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2.发明公开
公开(公告)号：EP4410667A1
公开(公告)日：2024-08-07
申请号：EP23154160.8
申请日：2023-01-31
发明人： Lorenz, Florian , Bernhard, Schlipf
摘要： The invention relates to a flap system (10) for an aircraft (100). The flap system (10) comprises a wing structure (12), a trailing-edge movable (18a, 18b, 18c) and an attachment unit (20) for movably coupling the trailing-edge movable (18a, 18b, 18c) to the wing structure (12). The attachment unit (20) comprises an attachment mechanism (22) and a cover element (24) which at least partly encloses the attachment mechanism (22). The attachment unit (20) comprises a drive element (26) which is configured to move the cover element (24) along an aerodynamic outer surface (16) of a skin section (14) of the wing structure (12) between a first position (51) and a second position (52), wherein the movement of the cover element (24) along the aerodynamic outer surface (16) is defined by a translational movement (53) of the cover element (24) relative to the skin section (14).
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公开(公告)号：EP4385888A1
公开(公告)日：2024-06-19
申请号：EP22213598.0
申请日：2022-12-14
发明人： Seack, Oliver , Daandels, Dort , Stubbe, Kathrin , Ender, Tobias
摘要： The invention relates to a load introduction system (1) comprising an aerodynamic component (10) having a skin section (12) with an outer surface (14) and a first protrusion (16), and an attachment unit (20) for movably coupling the aerodynamic component (10) to a base unit (30). The attachment unit (20) is attached to the skin section (12) of the aerodynamic component (10) and to the first protrusion (16), wherein the first protrusion (16) extends away from the aerodynamic outer surface (14), thereby separating a space adjacent the aerodynamic outer surface (14) into a front space (16a) and a rear space (16b). The attachment unit (20) extends over the first protrusion (16) such that the attachment unit (20) comprises a front portion (21) in the front space (16a) and a rear portion (22) in the rear space (16b). The invention also relates to a method for manufacturing a load introduction system (1).
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公开(公告)号：EP3998687B1
公开(公告)日：2024-05-15
申请号：EP21174719.1
申请日：2021-05-19
IPC分类号： H02H7/26 , B64D27/24 , B64C29/00 , B64C13/50 , H02J1/10 , B64C9/16 , B64C9/18 , B64D31/14 , B64C9/08 , B64C39/12 , B64C15/12
CPC分类号： H02J2310/4420200101 , H02H7/26 , B64D27/24 , B64D2221/0020130101 , B64C29/0033 , B64C13/50 , H02J1/106 , B64D31/14 , B64C39/12 , B64C15/12 , Y02T50/60 , B64C9/16 , B64C9/18
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公开(公告)号：EP4286271A1
公开(公告)日：2023-12-06
申请号：EP22176859.1
申请日：2022-06-01
申请人： Asco Industries NV
IPC分类号： B64C9/16
摘要： Actuation assembly for a trailing edge flap of an aircraft wing, comprising: a track fixable to the aircraft wing; a carriage arranged on the track so as to be movable across a range of carriage positions along the track; a flap-to-carriage connector configured to hingeably connect the carriage to a leading edge of the flap so as to determine a flap-to-carriage hinging axis extending transverse to a main track direction of the track at the leading edge of the flap; and a first actuator configured to controllably rotate the flap with respect to the carriage about the flap-to-carriage hinging axis, wherein the actuation assembly is configured to enable the flap, when connected, to be adjusted with respect to the wing between a retracted flap position and an extended flap position by moving the carriage within the range of carriage positions along the track.
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公开(公告)号：EP3789289B1
公开(公告)日：2023-02-15
申请号：EP20185219.1
申请日：2020-07-10
发明人： TSAI, Kevin R. , GRUNER, Bryan J.
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公开(公告)号：EP4086166A1
公开(公告)日：2022-11-09
申请号：EP21171906.7
申请日：2021-05-03
发明人： Schlipf, Bernhard , Schreck, Tobias
摘要： Disclosed is a wing (5) for an aircraft (1), comprising a main wing (11), a high lift body (15), and a connection assembly (17) movably connecting the high lift body (15) to the main wing (11), such that the high lift body (15) can be moved between a retracted position and at least one extended position, wherein the connection assembly (17) comprises a drive system (25) comprising a first drive unit (27) and a second drive unit (29), wherein the first drive unit (27) has a first input section (31) coupled to a drive shaft (33), a first gear unit (35) and a first output section (37) drivingly coupled to the high lift body (15), wherein the second drive unit (29) has a second input section (39) coupled to the drive shaft (33), a second gear unit (41), and a second output section (43) drivingly coupled to the high lift body (15), wherein the first output section (37) comprises a first drive arm (45) drivingly coupled to the high lift body (15) via at least one first link element (49) rotatably coupled to the first drive arm (45) and mounted to the high lift body (15), and the second output section (43) comprises a second drive arm (47) drivingly coupled to the high lift body (15) via at least one second link element (51) rotatably coupled to the second drive arm (47) and mounted to the high lift body (15). The object to prevent excessively high torque loads during skew cases of the high lift body, is achieved in that the first link element (49) comprises a first linear deformation element (53), and/or the second link element (51) comprises a second linear deformation element (55), and the first linear deformation element (53) and/or the second linear deformation element (55) have a non-linear force-displacement characteristic (62).
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公开(公告)号：EP3998207A1
公开(公告)日：2022-05-18
申请号：EP21158191.3
申请日：2021-02-19
摘要： The invention refers to an aircraft, particularly an aircraft capable of vertical take-off and landing, comprising a fuselage, and a variable lift body defining an aerofoil and being moveably attached to the fuselage, wherein the variable lift body is pivotable around a first axis extending in the wing span direction; wherein a rotary actor adapted to cause the variable lift body to pivot in relation to the fuselage arranged within the aerofoil.
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