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    Verfahren und Vorrichtung zum Reduzieren eines mit einem begrenzten Überschallströmungsgebiet verbundenen Wellenwiderstands
    4.
    发明公开
    Verfahren und Vorrichtung zum Reduzieren eines mit einem begrenzten Überschallströmungsgebiet verbundenen Wellenwiderstands 有权
    的方法和流体，其包括一个装置用于减少连接到有限超音速流场的流动阻力

    公开(公告)号：EP1506922A1

    公开(公告)日：2005-02-16

    申请号：EP04016283.6

    申请日：2004-07-10

    申请人： DLR Deutsches Zentrum für Luft- und Raumfahrt e.V.

    发明人： Dietz, Guido, Dr.-Ing.

    IPC分类号： B64C23/04 ,  B64C21/00

    CPC分类号： B64C21/00 ,  B64C23/04 ,  Y02T50/166

    摘要： Zum Reduzieren eines Strömungswiderstands, der mit einem begrenzten Überschallströmungsgebiet, das sich über einer in einer Strömungsrichtung (6) umströmten Oberfläche (2) eines Strömungskörpers (1) ausbildet und das mit einem starken Verdichtungsstoß (7) abschließt, verbunden ist, wird die Strömungsgeschwindigkeit in quer zu der Strömungsrichtung (6) voneinander beabstandeten und in der Strömungsrichtung (6) langgestreckten Bereichen (4) an der Oberfläche (2) unterhalb der Schallgeschwindigkeit gehalten, so dass die Druckinformation von dem Verdichtungsstoß (7) in diesen Bereichen (4) entgegen der Strömungsrichtung (6) an der Oberfläche (2) nach vorne gelangt und sich von diesen Bereichen (4) ausgehend quer zu der Strömungsrichtung (6) an der Oberfläche (2) ausbreitet.

    摘要翻译： 该方法是用于通过翼面（1）的一个表面连接到一个有限的超声流区域中的波阻的降低。 被提供在（7）终止所述的超音速区在强压缩休克前的流动方向（6）的翼面的表面上，用于弱压缩冲击（9）的创建扰流板。 各组与一些小扰流板被布置在机翼的所述表面（2）上，并在流动方向上延伸，并在垂直于流动方向间隔开。 一个独立的claimsoft包括用于为波阻的上翼面的减少的装置。

    AIRFOIL FOR SUPERSONIC AIRCRAFT
    5.
    发明公开
    AIRFOIL FOR SUPERSONIC AIRCRAFT 审中-公开

    公开(公告)号：EP4190695A1

    公开(公告)日：2023-06-07

    申请号：EP22183853.5

    申请日：2022-07-08

    申请人： O'Leary, Patrick

    发明人： O'Leary, Patrick

    IPC分类号： B64C30/00 ,  B64C21/02 ,  B64C23/04 ,  B64C3/14

    摘要： A wing structure for a supersonic aircraft including a pair of supersonic wave-tripping channels formed on each of two laterally extending wings of the supersonic aircraft, wherein each of the pair of supersonic wave-tripping channels extend in a span-wise direction of the wings respectively, wherein an upper supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on an upper surface of each of the wings and a lower supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on a lower surface of each of the wings, wherein the upper supersonic wave-tripping channel and the lower supersonic wave-tripping channel are set back from a leading edge of the wings respectively.

    AIRCRAFT WING WITH AN ADAPTIVE SHOCK CONTROL BUMP
    6.
    发明公开
    AIRCRAFT WING WITH AN ADAPTIVE SHOCK CONTROL BUMP 审中-公开
    飞机翼带适应性冲击控制缓冲器

    公开(公告)号：EP3187412A1

    公开(公告)日：2017-07-05

    申请号：EP15203195.1

    申请日：2015-12-30

    申请人： Airbus Defence and Space GmbH ,  Airbus Operations GmbH

    发明人： Hansen, Heinz ,  Kirn, Johannes ,  Machunze, Wolfgang ,  Metzner, Christian ,  Weber, Markus J.

    IPC分类号： B64C3/14 ,  B64C23/04

    摘要： Provided is an aircraft wing (100) with an upper surface element (101) and a first actuator powered mechanism (102) for varying the shape of the upper surface element (101), wherein the surface element (101) is comprising: an upstream segment SEG 1 with a stiffness S 1 , a downstream segment SEG 2 with a stiffness S 2 , an interconnecting segment SEG 3 with a stiffness S 3 , the interconnecting segment SEG 3 is interconnecting a downstream edge of SEG 1 with an upstream edge of SEG 2 , wherein the interconnecting segment SEG 3 is extending along the whole downstream edge of SEG 1 and the whole upstream edge of SEG 2 , or at least along a major part of the downstream edge of SEG 1 and a major part of the upstream edge of SEG 2 , and the interconnecting segment SEG 3 exhibits a mechanical pretension causing a convex shape of the upper surface element with: S 3 1 , S 2 , a link element LNK, the link element LNK is interconnecting an upstream edge of SEG 1 with an upper surface (103) of the aircraft wing, and the first actuator powered mechanism (102) is interconnecting a contact C1 on a lower side of the upper surface element (101) with a contact C2 on an inner structure of the airfoil, wherein the first actuator powered mechanism (102) controls the shape of the upper surface element (101) by controlling the distance between C1 and C2.

    摘要翻译： 提供了一种具有用于改变上表面元件（101）的形状的上表面元件（101）和第一致动器驱动机构（102）的飞行器机翼（100），其中表面元件（101）包括：上游 具有刚度S1的节段SEG1，具有刚度S2的下游节段SEG2，具有刚度S3的互连节段SEG3，互连节段SEG3将SEG1的下游边缘与SEG2的上游边缘互连，其中互连节段SEG3延伸 沿着SEG1的整个下游边缘和SEG2的整个上游边缘，或者至少沿着SEG1的下游边缘的主要部分和SEG2的上游边缘的主要部分，并且互连段SEG3呈现出机械预应力， S3

    SHOCK BUMP
    9.
    发明公开
    SHOCK BUMP 有权
    冲击产生隆起

    公开(公告)号：EP2250086A2

    公开(公告)日：2010-11-17

    申请号：EP09714018.0

    申请日：2009-02-17

    申请人： Airbus Operations Limited

    发明人： WOOD, Norman

    IPC分类号： B64C23/04 ,  B64C7/00

    CPC分类号： B64C23/04 ,  B64C2003/148 ,  B64C2003/149

    摘要： A shock bump (10) comprising a diverging nose (20) and a converging tail. The tail has at least one plan-form contour line with a pair of concave opposite sides (22, 23). The shock bump provides an improved shape with relatively low drag. Furthermore, the concave shape of the tail tends to promote the development of longitudinal vortices which can reduce shock induced buffet at certain operating conditions.