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11.发明授权AIRFOIL WITH A MAIN WING AND A HIGH-LIFT BODY AND METHOD FOR REALIZING ADJUSTING MOVEMENTS OF A HIGH-LIFT BODY RELATIVE TO A MAIN WING 有权与主翼剖面和高提升本体和方法用于高提升身体的停车动作相对于主翼EXECUTION
公开(公告)号：EP2726372B1
公开(公告)日：2015-10-21
申请号：EP12743671.5
申请日：2012-06-28
发明人： SCHLIPF, Bernhard , TRIEBL, Carsten
摘要： A wing assembly and method for operating the wing assembly, the assembly having a main wing and high-lift body movably coupled to the leading edge of the main wing, the coupling achieved by a driving device, an adjusting lever arrangement having a first main wing lever coupled to the main wing formed between a first adjusting lever pivot joint and the high-lift body as well as a second main wing lever coupled to the main wing so as to form an effective lever arm between a second adjusting lever pivot joint and a first adjusting lever pivot joint, and at least one adjusting lever non-rotatably coupled to the high-lift body, the high-lift body being movable between an initial position and a maximally adjusted position with respect to the initial position, at least one guide mechanism aiding movement of the high-lift body.
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12.发明授权
公开(公告)号：EP2467297B1
公开(公告)日：2015-05-27
申请号：EP10747588.1
申请日：2010-08-17
发明人： SCHLIPF, Bernhard , MISSBACH, Mirko
IPC分类号： B64C9/22
CPC分类号： B64C9/22
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公开(公告)号：EP2566754A1
公开(公告)日：2013-03-13
申请号：EP11721427.0
申请日：2011-05-03
发明人： SCHLIPF, Bernhard , HUE, Xavier
IPC分类号： B64C3/56
CPC分类号： B64C3/56
摘要： The invention relates to a wing with an extension in the wingspan direction, in the wing chord direction and in the wing thickness direction for use in an aircraft, with a retractable wing end piece. A mechanical lever system is here used, which can execute a pivoting motion of a wing end piece comprising both a rotational component and a translational component. The lever kinematics here comprises two lever arrangements, for which a respective two hinged devices are provided.
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14.发明公开
公开(公告)号：EP2473403A1
公开(公告)日：2012-07-11
申请号：EP10752524.8
申请日：2010-09-03
摘要： The invention relates to an adjusting mechanism (M) for kinematically guiding an adjusting body (K) during an adjustment of said mobile body on a supporting structure, said adjusting body (K) can be displaced between a retracted position and a deployed position by a movement in the longitudinal direction (L) in combination with a rotational position. Said adjusting mechanism (M) comprises: a first transmission lever (11a, 11 b) and a second transmission lever (15a, 15b) for coupling to the supporting structural part (H1, H2), a base connecting lever (20) to which the first transmission lever and the second transmission lever are coupled, a third transmission lever (21 a, 21 b) coupled to the base connecting lever (20) and a fourth transmission lever (25a, 25b), an adjusting lever (30) coupled to the third transmission lever (21a, 21b) and the fourth transmission lever (25a, 25b) for mounting the adjusting body (K) in order to adjust said adjusting body (K) by moving the adjusting lever (30) and a coupling lever to which the first transmission lever and the third transmission lever (21a, 21b) are coupled. The invention also relates to an adjusting mechanism for kinematically adjusting a vertical lift body and vertical lift system comprising said type of adjusting mechanism.
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公开(公告)号：EP2344379A2
公开(公告)日：2011-07-20
申请号：EP09744054.9
申请日：2009-10-06
发明人： SCHLIPF, Bernhard , HUE, Xavier
IPC分类号： B64C9/24
摘要： The invention relates to a fore flap disposed on the wing of an aircraft, wherein the wing comprises a main wing (24) having an upper planking (21), a lower planking (22), and a profile nose (23), and the fore flap (12) is on the front side of the main wing (24) and has a profile nose (10) oriented forward and an end edge (11) facing the main wing (24) and oriented rearward, and can be extended in order to increase lift by increasing the curvature and extent of the wing profile in the depth direction of the wing, from a retracted cruise flight position (I) in which the fore flap (12) contacts the front side of the main wing (24) and extends the profile thereof into a shape suitable for cruise flight, wherein the end edge (11) of the fore flap (12) contacts the main wing (24) in a first, partially extended position (II), and having the end edge (11) at a distance from the profile nose (23) of the main wing in a second, further extended position (IM), exposing high-energy air from the bottom side of the fore flap (12) to the top side (21) of the gap (14) leading the main wing (24). The fore flap (12) comprises a main body (6) and an end edge part (2) facing the main wing (24) and displaceable at an angle in the wing span direction of the fore flap (12) relative to the main body (6), and on which the end edge (11) of the fore flap (12) is provided, and which is acted on by means of a device (4; 8; 9) generating a contact force for contacting the end edge (11) of the fore flap against the profile nose (23) of the main wing (24).
摘要翻译： 一架安装在飞机机翼上的前缘板条。 前缘板条设置在主翼的前部。 前缘板条具有部分延伸的设置，其后缘平坦地抵靠机翼，并且进一步延伸的设置，其后缘与机翼的鼻部间隔开，以打开从下表面供给高能空气的间隙 的板条到机翼的上表面。 前缘板条包括一个主体和一个面向主翼的后缘，它可相对于主体围绕板条的翼展方向弯曲，并且在其上设有板条的后缘，并且借助于 加载产生接触力的装置用于使板条的后缘与机翼的轮廓鼻之间接触。
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公开(公告)号：EP4292924A1
公开(公告)日：2023-12-20
申请号：EP22179330.0
申请日：2022-06-15
发明人： SCHLIPF, Bernhard , KREY, Dennis , GEMILANG, Altra
IPC分类号： B64C7/00
摘要： A sealing device for covering an aperture in a wing part of an aircraft is proposed, the sealing device (16) comprising a cover plate (24) for covering at least a part of the aperture, the cover plate (24) having an outer surface (15) delimited by a cover plate edge (26), and at least one holding device (28) coupled with the cover plate (24), wherein the at least one holding device (28) comprises a resilient element (42), wherein the at least one holding device (28) is designed for resiliently holding the cover plate (24) in a distance to an actuation element (20), wherein the distance is variable in a first direction substantially perpendicular to the outer surface (15), wherein the at least one holding device (28) is designed for holding the cover plate (24) in a substantially fixed spatial alignment in second directions perpendicular to the first direction, and wherein the resilient element (42) is designed for urging the cover plate towards the actuation element (20) in a mounted state of the sealing device (16).
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公开(公告)号：EP3969361A1
公开(公告)日：2022-03-23
申请号：EP20743599.1
申请日：2020-07-10
发明人： DAANDELS, Dort , SCHLIPF, Bernhard
IPC分类号： B64C9/22
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公开(公告)号：EP3885251A1
公开(公告)日：2021-09-29
申请号：EP21164234.3
申请日：2021-03-23
发明人： Krey, Dennis , Huber, Alexander , SCHLIPF, Bernhard , Lorenz, Florian , Shapi, Dustin , Grahs, Robert
摘要： Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5), a slat (7), and a connection assembly (9) movable connecting the slat (7) to the main wing (5), wherein the connection assembly (9) comprises an elongate slat track (17), wherein the front end (21) of the slat track (17) is mounted to the slat (7) and the rear end (23) and the intermediate portion (25) of the slat track (17) are mounted to the main wing (5) by a roller bearing (27) comprising a guide rail (29) mounted to the main wing (5) and a first roller unit (31) mounted to the rear end (23) of the slat track (17) and engaging the guide rail (29), wherein the roller bearing (27) comprises a second roller unit (33) mounted to the main wing (5) and engaging an engagement surface (35) at the intermediate portion (25) of the slat track (17), wherein the slat track (17) has a profile (37) comprising an upper flange portion (39), a lower flange portion (41) and at least one web portion (43), and wherein the second roller unit (33) is arranged in a recess (45) between upper and lower flange portions (39, 41) and engages the engagement surface (35) provided at the upper flange portion (39) and/or at the lower flange portion (41). The object, to provide a wing that allows for a simplified installation of the slat track at the main wing, is achieved in that a gap (112) is provided between the upper flange portion (39) and the first roller unit (31) or between the upper flange portion (39) and a yoke portion (127) for holding the first roller unit (31), wherein the gap (112) is wider than the diameter of the second roller unit (33), so that the second roller unit (33) might be passed through the gap (112) to be inserted into the recess (45) when the slat track (17) is installed on the main wing (5).
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公开(公告)号：EP2701974B1
公开(公告)日：2018-11-21
申请号：EP12718964.5
申请日：2012-04-27
发明人： SCHLIPF, Bernhard , HUE, Xavier
摘要： A high lift component includes at least one intermediate seal on at least one lateral surface, wherein the intermediate seal includes at least one hollow body made of an elastic material, which hollow body includes a fluid inlet that is connectable to a fluid source. A gap between two high lift components, which gap is subjected to dynamic changes in geometry, can be flexibly sealed in this manner.
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公开(公告)号：EP3315399A1
公开(公告)日：2018-05-02
申请号：EP16196415.0
申请日：2016-10-28
发明人： DAANDELS, Dort , SCHLIPF, Bernhard
CPC分类号： B64C9/02 , B64C9/14 , B64C2009/143
摘要： A wing (2) for an aircraft comprises a main wing structure (10) fixedly attachable to a body of an aircraft, a high lift body (8) movably supported at the main wing structure (10), a drive unit (12) coupled with the main wing structure (10) and the high lift body (8) and adapted to move the high lift body (8) relative to the main wing structure (10) in a substantial chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body (8) and the main wing structure (10). The high lift body (8) comprises at least one outer edge (26) facing to the main wing structure (10), which at least one outer edge (26) creates a gap (36) to the main wing structure (8) at least in the extended position. The sealing device comprises a flexible sealing body (34), which seals the intermediate space (36) between the high lift body (8) and the main wing structure (10) in the extended position of the high lift body (8).
摘要翻译： 一种用于飞机的机翼（2）包括：可固定地连接到飞机机身的主机翼结构（10）;可移动地支撑在主机翼结构（10）上的高升力机身（8） 与主翼结构（10）和高升力本体（8）并且适于相对于主翼结构（10）相对于主翼结构（10）在缩回位置和延伸位置之间的基本弦向方向上移动， 以及与高升力本体（8）和主翼结构（10）联接的密封装置。 所述高升力本体（8）包括面向所述主翼结构（10）的至少一个外边缘（26），所述至少一个外边缘（26）在所述主翼结构（8）处形成间隙（36） 至少在延长的位置。 该密封装置包括柔性密封体（34），该柔性密封体在高升力体（8）的延伸位置中在高升力体（8）和主翼结构（10）之间密封中间空间（36）。
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