power consumption of the actuator system as a single control objective function to suppress a vibration of the structure.

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 an actuator voltage to the actuator system to force an 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 an actuator voltage to the actuator system to force an actuator current to lead 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 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 lead 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.