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公开(公告)号：US12006025B2
公开(公告)日：2024-06-11
申请号：US17796520
申请日：2021-01-27
发明人： Ivano Bertolini , Martin Obermaier , Michael Höft , Frank Nielsen , Sergej Rajkowski , Jeff Wee Hong Yap
摘要： A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) having micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61).
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公开(公告)号：US11964765B2
公开(公告)日：2024-04-23
申请号：US17581077
申请日：2022-01-21
发明人： Ivano Bertolini , Stefano Giaquinto , Sebastian Welz , Nina Düren , Jeff Wee Hong Yap , Nicole Jordan , Frank Nielsen
IPC分类号： B64C5/02
CPC分类号： B64C5/02
摘要： A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).
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公开(公告)号：US11932388B2
公开(公告)日：2024-03-19
申请号：US17581640
申请日：2022-01-21
发明人： Ivano Bertolini , Stefano Giaquinto , Sebastian Welz , Nina Düren , Jeff Wee Hong Yap , Michael Höft , Nicole Jordan , Frank Nielsen
摘要： A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).
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