System and method of harvesting power with a rotor hub damper

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.