公开(公告)号：EP2021243B1

公开(公告)日：2018-10-24

申请号：EP07815105.7

申请日：2007-04-27

申请人： Flexsys, Inc.

发明人： HETRICK, Joel, A. ,  ERVIN, Gregory, F. ,  KOTA, Sridhar (nmn)

IPC分类号： B64C27/54

CPC分类号： B64C3/52 ,  B64C3/48 ,  B64C3/50 ,  B64C9/16 ,  B64C9/22 ,  B64C27/473 ,  B64C27/72 ,  Y02T50/34 ,  Y10T74/18056 ,  Y10T74/18288

摘要： An edge mo&phgr;hing arrangement for an airfoil having upper and lower control surfaces is provided with a rib element arranged to overlie the edge of the airfoil. The rib element has first and second rib portions arranged to communicate with respectively associated ones of the upper and lower control surfaces of the airfoil. A first compliant linkage element has first and second ends and is disposed between the first and second rib portions of the rib element, the first and second ends are each coupled to the interior of a respectively associated one of the first and second rib portions. There is additionally provided a driving link having first and second driving link ends, the first driving link end being coupled to the interior of a selectable one of the first and second rib portions.

公开(公告)号：EP3323712A1

公开(公告)日：2018-05-23

申请号：EP17202633.8

申请日：2017-11-20

申请人： The Boeing Company

发明人： CURRIE, Andrew S. ,  SANDERS, Tony

IPC分类号： B64C9/02 ,  B64C9/18

CPC分类号： B64C9/02 ,  B64C3/50 ,  B64C9/18 ,  F16C11/04 ,  Y02T50/32 ,  Y02T50/44

摘要： Aerodynamic drag associated with a flap hinge assembly (30) used to pivotally mount a flap (17) to the trailing edge (22) of an aircraft (10) wing (14) can be reduced when the cross-sectional area of the hinge fairing (24) which surrounds the flap hinge assembly is reduced in size. The reduction in cross-sectional area of the hinge fairing is enabled when the flap hinge assembly attachment footprint to the underside of the flap box is also reduced. The flap hinge assembly has an internal support rib (66) positioned between spars of the flap box structure internal to the skin, a hinge fitting (44) exhibiting an actuation point (50) and a hinge point (52) positioned proximate a front spar (60) of the flap box structure external to the skin, and a link (68) passing through an aperture (70) in the lower skin (46) of the flap and coupling the internal support rib to the hinge fitting.

公开(公告)号：EP3307618A1

公开(公告)日：2018-04-18

申请号：EP16727850.6

申请日：2016-06-07

申请人： Bombardier Inc. ,  Short Brothers Plc

发明人： OUELLETTE, Benoit

IPC分类号： B64C3/44 ,  B64C3/50 ,  B64C9/16 ,  B64C9/22 ,  B64D45/00

CPC分类号： B64D45/0005 ,  B64C3/44 ,  B64C3/50 ,  B64C9/16 ,  B64C9/22 ,  B64D43/00

摘要： Systems, devices and methods a for use with one or more high-lift flight control surfaces (24) of aircraft are disclosed. One exemplary method comprises receiving data representative of a commanded configuration (48) for a high-lift flight control surface (24); and on a display device (14) of the aircraft, showing an indicator (30) indicating the commanded configuration and a corresponding commanded position (50) for the high-lift flight control surface (24). The indicator (30) graphically indicates a correlation between the commanded configuration (48) and the corresponding commanded position (50) for the high-lift flight control surface (24).

公开(公告)号：EP3112259A1

公开(公告)日：2017-01-04

申请号：EP16169854.3

申请日：2016-05-17

申请人： The Boeing Company

发明人： SALMON, Huw James ,  GOMEZ, Roberto J.

IPC分类号： B64C3/50 ,  B64C7/02 ,  B64C9/24

CPC分类号： B64C9/22 ,  B64C3/48 ,  B64C3/50 ,  B64C7/02 ,  B64C9/24 ,  Y02T50/14 ,  Y02T50/32

摘要： Systems and methods according to one or more embodiments are provided for a Krueger flap (104) assembly with dual Krueger seal assemblies (310,312). In certain embodiments, the dual Krueger seal assemblies (310,312) may seal a space between a Krueger flap main body (104) and an aircraft engine (108). Further seals may be provided to seal any gaps between the dual Krueger seal assemblies (310,312). In certain embodiments, one or both of the dual Krueger seal assemblies (310,312) may include centrally grounded springs (418a,418b,420a,420b). The dual Krueger seal assemblies may include a plurality of springs supporting each Krueger seal assembly.

摘要翻译： 根据一个或多个实施例的系统和方法被提供用于具有双Krueger密封组件（310,312）的Krueger翼片（104）组件。 在某些实施例中，双Krueger密封组件（310,312）可以密封克鲁格翼片主体（104）和飞机发动机（108）之间的空间。 可以提供进一步的密封以密封双克鲁格密封组件（310,312）之间的任何间隙。 在某些实施例中，双Krueger密封组件（310,312）中的一个或两个可以包括中心接地的弹簧（418a，418b，420a，420b）。 双Krueger密封组件可以包括支撑每个Krueger密封组件的多个弹簧。

公开(公告)号：EP2923943B1

公开(公告)日：2017-01-04

申请号：EP15156160.2

申请日：2015-02-23

申请人： The Boeing Company

发明人： Zeon, Young L ,  Achtner, Gerfried R ,  Lee, Robert Michael

IPC分类号： B64C3/50 ,  B64C7/00 ,  B64C9/02 ,  F16J15/02

CPC分类号： B64C1/38 ,  B64C3/50 ,  B64C7/00 ,  B64C9/02 ,  F16J15/027 ,  Y02T50/14 ,  Y02T50/32

摘要： A system and method for reducing aerodynamic drag is disclosed. A compression seal is attached to the inboard edges of the stabilizer and elevators of an airplane. The seal blocks airflow in a gap located between these inboard edges and a fuselage. The shape of the compression seal changes as the shape of the gap changes due to movement of the stabilizer and elevators during flight to effectively block airflow through the gap during flight. By blocking the airflow, the seal reduces the aerodynamic drag of the airplane.

摘要翻译： 公开了一种减小气动阻力的系统和方法。 压缩密封件附接到飞机的稳定器和电梯的内侧边缘。 密封件阻挡位于这些内侧边缘和机身之间的间隙中的气流。 压缩密封件的形状随着在飞行期间由于稳定器和电梯的运动而改变间隙的形状而改变，以有效地阻挡在飞行中通过间隙的气流。 通过阻塞气流，密封件可以减少飞机的空气动力学阻力。

公开(公告)号：EP2952429A1

公开(公告)日：2015-12-09

申请号：EP15165345.8

申请日：2015-04-28

申请人： The Boeing Company

发明人： Jamison, Flint M ,  Amorosi, Stephen R ,  Klein, Michael K

IPC分类号： B64C3/38 ,  B64C3/14 ,  B64C3/28

CPC分类号： B64C13/24 ,  B64C3/28 ,  B64C3/38 ,  B64C3/50 ,  B64C9/02 ,  B64C9/16 ,  B64C2003/147 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/32 ,  Y02T50/44

摘要： A wing (130) includes a trailing edge, which may include a moveable flight control surface (230), and a divergent trailing edge device (240) slideable along an aft surface of the trailing edge or moveable flight control surface (230) between a stowed position and a fully deployed position. The divergent trailing edge device (240) is located entirely within the trailing edge or moveable flight control surface (230) when stowed, and it increases lift over drag of the wing (130) when deployed.

摘要翻译： 机翼（130）包括后缘，其可以包括可移动的飞行控制表面（230），以及沿着后缘或可移动飞行控制表面（230）的后表面可滑动的发散后缘装置（240） 收起位置和充分部署的位置。 发散后缘装置（240）在收起时完全位于后缘或可移动飞行控制表面（230）内，并且当展开时它增加了机翼（130）的拖动力。

公开(公告)号：EP2552775B1

公开(公告)日：2015-04-29

申请号：EP11707055.7

申请日：2011-02-28

申请人： The Boeing Company

发明人： SHMILOVICH, Arvin ,  YADLIN, Yoram

IPC分类号： B64C3/50 ,  B64C9/24 ,  B64C9/14

CPC分类号： B64C3/50 ,  B64C9/24 ,  B64C2009/143 ,  B64C2230/14 ,  Y02T50/14 ,  Y02T50/166 ,  Y02T50/32

摘要： Concepts and technologies described herein provide for a low noise aircraft wing slat system. According to one aspect of the disclosure provided herein, a cove-filled wing slat is used in conjunction with a moveable leading edge element of an aircraft wing to provide a high lift system. The moveable leading edge element may include a one-piece or two-piece panel that retracts within the aircraft wing to accommodate the cove-filled slat in the stowed position. Upon deployment of the cove-filled slat, the moveable leading edge element deploys outward to create a continuous outer mold line shape with the wing.

公开(公告)号：EP2733063A1

公开(公告)日：2014-05-21

申请号：EP13192160.3

申请日：2013-11-08

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

发明人： Heintze, Dr. Olaf ,  Kintscher, Markus

IPC分类号： B64C3/52 ,  B64C9/24

CPC分类号： B64C3/50 ,  B64C2003/445

摘要： Bei einer Flügelvorderkante (1) mit einer verformbaren Haut (2), die an ihren beiden Enden (3, 4) an eine tragende Struktur (8) angeschlossen ist und die einen Faserverbund mit Verstärkungsfasern in unterschiedlicher Orientierung aufweist, und mit mindestens einem in der Flügelvorderkante (1) wirksamen Aktuator (10), mit dem die Haut (2) in einem längs der Flügelvorderkante (1) verlaufenden Bereich (7) gegenüber der tragenden Struktur (8) auslenkbar ist, um die Flügelvorderkante (1) umzuformen, weist der Faserverbund im Bereich einer neutralen Faser der Haut (2) eine schubweiche Zwischenlage aus Elastomerwerkstoff (28) auf.

摘要翻译： 机翼前缘（1）具有可变形壳体（2），其在其两端（3,4）处连接到支撑结构（8）。 纤维复合材料在外壳的中性纤维区域具有剪切柔性中间层。 剪切柔性中间层由弹性体材料制成。 壳体两端的复合纤维的增强纤维面密度降低到机翼前缘的前区域（21）。

公开(公告)号：EP2727825A1

公开(公告)日：2014-05-07

申请号：EP12425175.2

申请日：2012-10-30

申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.

发明人： Ameduri, Salvatore

IPC分类号： B64C3/50 ,  B64C3/48

CPC分类号： B64C3/48 ,  B64C3/50 ,  Y02T50/14

摘要： A device (1) for varying a geometry of a wing profile for leading edges of wings (2) of aircraft (100) comprising an exposed surface (8) extending parallel to the longitudinal development direction of the wing (2); the exposed surface (8) defines a front portion of the wing profile (9) of the wing (2), exhibits a first and a second engaging portion (6, 7) constrained stably to the wing (2) and a deformable portion (5) interposed between the first and the second engaging portions (6, 7) and mobile in relation to the wing (2) such as to enable variations in shape of the portion of wing profile (9) of the wing (2), The device (1) comprises a mechanism (10), arranged internally of a housing compartment (9a) of the wing profile, configured such as to move relatively to the wing along at least a plane that is transversal to the main development direction thereof and such as to generate a deformation of the deformable portion (5). The device (1) comprises an activating element (13) configured such as to move the mechanism (10) and provided with an actuator (14) configured such as to generate a push (S) and a kinematic mechanism (28) receiving the push (S) generated by the actuator (14) and configured such as to move the mechanism (10). The actuator (14) is positioned and configured such as to generate a push (S) in a transversal direction to the movement plane of the mechanism (10) and the kinematic mechanism (28) generates a corresponding action on the mechanism (10) such as to move the mechanism (10) in the movement plane thereof transversal to the main development direction (A).

摘要翻译： 1.一种用于改变飞行器（100）的翼（2）的前缘的翼型的几何形状的装置（1），包括平行于所述翼（2）的纵向展开方向延伸的暴露表面（8）。 暴露表面（8）限定翼（2）的翼型（9）的前部，其表现出稳定地约束到翼（2）的第一和第二接合部分（6,7）和可变形部分 5），其插入在第一和第二接合部分（6,7）之间并相对于机翼（2）可移动，以使得翼（2）的翼型（9）的部分的形状能够变化。 装置（1）包括机构（10），其布置在机翼轮廓的壳体隔室（9a）的内部，其被构造为沿着至少沿其主显影方向横切的平面相对于翼移动， 以产生可变形部分（5）的变形。 所述装置（1）包括一个致动元件（13），其构造成使所述机构（10）移动并设置有致动器（14），所述致动器构造成用于产生推动件（S）和运动机构（28） （14）产生并且构造成使得所述机构（10）移动。 致动器（14）的定位和构造使得沿着横向于机构（10）的运动平面的方向产生推动（S），并且运动机构（28）产生对机构（10）的相应作用， 以使机构（10）沿其移动平面横向于主显影方向（A）移动。

公开(公告)号：EP2726372A2

公开(公告)日：2014-05-07

申请号：EP12743671.5

申请日：2012-06-28

申请人： Airbus Operations GmbH

发明人： SCHLIPF, Bernhard ,  TRIEBL, Carsten

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

CPC分类号： B64C9/02 ,  B64C3/50 ,  B64C9/22 ,  B64C9/24 ,  Y02T50/14 ,  Y02T50/32

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.