公开(公告)号：US06722615B2

公开(公告)日：2004-04-20

申请号：US10116875

申请日：2002-04-05

申请人： Gerd Heller ,  Manfred Maisel ,  Peter Kreuzer

发明人： Gerd Heller ,  Manfred Maisel ,  Peter Kreuzer

IPC分类号： B64C508

CPC分类号： B64C3/10 ,  B64C23/069 ,  Y02T50/12 ,  Y02T50/164

摘要： The present invention relates to a wing tip extension (7) for a wing, having an upper and a lower surface (10 and 11) and a leading edge and a trailing edge (12 and 13), the geometries of which are such that between a connection region (8), for connection with a wing, and the tip (9) of the wing tip extension (7) there is provided a continuous increase of the local dihedral, a continuous increase both of the sweepback angle of the leading edge (12) and also of the trailing edge (13), and a continuous decrease of the chord of the wing tip extension (7), and in that the wing tip extension (7) in the connection region (8) carries on from the wing in substance continuously. The wing tip extension (7) in accordance with the invention thereby ensures a significant reduction of the overall drag.

摘要翻译： 本发明涉及一种用于机翼的翼尖延伸部（7），其具有上和下表面（10和11）以及前缘和后缘（12和13），其几何形状使得在 用于与翼连接的连接区域（8）和翼尖延伸部（7）的尖端（9）提供局部二面体的连续增加，连续增加前缘的回扫角 （12）以及后缘（13）的延伸，并且翼尖延伸部（7）的弦的连续减小，并且连接区域（8）中的翼尖延伸部（7）从 翼在物质上不断。 因此，根据本发明的翼尖延伸部（7）从而确保整体阻力的显着减小。

公开(公告)号：US08286921B2

公开(公告)日：2012-10-16

申请号：US12598728

申请日：2008-05-05

申请人： Gerd Heller

发明人： Gerd Heller

IPC分类号： B64C3/54

CPC分类号： B64C9/24 ,  B64C3/50 ,  B64C9/22

摘要： A high-lift system on a wing with a curved nose and a leading-edge flap mounted via levers for movement between retracted and extended positions while expanding the airfoil profile, increasing its curvature and exposing a gap for guiding air from under the flap to above the wing. The levers form a four bar mechanism including first and second levers respectively pivotably connected at one end to spaced first and second points on the wing. The other ends of the levers are connected to opposite ends of a third lever forming part of the flap. The length and positions of the levers and the curvature of the wing nose are matched such that during initial extension from retracted position to an intermediate position the trailing edge of the flap blocks the gap between the flap and wing, and during further extension beyond the intermediate position the gap is exposed.

摘要翻译： 机翼上的一个高升力系统，具有弯曲的鼻部和前缘翼片，通过杠杆安装，用于在收缩和伸展位置之间移动，同时扩大翼面轮廓，增加其曲率并露出用于将空气从翼片下方引导到上方的间隙 机翼。 杠杆形成四杆机构，其包括第一和第二杆，其分别在一端可枢转地连接到机翼上的间隔开的第一和第二点。 杠杆的另一端连接到形成翼片一部分的第三杆的相对端。 杠杆的长度和位置以及翼尖的曲率相匹配，使得在从缩回位置到中间位置的初始延伸期间，翼片的后缘阻挡翼片和翼之间的间隙，并且在进一步延伸超过中间 位置的差距是暴露的。

公开(公告)号：US20100155542A1

公开(公告)日：2010-06-24

申请号：US12598728

申请日：2008-05-05

申请人： Gerd Heller

发明人： Gerd Heller

IPC分类号： B64C9/24 ,  B64C3/50

CPC分类号： B64C9/24 ,  B64C3/50 ,  B64C9/22

摘要： A high-lift system on the airfoil of an aircraft, comprising a main wing (H) which has a curved main wing nose (N) and comprising a leading-edge flap (V) is disposed retractably on the main wing (H) by means of an arrangement of several levers (a, b, c) so that said leading-edge flap can be moved from a retracted position (I) whilst increasing the expansion of the airfoil profile in the chord direction and whilst increasing its curvature and whilst exposing a gap (g) which guides energetic air from the underside of the leading-edge flap (V) to the upper side of the main wing (H), as far as a fully extended position (III). According to the invention, the lever arrangement (a, b, c) is configured in the form of a four-bar mechanism and comprises a first lever (a) and a second lever (b), of which the first lever (a) is connected at one end to a first point (A) on the main wing (H) in an articulated manner and the second lever (B) is connected at one end to a second point (B) at a distance therefrom on the main wing (H) in an articulated manner, and which are each connected at the respectively other end in an articulated manner to the opposite ends of a third lever (c) which is part of the leading-edge flap (V) and defines its extending movements, wherein the length and the mutual position of the levers (a, b, c) and the curvature of the main wing nose (N) are matched to one another such that during a first part of the extending movement from the retracted position (I) to an intermediate position (II) the trailing edge (K) of the leading-edge flap (V) substantially blocks the gap (g) between the leading-edge flap (V) and the main wing (H) and that during a further part of the extension movement following the intermediate position (II), the trailing edge (K) of the leading-edge flap increasingly exposed the gap (g).