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

申请人： Bell Helicopter Textron Inc.

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

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

摘要： 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.

公开(公告)号：EP3421361A1

公开(公告)日：2019-01-02

申请号：EP18167032.4

申请日：2018-04-12

申请人： Bell Helicopter Textron Inc.

发明人： PARHAM, Jr., Thomas Clement ,  MILLER, Gary ,  STAMPS, Frank Bradley ,  CHOI, Jouyoung Jason

IPC分类号： B64C27/35 ,  B64C29/00 ,  B64C27/635 ,  B64C27/51

摘要： A proprotor system (32a, 32b) operable for use on a tiltrotor aircraft (10) having a helicopter flight mode and an airplane flight mode. The proprotor system (32a, 32b) includes a rotor hub (102) and a plurality of proprotor blades (34) coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis (128), blade flap about a flapping axis (130) and lead-lag about a lead-lag axis (132). Each of a plurality of spherical bearings couples one of the proprotor blades (34) with the rotor hub (102) . In addition, each of a plurality of lead-lag dampers (134) couples one of the proprotor blades (34) with the rotor hub (102), wherein each lead-lag damper is aligned with the pitch change axis (128) of the respective proprotor blade, thereby providing pitch independent lead-lag damping.

公开(公告)号：EP3421361B1

公开(公告)日：2019-06-12

申请号：EP18167032.4

申请日：2018-04-12

申请人： Bell Helicopter Textron Inc.

发明人： PARHAM, Jr., Thomas Clement ,  MILLER, Gary ,  STAMPS, Frank Bradley ,  CHOI, Jouyoung Jason

IPC分类号： B64C27/35 ,  B64C29/00 ,  B64C27/635 ,  B64C27/51