Patent ID: 9260185
Filing Date: 2016-02-16
CPC Classification: B64C,F16F

Claim Text:
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.