System and method of harvesting power with a rotor hub damper

Patent metadata

Field	Value
Publication number	US-9260185-B2
Application number	US-201213358046-A
Country	US
Kind code	B2
Filing date	Jan 25, 2012
Priority date	Jan 25, 2012
Publication date	Feb 16, 2016
Grant date	Feb 16, 2016

Abstract

The system and method of the present application relate to a lead/lag damper for a rotorcraft. The lead/lag damper is configured to harvest power from the lead/lag oscillatory motions of rotor blades with an electromagnetic linear motor/generator. Further, the lead/lag damper is configured to treat the lead/lag motions with the electromagnetic linear motor/generator. The system and method is well suited for use in the field of aircraft, in particular, helicopters and other rotary wing aircraft.

First claim

The invention claimed is:

1. A lead/lag damper for an aircraft, comprising:
a first connection member; a second connection member;
a plurality of magnets rigidly associated with the first connection member; an electrically conductive member rigidly associated with the second connection member, the electrically conductive member being located approximate to the plurality of magnets;
a shaft coupled between the first connection member and the plurality of magnets; a housing coupled between the second connection member and the electrically conductive member;
a heat sink located approximate to the electrically conductive member on an exterior of the housing and in thermal communication with the housing; and
a power storage device configured to release stored electrical energy to generate a force between the plurality of magnets and the electrically conductive member, the force being tailored to treat the lead/lag motion during operation of the aircraft;
wherein the power storage device is configured to release the stored electrical energy to a power consuming system associated with a rotor system;
wherein the lead/lag damper is configured such that a lead/lag force causes a translation of the plurality of magnets relative to the electrically conductive member, thereby generating electrical energy.

2. The lead/lag damper according to claim 1 , further comprising:
a first elastomeric bearing attached between the housing and the shaft, the first elastomeric bearing being configured to provide damping when the lead/lag damper is subjected to the lead/lag force.

3. The lead/lag damper according to claim 2 , further comprising:
a second elastomeric bearing attached between the housing and the shaft, the second elastomeric bearing being configured to provide damping when the lead/lag damper is subjected to the lead/lag force.

4. The lead/lag damper according to claim 1 , further comprising:
a circuit coupled to the electrically conductive member.

5. The lead/lag damper according to claim 1 , further comprising:
a resistance in a translation of the plurality of magnets relative to the electrically conductive member, the resistance being configured to provide damping to the lead/lag motion.

6. The lead/lag damper according to claim 5 , wherein the resistance is variable so that the damping to the lead/lag motion can be selectively varied during operation of the aircraft.

7. The lead/lag damper according to claim 1 , wherein the power consuming system is at least one of: a rotor blade de-icing system; an actuated rotor blade flap; and a rotor blade light.

8. The lead/lag damper according to claim 1 , wherein the electrically conductive member is a coil winding.

9. The lead/lag damper according to claim 1 , wherein the electrically conductive member is a plurality of disk members.

10. A system or a rotor hub assembly, the system comprising:
a lead/lag damper having an electromagnetic linear motor and an external heat sink, the electromagnetic linear motor being configured to generate electrical power when subjected to a lead/lag force;
an energy storage device electrically coupled to the electromagnetic linear motor; and a controller associated with a circuitry for selectively changing a resistance between translating components in the electromagnetic linear motor;
wherein the controller is configured to release electrical energy stored by the energy storage device to the electromagnetic linear motor so as to treat the lead/lag force;
wherein the energy storage device is configured to release the stored electrical energy to a power consuming with a rotor system.

11. The system according to claim 10 , wherein the circuitry includes a resistor.

12. The system according to claim 10 , wherein the energy storage device is a battery.

13. The system according to claim 10 , wherein the energy storage device is a capacitor.

14. The system according to claim 10 , wherein the energy storage device is an inductor.

15. A method of using a lead/lag damper in an aircraft, the method comprising:
generating an electrical energy by converting a mechanical lead/lag motion to the electrical energy with an electromagnetic linear motor in the lead/lag damper;
storing the electrical energy generated by the electromagnetic linear motor;
powering a system in a rotating portion of a rotor assembly with the stored electrical energy;
treating the mechanical lead/lag motion by using the stored electrical energy to generate a reactive force in the electromagnetic linear motor; and
dissipating heat produced by the lead/lag damper through an external heat sink.

16. The method according to claim 15 , wherein the step of treating the mechanical lead/lag motion further comprises varying the reactive force as a rate of revolution of the rotating portion varies.

17. The method according to claim 15 , wherein the step of treating the mechanical lead/lag motion further comprises varying the reactive force as an ambient condition varies.

18. The method according to claim 17 , wherein the ambient condition is at least one of:
an ambient temperature; and
an ambient altitude.

Assignees

• Covington Charles Eric
• Yuce Mithat
• Popelka David A
• Stamps Frank B
• Textron Innovations Inc

Inventors

• Covington Charles Eric
• Yuce Mithat
• Popelka David A
• Stamps Frank B

Classifications

• B64C27/51 Primary

  Damping of blade movements · CPC title

• F16F2230/16

  used in a strut, basically rigid · CPC title

• F16F15/022

  using dampers and springs in combination · CPC title

• F16F15/03

  using {magnetic or} electromagnetic means (F16F9/53, {F16F15/005} take precedence) · CPC title