公开(公告)号：EP3705744A1

公开(公告)日：2020-09-09

申请号：EP19180627.2

申请日：2019-06-17

Applicant: Bell Helicopter Textron Inc.

Inventor： SEIFERT, Michael Scott ,  ROMANO, Peter Quinn ,  PARHAM, Thomas

IPC: F16F7/14 ,  F16F7/116

Abstract: The present invention includes a damper assembly (306), method and kit to provide dampening to an airframe comprising: a mass (310) to dampen the vibration of the airframe; one or more wire rope isolators (312a, 312b) having a first and a second portion, wherein the mass (310) is attached to the one or more wire rope isolators (312a, 312b) and the mass (310) is isolated from the airframe by the one or more wire rope isolators (312a, 312b); and a first fastener (314a) and a second fastener (316a), wherein the first fasteners (314a) attaches to the first portion of the wire rope isolator (312a) to the mass (310), and the second fastener (316a) attaches the second portion of the wire rope isolator (312a) to the airframe to dampen vibration of the airframe.

公开(公告)号：EP3421353A1

公开(公告)日：2019-01-02

申请号：EP18167038.1

申请日：2018-04-12

Applicant: Bell Helicopter Textron Inc.

Inventor： PARHAM, Jr., Thomas Clement ,  BOSWORTH, Jeffrey ,  MILLER, Gary ,  STAMPS, Frank Bradley ,  CHOI, Jouyoung Jason ,  OLDROYD, Paul K. ,  RAUBER, Richard Erler ,  SEIFERT, Michael Scott

IPC: B64C3/26 ,  B64C29/00 ,  B64C1/12 ,  B64C3/20

Abstract: A wing airframe (36, 100, 222) for a wing (18, 102, 200) of a tiltrotor aircraft (10) includes a wing airframe coreassembly (110, 206) and a wing skin assembly (24, 118, 202) disposed on the wing airframe core assembly. The wing skin assembly (118, 202) includes an outer skin (52, 130, 208) and a damping sublayer (50, 128, 204), the damping sublayer interposed between the outer skin and the wing airframe core assembly (110, 206). The tiltrotor aircraft (10) includes a pylon assembly (30a, 30b) subject to aeroelastic movement during forward flight. The wing (18, 102, 200) is subject to deflection in response to the aeroelastic movement of the pylon assembly (30a, 30b). The damping sublayer (50, 128, 204) reduces the deflection of the wing (18, 102, 200), thereby stabilizing the wing during forward flight.