ELECTROMAGNETIC INERTIAL ACTUATOR

• US 20110033310A1
• Filed: 05/05/2010
• Published: 02/10/2011
• Est. Priority Date: 11/04/2008
• Status: Active Grant

• Current Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Original Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Inventors: Janowski, Michael D., Trull, Michael W., Badre-Alam, Askari
• Granted Patent: US 9,404,549 B2
• Time in Patent Office: Days
• US Class Current: 416/500
• CPC Class Codes: F16F 1/185 characterised by shape or design of individual leaves F16F1/22 takes precedence
• CPC Class Codes: F16F 1/20 with layers, e.g. anti-friction layers, or with rollers between the leaves
• CPC Class Codes: F16F 15/03 using magnetic or electromagnetic means F16F9/53, F16F15/005 take precedence
• CPC Class Codes: F16F 3/12 the steel spring being in contact with the rubber spring F16F1/12 takes precedence
• CPC Class Codes: F16F 7/1011 by electromagnetic means
• CPC Class Codes: F16F 7/104 the inertia member being resiliently mounted F16F7/1022 takes precedence
• CPC Class Codes: Y10T 29/49609 Spring making

Abstract

An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base.

Claims

1. An electromagnetic inertial actuator, comprising:

a support base; and

a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part, the parallel arrangement being cantilevered from the support base.

2. The electromagnetic inertial actuator of claim 1, wherein the voice coil motor part comprises a magnet part and a coil part, the magnet part comprising a plurality of permanent magnets, the coil part comprising a coil.

3. The electromagnetic inertial actuator of claim 2, wherein each of the flexure parts has opposing first and second ends, the first ends being coupled to the support base, the second ends being coupled to the magnet part.

4. The electromagnetic inertial actuator of claim 3, wherein the magnet part further comprises ferromagnetic material disposed adjacent to each of the permanent magnets.

5. The electromagnetic inertial actuators of claim 4, wherein each of the permanent magnets is flat.

6. The electromagnetic inertial actuator of claim 4, wherein each of the permanent magnet has a rectangular or triangular cross-section.

7. The electromagnetic inertial actuator of claim 4, wherein the permanent magnets define at least one gap for receiving the coil.

8. The electromagnetic inertial actuator of claim 7, wherein the permanent magnets define two parallel gaps for receiving the coil.

9. The electromagnetic inertial actuator of claim 7, wherein distal ends of the magnet part and coil define an adjustable gap to accommodate arc motion of the parallel arrangement relative to the support base when the electromagnetic inertial actuator is driven.

10. The electromagnetic inertial actuator of claim 7, wherein the first flexure part comprises a first flexure stack and the second flexure part comprises a second flexure stack.

11. The electromagnetic inertial actuator of claim 10, further comprising a first clamp engaged with the first end of the first flexure stack and a second clamp engaged with the first end of the second flexure stack, each of the first clamp and the second clamp being attached to the support base at a plurality of points, thereby coupling first ends of the first and second flexure parts to the support base.

12. The electromagnetic inertial actuator of claim 10, further comprising a yoke coupled to the magnet part and to a second end of the first flexure stack and a second end of the second flexure stack, thereby coupling second ends of the of the flexure parts to the magnet part.

13. The electromagnetic inertial actuator of claim 12, further comprising a third clamp engaged with the second end of the first flexure stack and a fourth clamp engaged with the second end of the second flexure stack, each of the third clamp and the fourth clamp being attached to the yoke at a plurality of points, thereby coupling the second ends of the first and second flexure stacks to the yoke.

14. The electromagnetic inertial actuator of claim 13, wherein the first flexure part comprises a plurality of first flexure stacks and the second flexure part comprises a plurality of second flexure stacks with said yoke in between said first flexure stacks and in between said second flexure stacks.

15. The electromagnetic inertial actuator of claim 10, wherein each of the first flexure stack and second flexure stack comprises a plurality of flexures interleaved with a plurality of shims.

16. The electromagnetic inertial actuator of claim 15, wherein the shims are bonded elastomeric end shims.

17. The electromagnetic inertial actuator of claim 16, wherein the flexures are composite flexures and the bonded elastomeric end shims are fret-inhibiting shims.

18. The electromagnetic inertial actuator of claim 9, wherein the coil is physically grounded to the support base.

19. An aircraft, said aircraft having an aircraft structure and a plurality of troublesome structure vibrations, said aircraft including an electromagnetic inertial actuator support base, said electromagnetic inertial actuator support base being physically grounded to said aircraft structure, said aircraft comprising:

an electromagnetic inertial actuator parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part, the parallel arrangement being cantilevered from the electromagnetic inertial actuator support base.

20. The aircraft of claim 19, wherein said aircraft includes a rotary wing system with at least one rotating blade rotating about a rotation axis, the rotary wing system generating said troublesome structure vibrations.

21. The aircraft of claim 19, wherein said aircraft includes a vibration sensor, said vibration sensor sensing said troublesome structure vibrations, and inertial actuator controller, said vibration sensor outputting vibration sensor signals to said inertial actuator controller wherein said inertial actuator controller electromagnetically drives said electromagnetic inertial actuator parallel arrangement relative to an electromagnetic coil physically grounded to the support base to minimize said troublesome structure vibrations sensed by said vibration sensor.

22. The aircraft of claim 19, wherein the first flexure part comprises a plurality of first flexure stacks and the second flexure part comprises a plurality of second flexure stacks, each of the first flexure stack and second flexure stack comprises a plurality of flexures interleaved with a plurality of shims.

23. The aircraft of claim 22, wherein the shims are bonded elastomeric end shims.

24. The aircraft of claim 23, wherein the flexures are composite flexures and said bonded elastomeric end shims are fret-inhibiting shims.

25. The aircraft of claim 21, wherein the electromagnetic inertial actuator parallel arrangement traces an arc relative to the electromagnetic inertial actuator support base when driven the electromagnetic inertial actuator is driven.

26. A method for controlling troublesome aircraft vibrations of an aircraft, said method including:

providing an electromagnetic inertial actuator, said electromagnetic inertial actuator including a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part, the parallel arrangement being cantilevered from the support base;

physically grounding said electromagnetic inertial actuator support base to an aircraft structure of said aircraft; and

electromagnetically driving said electromagnetic inertial actuator wherein said parallel arrangement traces an arc relative to said support base.

27. A method of making an electromagnetic inertial actuator, comprising:

proving a support base;

providing a coil part;

physically grounding said coil part with said support base;

providing a parallel arrangement of at least a first flexure part, and a voice coil motor part; and

cantilevering said parallel arrangement from the support base.

28. The method of claim 27, wherein providing said voice coil motor part comprises providing a magnet part comprising a plurality of permanent magnets and a coil part comprising a coil.

29. The method of claim 28, wherein said at least first flexure has opposing first and second ends, the first ends being attached to the support base, the second ends being coupled to the magnet part.

30. The method of claim 29, wherein the parallel arrangement is cantilevered such that the parallel arrangement traces an arc relative to the support base when the electromagnetic inertial actuator is driven.

31. The method of claim 30, wherein the distal ends of the magnet part and coil define an adjustable gap to accommodate arc motion of the magnet part relative to the support base.

32. The method of claim 29, wherein each of the permanent magnets is flat.