Patent ID: 9038789
Filing Date: 2015-05-26
Classification: B64D,F16F

Abstract:
1. A vibration damping apparatus in an aircraft having an airframe structure and an aircraft component, comprising: an elastomeric damper; said elastomeric damper comprising an elastomeric material filled with electrically conductive particles; a temperature sensor disposed on said elastomeric damper; a temperature control system configured to heat the elastomeric damper by passing an electric current through the elastomeric damper, wherein as the elastomeric damper is heated by increasing the flow of the electric current, the stiffness of the elastomeric damper is decreased; said temperature sensor providing a feedback control to said control system; wherein the elastomeric damper is interposed in the load path between said aircraft airframe structure and said aircraft component; and, wherein said temperature control system includes an open loop control input module enabling the control system to perform dynamic vibration control to optimize vibration damping.