公开(公告)号：EP3201075A4

公开(公告)日：2018-02-28

申请号：EP14903033

申请日：2014-09-29

申请人： BOEING CO

发明人： REUSCH DAVID C

IPC分类号： B64C3/18

CPC分类号： B64C3/18 ,  B64C3/00 ,  B64C3/14 ,  B64C3/185 ,  B64C5/02 ,  B64C9/02 ,  B64C13/00 ,  B64C2003/142

摘要： An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

公开(公告)号：EP3261835A1

公开(公告)日：2018-01-03

申请号：EP16754710.8

申请日：2016-02-25

申请人： Church, Ryan

发明人： Church, Ryan

IPC分类号： B32B9/02 ,  B33Y10/00 ,  B33Y70/00 ,  C12N1/16 ,  C12P1/00 ,  F03D80/00 ,  C12N9/80 ,  C12N11/00

CPC分类号： B32B9/02 ,  B33Y10/00 ,  B33Y70/00 ,  B64C3/00 ,  C12N1/16 ,  C12N9/80 ,  C12N11/00 ,  C12P1/00 ,  F01D5/147 ,  F01D21/003 ,  F03D1/065 ,  F03D1/0675 ,  F03D13/10 ,  F05B2230/30 ,  F05B2230/50 ,  F05B2230/80 ,  F05B2240/21 ,  F05B2240/57 ,  F05B2270/107 ,  F05B2270/17 ,  F05B2270/301 ,  Y02B10/30 ,  Y02E10/721 ,  Y02P70/523

摘要： A structure adapted to traverse a fluid environment exerting an ambient fluid pressure is provided. The structure includes an elongate body extending from a root to a wingtip and encapsulating at least one interior volume containing an interior fluid exerting an interior fluid pressure that is different from the ambient fluid pressure. A method of retrofitting a structure adapted to traverse a fluid environment exerting an ambient fluid pressure, the structure comprising an elongate body extending from a root to a wingtip and having at least one interior volume is also provided. The method includes sealing the elongate body to encapsulate the at least one interior volume containing an interior fluid; associating at least one valve with the at least one interior volume; and modifying interior fluid content via the at least one valve to produce an interior fluid pressure that is different from the ambient fluid pressure.

公开(公告)号：EP2848519B1

公开(公告)日：2017-11-22

申请号：EP14172648.9

申请日：2014-06-17

申请人： The Boeing Company

发明人： Charles, Jordan Daniel ,  Hamada, Jason

IPC分类号： B64C1/26

CPC分类号： B64C1/26 ,  B64C3/00 ,  B64C3/182 ,  B64C3/187 ,  B64C2001/0072 ,  B64C2001/0081

摘要： An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. In some embodiments, outboard upper stringers may be configured differently than center upper stringers. In some embodiments, a subset of the center upper stringers may not directly oppose the outboard upper stringers. In other embodiments, for at least a substantial fore/aft span of the upper joint, each of the center upper stringers may directly oppose an outboard upper stringer. In particular the present invention relates to An upper joint for a wing assembly of an aircraft, the upper joint comprising: an outboard upper wing panel (24) of an outboard wing box (20, 22); a center upper wing panel (28) of a wing center section (18); a rib (32) that is located between the outboard wing box and the wing center section; and an upper joint assembly (38) operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib; wherein the upper joint assembly defines a mating plane (48) between the outboard wing box and the wing center section; wherein when the upper joint is in compression, the outboard upper wing panel expresses a compressive inward pressure toward the upper joint assembly; wherein when the upper joint is in compression, the center upper wing panel expresses a compressive outward pressure toward the upper joint assembly; and wherein a centroid (54) of the compressive inward pressure (50) across an acreage of the outboard upper wing panel when extended across the mating plane intersects the mating plane below or above where a centroid (56) of the compressive outward pressure (52) across an acreage of the center upper wing panel when extended across the mating plane intersects the mating plane.

公开(公告)号：EP3201075A1

公开(公告)日：2017-08-09

申请号：EP14903033.0

申请日：2014-09-29

申请人： The Boeing Company

发明人： REUSCH, David, C.

IPC分类号： B64C3/18

CPC分类号： B64C3/18 ,  B64C3/00 ,  B64C3/14 ,  B64C3/185 ,  B64C5/02 ,  B64C9/02 ,  B64C13/00 ,  B64C2003/142

摘要： An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

摘要翻译： 并入飞行器控制表面（10）中的空气动力学结构提供沿着控制表面的至少一部分在一个方向上延伸的翼梁（16），并且翼梁包括沿着控制表面的延伸方向上的多个弯曲部，以提供 空间以适应执行器配件或其他结构或操作要求。

公开(公告)号：EP3118112A1

公开(公告)日：2017-01-18

申请号：EP16177015.1

申请日：2016-06-29

申请人： Airbus Helicopters

发明人： TOULMAY, François

IPC分类号： B64C27/26 ,  B64C27/82

CPC分类号： B64C27/26 ,  B64C3/00 ,  B64C3/32 ,  B64C9/18 ,  B64C27/22 ,  B64C27/82 ,  B64C29/0025 ,  B64C2027/8236

摘要： La présente invention concerne un aéronef combiné (1) comportant un fuselage (2), un rotor principal (3), un dispositif anticouple principal (4) et deux ailes (11,11') positionnées de part et d'autre dudit fuselage (2). Chaque aile (11,11') comporte au moins un volet (12,12') mobile situé au niveau de son bord de fuite. Lesdits volets (12,12') peuvent être orientés de façon dissymétrique vis à vis d'un flux d'air généré en réaction à la portance dudit rotor principal (3) de part et d'autre dudit fuselage (2) afin de créer des efforts aérodynamiques longitudinaux de sens opposés de part et d'autre dudit fuselage (2) et, par suite, un couple complémentaire s'ajoutant au couple principal dudit dispositif anticouple principal (4).

摘要翻译： 具有机身，主转子，主抗扭矩装置和位于机身两侧的两个机翼的复合飞机。 每个翼片具有位于其后缘的至少一个活动翼片。 翼片可相对于机身两侧的主转子升力产生的空气流不对称地偏转，从而在机身两侧产生相反方向的纵向空气动力，从而产生额外的转矩， 被加到主反扭矩装置的主扭矩上。

公开(公告)号：EP3093128A1

公开(公告)日：2016-11-16

申请号：EP16169113.4

申请日：2016-05-11

申请人： Airbus Operations Limited

发明人： Price, Jonathan ,  Evans, Steven

IPC分类号： B29C70/30 ,  B32B27/12 ,  C08J5/24 ,  B29C70/54 ,  C08J5/04

CPC分类号： B29C70/34 ,  B29C53/382 ,  B29C70/08 ,  B29C70/30 ,  B29C70/382 ,  B29L2031/3076 ,  B29L2031/3085 ,  B32B3/00 ,  B32B3/04 ,  B32B27/00 ,  B32B27/06 ,  B32B27/12 ,  B32B37/06 ,  B32B37/10 ,  B32B2305/00 ,  B32B2305/72 ,  B32B2307/50 ,  B32B2405/00 ,  B32B2597/00 ,  B32B2605/18 ,  B64C1/06 ,  B64C3/00 ,  B64C3/18 ,  B64C5/02 ,  B64C2001/0072 ,  C08J5/042 ,  C08J5/24 ,  C08J2300/22 ,  C08J2300/24 ,  C08J2363/00 ,  Y02T50/43

摘要： A method of forming composite components is described in which a composite lay-up is created using varying fibre types across the lay-up. This can adapt the lay-up to forming processes in regions of the lay-up to be formed and uses fibre types which give the greatest strength benefits in areas which do not need to be formed. Regions not requiring forming may have binders in them activated prior to a forming step or steps, after which the formed regions may be impregnated with a matrix and the component cured.

摘要翻译： 描述了形成复合部件的方法，其中使用跨越层叠的不同纤维类型产生复合层叠。 这样可以适应形成层叠区域的成型工艺，并使用在不需要形成的区域中具有最大强度优势的纤维类型。 不需要成形的区域可以在其形成步骤或步骤之前具有活化的粘结剂，之后，可以用基质浸渍所形成的区域并使组分固化。

公开(公告)号：EP2878538B1

公开(公告)日：2016-05-18

申请号：EP14192431.6

申请日：2014-11-10

申请人： Rolls-Royce plc

发明人： Moxon, Matthew

IPC分类号： B64D27/12 ,  B64D27/24

CPC分类号： B64C23/005 ,  B64C3/00 ,  B64C3/28 ,  B64C9/18 ,  B64C11/00 ,  B64C39/00 ,  B64D27/10 ,  B64D27/12 ,  B64D27/24 ,  Y02T50/44 ,  Y02T50/64

公开(公告)号：EP2878538A1

公开(公告)日：2015-06-03

申请号：EP14192431.6

申请日：2014-11-10

申请人： Rolls-Royce plc

发明人： Moxon, Matthew

IPC分类号： B64D27/12 ,  B64D27/24

CPC分类号： B64C23/005 ,  B64C3/00 ,  B64C3/28 ,  B64C9/18 ,  B64C11/00 ,  B64C39/00 ,  B64D27/10 ,  B64D27/12 ,  B64D27/24 ,  Y02T50/44 ,  Y02T50/64

摘要： An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a centre of thrust (70) of the propulsors (46) on that wing (44).

摘要翻译： 一架飞机（40）。 飞机（40）包括推进系统，该推进系统包括一对内燃机（10），每个内燃机驱动电力发电机（56），每个电力发电机（56）电耦合到多个电力驱动的推进器（46）。 推进器（46）位于机翼（44）的前缘（45）的前方，使得由推进器产生的气流在使用中流过机翼（44）。 每个内燃机（10）和发电机（56）安装在翼（44）上的推进器（46）的推力（70）的中心外侧的相应翼（44）上。

公开(公告)号：EP2821340A1

公开(公告)日：2015-01-07

申请号：EP13754443.3

申请日：2013-02-14

申请人： Mitsubishi Heavy Industries, Ltd.

发明人： KASHIWAGI, Masahiro ,  NONAKA, Yoshinori ,  ABE, Toshio

IPC分类号： B64C1/14 ,  B29C70/06 ,  B64C1/12 ,  B64C3/26 ,  B29K105/08 ,  B29L31/30

CPC分类号： B64C1/1484 ,  B29C70/30 ,  B29L2031/3082 ,  B64C1/00 ,  B64C3/00 ,  B64C3/20 ,  B64C3/34 ,  B64C2001/0072 ,  B64F5/00 ,  B64F5/10 ,  Y02T50/43 ,  Y10T29/49801 ,  Y10T428/24273

摘要： There is provided a composite structure (3) formed of a composite member which extends in one direction, includes holes (5), and is made of fiber reinforced plastics. A tensile load and/or a compressive load are applied to the composite structure (3) in the one direction. Tensile stiffness and/or compression stiffness of peripheral areas (3a) of the holes (5) in the one direction is lower than tensile stiffness and/or compression stiffness of the other area (3b), which surrounds the peripheral areas (3a), in the one direction, and the width of the peripheral area (3a) in a direction orthogonal to the one direction is set to 1.1 times or less of the diameter of the hole (5) in the direction orthogonal to the one direction.

摘要翻译： 提供了形成有在一个方向延伸的复合构件的复合结构（3），包括：孔（5），并且由纤维增强塑料。 的拉伸载荷和/或压缩载荷在一个方向上施加到复合结构（3）。 在所述一个方向上的孔（5）的周边区域（3a）的拉伸刚度和/或压缩刚性比抗张挺度和/或其他区域（3b）中，其围绕周边区域的压缩刚度（3a）的下 在一个方向上，并且在一个方向上的周边区域（3a）的垂直于所述一个方向上的宽度被设定为1.1倍或更小的方向正交的一个方向上的孔（5）的直径的。

公开(公告)号：EP2799330A3

公开(公告)日：2014-12-17

申请号：EP14163491.5

申请日：2014-04-04

申请人： The Boeing Company

发明人： Campbell, Darrell. D., JR

IPC分类号： B64C11/20 ,  B64C3/00 ,  B64C23/06

CPC分类号： B64D45/00 ,  B64C3/00 ,  B64C21/00 ,  B64C23/065 ,  B64C23/069 ,  B64D2045/009 ,  Y02T50/164 ,  Y10T156/10

摘要： The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing.

摘要翻译： 本公开提供了一种用于翼型的保护装饰的系统，方法和装置。 在一个或多个实施例中，所公开的方法包括提供护套，并将护套施加到翼型件的表面。 在一个或多个实施例中，护套围绕翼型件的表面从翼型的前缘朝向翼型的后缘卷绕。 在至少一个实施例中，护套覆盖翼型的翼弦长度的大约50％至大约70％。 在一些实施方案中，护套由至少一种聚合物如聚氨酯和/或共聚物制成。 在一个或多个实施例中，翼型件是小翼，斜翼翼尖和/或机翼。