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公开(公告)号：US11155342B2
公开(公告)日：2021-10-26
申请号：US16354757
申请日：2019-03-15
发明人： Alexander Büscher
IPC分类号： B64C21/04 , B64C5/02 , B64C21/02 , B64C21/08 , B64C21/06 , B64C3/28 , F15D1/00 , B64C5/06 , B64C3/14
摘要： A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding surrounds a plenum (17) which extends in a span direction (19), wherein the leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25), wherein the leading edge panel (13) has a second side portion (27) opposite the first side portion (21), extending from the leading edge point (23) to a second attachment end (29), wherein the leading edge panel (13) comprises an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39).
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公开(公告)号：US11673651B2
公开(公告)日：2023-06-13
申请号：US17277130
申请日：2019-09-18
发明人： Alexander Büscher
摘要： A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.
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