Patent ID: 8979078
Filing Date: 2015-03-17
Classification: F16F

Abstract:
1. A vibration damper interposed between an electronic module and a fixed structure of an aircraft nacelle, the vibration damper comprising: a block made of elastic material; a screw fastening the block to said fixed structure, said screw passing through a fastening washer; fastening means to fasten said electronic module to said block; and means for limiting the travel of said fastening means relative to said fastening screw in at least two directions, said limiting means comprising a cup capable of being fastened to said fixed structure and an impactor moving freely inside said cup, the impactor being secured to said electronic module by at least two fasteners and said electronic module fastened between the fastening washer and the impactor, and the at least two fasteners passing through the fastening washer, wherein the impactor is separated from the cup over its radially-outer periphery by a gap “J