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1. 发明申请

WO2010124877A8 NON-PLANAR WING TIP DEVICE FOR WINGS OF AIRCRAFT, AND WING COMPRISING SUCH A WING TIP DEVICE 审中-公开
标题翻译：非平面翼形装置，包括飞行器的翅膀，以及包含这种方式的装置
公开(公告)号：WO2010124877A8
公开(公告)日：2010-12-23
申请号：PCT/EP2010002663
申请日：2010-04-30
申请人： AIRBUS OPERATIONS GMBH , BUESCHER ALEXANDER , KARWIN MICHAEL , THEURICH FRANK
发明人： BUESCHER ALEXANDER , KARWIN MICHAEL , THEURICH FRANK
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： A wing tip device (W; W1, W2) for a wing (T; 10a, 10b), comprising aroot (E1) and atip (E2) and the following determinant characteristics: the local dihedral of the wing tip device (W; W1, W2) continuously increases or decreases from the root (E1) to the tip (E2); the local sweep of the trailing edge (50) continuously increases along its progression from the root (E1) to the tip (E2) of the wing tip device (W; W1, W2); wherein the local sweep of the leading edge (60) continuously increases in the progression of the leading edge (60) from the root (E1) to a first intermediate point (61a); continuously decreases from the first intermediate point (61a) to a second intermediate point (62a); and continuously increases from the second intermediate point (62a) at least to a region before of the tip (E2) of the wing tip device (W; W1, W2); as well as a wing comprising a wing tip device (W; W1, W2).
摘要翻译：用于翼（T; 10a，10b）的翼尖装置（W; W1，W2），包括根部（E1）和蹄（E2）和以下决定因素特征：翼尖装置的局部二面（W; W1 W2）从根（E1）到尖端（E2）连续地增加或减少; 后缘（50）的局部扫掠沿着其从根部（E1）到翼尖装置（W; W1，W2）的尖端（E2）的进展而连续地增加; 其中前缘（60）的局部扫描在前缘（60）从根部（E1）到第一中间点（61a）的进行中连续地增加; 从第一中间点（61a）连续地减小到第二中间点（62a）; 并且从第二中间点（62a）至少持续增加到翼尖装置（W; W1，W2）的前端（E2）之前的区域。以及包括翼尖装置（W; W1，W2）的翼。

2. 发明申请

WO2008061739A1 WING TIP SHAPE FOR A WING, IN PARTICULAR OF AIRCRAFT 审中-公开
标题翻译：特别是飞机的WING TIP形状
公开(公告)号：WO2008061739A1
公开(公告)日：2008-05-29
申请号：PCT/EP2007/010096
申请日：2007-11-21
申请人： AIRBUS DEUTSCHLAND GMBH , DEUTSCHES ZENTRUM FÜR LUFT- UND RAUMFAHRT E.V. (DLR) , THEURICH, Frank , HIMISCH, Jan
发明人： THEURICH, Frank , HIMISCH, Jan
IPC分类号： B64C23/00
CPC分类号： B64C23/069 , Y02T50/164
摘要： Described is a wing tip shape for a wing, in particular of aircraft, which wing comprises a profile that extends in the direction of the span of the wing (1), and across said direction of the span of the wing (1) extends from the wing leading edge (8, 6, 10) to the wing trailing edge (7), which profile is delimited by a first skin (11) and a second skin (12), with a winglet (3), arranged on the wing end, which winglet (3) is essentially planar, and with a transition region (2) arranged between the wing (1) and the winglet (3), which transition region (2) extends from a connection (4) on the wing (1) to a connection (5) on the winglet (3). The invention provides for the curvature of the local dihedral to increase in the transition region (2) from a low level or a level of zero at or near the wing intersection (4) in the outboard direction.
摘要翻译：描述了用于机翼，特别是飞行器的翼尖形状，该翼包括沿着机翼（1）的跨度的方向延伸的轮廓，并且跨越翼（1）的跨度的所述方向从所述机翼前缘（8,6,10）到所述机翼后缘（7），所述轮廓由第一皮肤（11）和第二皮肤（12）界定，所述小翼（3）布置在所述机翼端部，该小翼（3）基本上是平面的，并且具有布置在机翼（1）和小翼（3）之间的过渡区域（2），该过渡区域（2）从机翼上的连接（4）延伸 1）连接到小翼（3）上的连接（5）。本发明提供了局部二面体的曲率以在过渡区域（2）中从外侧方向上的翼交点（4）处或附近的零水平或零水平增加。

3. 发明申请

WO2007096171A1 FLAPTRACK FAIRING ON THE WING OF AN AIRCRAFT 审中-公开
标题翻译：飞行员在飞机上的飞行
公开(公告)号：WO2007096171A1
公开(公告)日：2007-08-30
申请号：PCT/EP2007/001548
申请日：2007-02-22
申请人： AIRBUS DEUTSCHLAND GMBH , LAU, Karl-Ernst , SCHWARTEN, Helmuth , THEURICH, Frank
发明人： LAU, Karl-Ernst , SCHWARTEN, Helmuth , THEURICH, Frank
IPC分类号： B64C9/16 , B64C23/00 , B64C7/00
CPC分类号： B64C7/00 , B64C9/16 , Y02T50/32
摘要： In a flaptrack fairing (3) on the wing (2) of an aircraft (1), which flaptrack fairing (3) partly protrudes beyond the trailing edge (7) of the wing (2) in the direction of the longitudinal axis (x) of the wing (2), the invention provides for the width of the flaptrack fairing, which width extends in the direction of the wingspan (y) of the aircraft (1), to increase towards the rear in the region of the trailing edge (7) of the wing with progressive x-direction. The maximum width of the flaptrack fairing is behind the trailing edge of the wing, preferably in a region which in relation to the local wing profile depth starts at 15% in front of the trailing edge of the wing and extends beyond said trailing edge of the wing.
摘要翻译：在飞行器（1）的机翼（2）上的翼片整流罩（3）中，所述翼板整流罩（3）在纵向轴线（x）的方向上部分地突出超过机翼（2）的后缘（7）），本发明提供了翼板整流罩的宽度，其宽度在飞行器（1）的翼展（y）方向上延伸，以在后缘的区域中朝向后方增加（7），具有渐进的x方向。翼片整流罩的最大宽度在翼的后缘之后，优选地在相对于局部翼型轮廓深度开始于翼的后缘前方的15％的区域中，并且延伸超过翼的后缘翅膀。

4. 发明申请

WO2013007396A1 WINGTIP DEVICE OF A WING, AND ALSO A WING WITH SUCH A WINGTIP DEVICE 审中-公开
标题翻译： WINGTIP设备的一个WING，还有一个WING与这样一个WINGTIP设备
公开(公告)号：WO2013007396A1
公开(公告)日：2013-01-17
申请号：PCT/EP2012/002986
申请日：2012-07-16
申请人： AIRBUS OPERATIONS GMBH , THEURICH, Frank , HIMISCH, Jan
发明人： THEURICH, Frank , HIMISCH, Jan
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： A wingtip device (W; W1, W2, W4, W5, W6, W7, W8) for a wing (T; 10a, 10b), which has an inner end (E1) and an outer end (E2), and in which the local dihedral of the wingtip device (W; W1, W2, W4, W5, W6, W7, W8) increases or reduces from the inner end (E1) to the outer end (E2), with a pressure-side flow surface (U-W) and a suction-side flow surface (P-W), wherein at least two ancillary wing sections (100; 101, 102, 103) are arranged on the wingtip device (W; W1, W2, W4, W5, W6, W7, W8), projecting in each case from the flow surface of the wingtip device (W; W1, W2, W3, W4, W5, W6, W7, W8), and wherein the ancillary wing sections (100; 101, 102, 103) in each case form an interface (q0) with the surface of the wingtip device (W; W1, W2, W4, W5, W6, W7, W8); which interfaces are located spaced apart from one another, and a wing (T) with such a wingtip device (W; W1, W2, W4, W5, W6, W7, W8).
摘要翻译：具有内端（E1）和外端（E2）的机翼（T; 10a，10b）的翼尖装置（W; W1，W2，W4，W5，W6，W7，W8）翼尖装置（W; W1，W2，W4，W5，W6，W7，W8）的局部二面体从内端（E1）向外端（E2）增加或减小，压力侧流动面 UW）和吸入侧流动面（PW），其中至少两个辅助翼部（100; 101,102,103）布置在翼尖装置（W; W1，W2，W4，W5，W6，W7， W8），从翼片装置（W; W1，W2，W3，W4，W5，W6，W7，W8）的流动面各自突出，并且其中辅助翼部（100; 101,102,103）在每种情况下，与翼尖装置的表面（W; W1，W2，W4，W5，W6，W7，W8）形成界面（q0）; 以及具有这种翼尖装置（W; W1，W2，W4，W5，W6，W7，W8）的机翼（T）。

5. 发明申请

WO2011127938A1 FIXED WING OF AN AIRCRAFT 审中-公开
标题翻译：固定翼的飞机
公开(公告)号：WO2011127938A1
公开(公告)日：2011-10-20
申请号：PCT/EP2010/002250
申请日：2010-04-12
申请人： AIRBUS OPERATIONS GMBH , AIRBUS OPERATIONS LTD. , HELLER, Gerd , BUESCHER, Alexander , THEURICH, Frank , GIBSON, Tom , KARWIN, Michael , POWELL, Stephen
发明人： HELLER, Gerd , BUESCHER, Alexander , THEURICH, Frank , GIBSON, Tom , KARWIN, Michael , POWELL, Stephen
IPC分类号： B64C23/06
CPC分类号： B64C3/58 , B64C23/069 , Y02T50/164
摘要： A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box comprised of spars extending along the spanwise direction of the main wing, a plurality of ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box is comprised of a wing box base section (K10) and a wing box adapter section (20), that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device (W). In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib (R3) of the wing box base section (K10) up to the outermost rib (R5) of the wing box adapter section.
摘要翻译：一种飞机的固定翼，具有在半跨上延伸的主翼，翼翼由沿着主翼的翼展方向延伸的翼梁组成，沿翼展方向观察的多个肋布置在另一个后面，和外皮。翼箱由翼箱基部（K10）和翼盒适配器部分（20）组成，从机翼根部观察时，形成翼盒的外端区域，并被设计成固定翼尖设备（W）。在其标称建造状态下，翼箱适配器部分参考相应的局部翼展方向的二面角从翼箱基部（K10）的外肋（R3）连续增加至多60度，直到最外侧机翼盒适配器部分的肋（R5）。

6. 发明申请

WO2010124877A1 NON-PLANAR WING TIP DEVICE FOR WINGS OF AIRCRAFT, AND WING COMPRISING SUCH A WING TIP DEVICE 审中-公开
标题翻译：用于飞机翼的非平面翼梢装置以及包括这种翼翼装置的翼
公开(公告)号：WO2010124877A1
公开(公告)日：2010-11-04
申请号：PCT/EP2010/002663
申请日：2010-04-30
申请人： AIRBUS OPERATIONS GMBH , BUESCHER, Alexander , KARWIN, Michael , THEURICH, Frank
发明人： BUESCHER, Alexander , KARWIN, Michael , THEURICH, Frank
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： A wing tip device (W; W1, W2) for a wing (T; 10a, 10b), comprising aroot (E1) and atip (E2) and the following determinant characteristics: the local dihedral of the wing tip device (W; W1, W2) continuously increases or decreases from the root (E1) to the tip (E2); the local sweep of the trailing edge (50) continuously increases along its progression from the root (E1) to the tip (E2) of the wing tip device (W; W1, W2); wherein the local sweep of the leading edge (60) continuously increases in the progression of the leading edge (60) from the root (E1) to a first intermediate point (61a); continuously decreases from the first intermediate point (61a) to a second intermediate point (62a); and continuously increases from the second intermediate point (62a) at least to a region before of the tip (E2) of the wing tip device (W; W1, W2); as well as a wing comprising a wing tip device (W; W1, W2).
摘要翻译：一种用于机翼（T; 10a，10b）的翼尖装置（W; W1，W2），包括根部（E1）和尖端（E2）以及以下行列式特征：翼尖装置（W; W1，W2）从根部（E1）向尖端（E2）连续增大或减小; 后缘（50）的局部扫掠沿其从翼尖装置（W; W1，W2）的根部（E1）到尖端（E2）的进展连续地增加; 其中前缘（60）的局部扫掠在前缘（60）从根部（E1）到第一中间点（61a）的前进中连续增加; 从第一中间点（61a）连续减小到第二中间点（62a）; 并且从第二中间点（62a）至少连续增加到翼尖装置（W; W1，W2）的尖端（E2）之前的区域; 以及包括翼尖装置（W; W1，W2）的机翼。

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