Patent ID: 8177202
Filing Date: 2012-05-15
Classification: B64C,F16F

Abstract:
1. A damping device intended to form a drag-mode damper for a helicopter blade, comprising: a radially external frame intended to be coupled to a first rotating element and a radially internal element mounted coaxially to the frame and intended to be coupled to a second rotating element, the frame and the internal element each having a symmetry of revolution; at least one elastomer damper of annular cross section mounted fixedly to the frame and to the internal element; and a working chamber which is bounded by the frame and by the elastomer damper and which communicates with a compensation chamber bounded and enclosed by a highly deformable flexible member mounted coaxially to the internal element, these chambers being filled with a hydraulic fluid, wherein the working chamber is formed at a first end of the device and communicates with the compensation chamber via a porous structure surmounting an end opening of the flexible member, which member is mounted inside the internal element such that, in response to relative movements of the frame and the internal element, the variation in volume of the working chamber forces the fluid to flow across this porous structure in order for the compensation chamber to compensate for this variation in volume.