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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
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
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.
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公开(公告)号：EP3333074A1
公开(公告)日：2018-06-13
申请号：EP17195818.4
申请日：2017-10-10
发明人： PARHAM Jr., Thomas Clement , CHOI, Jouyoung Jason , MILLER, Gary , STAMPS, Frank Bradley , RAUBER, Richard Erler
摘要： A soft-in-plane proprotor system (100) for a tiltrotor aircraft (10) having a helicopter mode and an airplane mode. The proprotor system (100) includes a hub (102), a plurality of proprotor blades (104) and a plurality of loop yokes (120), each coupling one of the proprotor blades (104) with the hub (102) and each including first (204) and second (206) longitudinal sections extending between inboard (208) and outboard (210) arcuate sections and a bearing assembly (118) disposed between the inboard (208) and outboard (210) arcuate sections of each loop yoke (120). Each bearing assembly (118) includes a flapping bearing (122) disposed generally within the inboard arcuate section (208) of the respective loop yoke (120) and coupled to the hub (102), a lead-lag damper (128) coupled to the hub (108), a centrifugal force bearing (138) disposed generally within the outboard arcuate section (210) of the respective loop yoke (120) and a blade anchor (130) coupled between the lead-lag damper (128) and the centrifugal force bearing (138). The blade anchor (130) is also coupled to the respective proprotor blade (104).
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公开(公告)号：EP3333074B1
公开(公告)日：2019-05-15
申请号：EP17195818.4
申请日：2017-10-10
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公开(公告)号：EP3323720A1
公开(公告)日：2018-05-23
申请号：EP17192413.7
申请日：2017-09-21
发明人： CHOI, Jouyoung Jason , MILLER, Gary , RAUBER, Richard Erler , PARHAM, Thomas Clement, Jr. , EWING, Alan Carl , STAMPS, Frank Bradley
IPC分类号： B64C27/41 , B64C27/473 , B64C27/54 , B64C27/51 , B64C27/52 , B64C27/28 , B64C29/00 , B64C11/30
CPC分类号： B64C29/0033 , B64C27/28 , B64C27/41 , B64C27/473 , B64C27/51 , B64C27/52 , B64C27/54 , B64C2027/4736
摘要： A proprotor system (100; 200; 300; 400) for tiltrotor aircraft (10) having a helicopter mode and an airplane mode. The proprotor system includes a hub (102; 202; 302; 404) and a plurality of proprotor blades (112; 212; 312; 402) coupled to the hub (102; 202; 302; 404) such that each proprotor blade (112; 212; 312; 402) is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.
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