Semi-active tuned mass damper to eliminate limit-cycle oscillation

Patent metadata

Field	Value
Publication number	US-10539201-B2
Application number	US-201715810793-A
Country	US
Kind code	B2
Filing date	Nov 13, 2017
Priority date	Nov 13, 2017
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

Methods of damping vibrations in a host structure are described. In one embodiment, the vibrations can be damped using a tuned mass damper. The tuned mass damper can include a suspended mass with magnets which is configured to move in response to current being applied to a voice coil. The tuned mass damper can damp vibrations resulting from an external load applied to the host structure, such as an external aerodynamic load. In one embodiment, the tuned mass damper can be mounted within a wind tunnel model undergoing transonic testing. The tuned mass damper can be operated to limit potentially destructive vibrations which can occur during testing.

First claim

What is claimed is:

1. A system comprising:
a host structure configured to receive a periodic external load;
a tuned mass damper, coupled to the host structure, including
a frame;
a voice coil configured to receive current;
a suspended mass including a magnet configured to move in response to the current moving through the voice coil;
a suspension system which couples the suspended mass to the frame; and
a displacement sensor configured to measure an amount of displacement of the suspended mass; and

a control system configured to receive sensor data from the displacement sensor and use the displacement sensor data to control the current in the voice coil to damp structural vibrations associated with the host structure.

2. The system of claim 1 , wherein the host structure is a wing on airplane and the periodic external load is an aerodynamic load that occurs during flight.

3. The system of claim 1 , wherein the host structure is a wind tunnel model and the periodic external load is an aerodynamic load during a wind tunnel test.

4. The system of claim 3 , wherein a speed of sound is exceeded locally on the wind tunnel model during the wind tunnel test.

5. The system of claim 3 , wherein the tuned massed damper is mounted internally in the wind tunnel model.

6. The system of claim 5 , wherein the tuned massed damper is mounted forward of wings of the wind tunnel model.

7. The system of claim 3 , wherein a resonant frequency of the wind tunnel model changes as the aerodynamic load changes and wherein the control system is configured to change movement characteristics of the suspended mass in response to the changes in the resonant frequency of the wind tunnel model.

8. The system of claim 1 , wherein a resonant frequency of the host structure changes as the periodic external load changes and wherein the control system is configured to change movement characteristics of the suspended mass in response to the changes in the resonant frequency of the host structure.

9. The system of claim 1 , wherein the control system further includes an amplifier which supplies the current to the voice coil.

10. The system of claim 1 , wherein the suspension system includes a plurality of elastic flexures which couple the suspended mass to the frame.

11. The system of claim 1 , wherein the suspension system includes one or more springs which couple the suspended mass to the frame.

12. The system of claim 1 , wherein the control system is configured to control the tuned mass damper to vibrate with random frequencies to shake the host structure to determine one or more resonant frequencies of the host structure.

13. The system of claim 1 , wherein the control system is configured to keep a movement of the suspended mass centered around a position.

14. The system of claim 13 , the control system further comprising a proportional integral loop coupled to the displacement sensor configured to keep the movement of the suspended mass centered.

15. An aerodynamic system comprising:
a wind tunnel model configured to receive an aerodynamic load;
a tuned mass damper, coupled to the wind tunnel model and disposed within an interior of the wind tunnel model, including
a frame;
a voice coil configured to receive current;
a suspended mass including a magnet configured to move in response to the current moving through the voice coil;
a suspension system which couples the suspended mass to the frame; and
a displacement sensor configured to measure an amount of displacement of the suspended mass; and

a control system configured to receive sensor data from the displacement sensor and use the displacement sensor data to control the current in the voice coil to damp structural vibrations associated with the wind tunnel model.

16. The aerodynamic system of claim 15 , further comprising a support system coupled to the wind tunnel model configured to support the wind tunnel model within a test chamber of the wind tunnel.

17. The aerodynamic system of claim 15 , wherein the wind tunnel model is an airplane.

18. The aerodynamic system of claim 15 , wherein the tuned mass damper and control system are configured to damp structural vibrations in the wind tunnel model resulting from limit-cycle oscillations at transonic Mach numbers.

19. A method comprising:
operating a wind tunnel including a wind tunnel model mounted to a support system in the wind tunnel to generate air flow over the wind tunnel model wherein the wind tunnel model includes a tuned mass damper mounted within the interior of wind tunnel model; and
controlling the tuned mass damper during wind tunnel tests to damp structural vibrations in the wind tunnel model.

20. The method of claim 19 wherein during the wind tunnel is configured to generate a local Mach number on the wind tunnel model which exceeds a speed of sound.

21. The method of claim 19 further comprising controlling the tuned mass damper to account for changes to a resonant frequency of the model that result from a change of an angle of attack of the wind tunnel model or a change in velocity in the wind tunnel during the operating.

22. The method of claim 19 further comprising prior to operating the wind tunnel to generate the air flow, controlling the tuned mass damper to shake the wind tunnel model to determine resonant frequencies associated with the wind tunnel model and in response adjusting control parameters associated with the tuned mass damper to improve damping at the resonant frequencies.

Assignees

• Boeing Co

Inventors

• Griffin Steven F
• Hovik Stefan P

Classifications

• G01M9/08

  Aerodynamic models · CPC title

• F16F2230/08

  Sensor arrangement · CPC title

• B64C17/00

  Aircraft stabilisation not otherwise provided for · CPC title

• G01M9/04

  Details · CPC title

• F16F7/1011 Primary

  by electromagnetic means · CPC title