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公开(公告)号：US11780567B2
公开(公告)日：2023-10-10
申请号：US17297880
申请日：2019-12-18
CPC分类号： B64C23/072 , B64C3/38
摘要： An aircraft wing is disclosed including a closed surface wing tip device which includes an element or actuator within the wing tip for deforming/morphing the shape of the wing tip between geometrical configurations having different aerodynamic properties, for example including one with better overall fuel efficiency for a shorter journey and one with overall fuel efficiency better suited for a longer journey. The device includes a lower winglet with an essentially planar portion spaced apart from the main body of the wing by a blended transition region which is shaped such that the curvature of the local dihedral increases in the outboard direction. The device includes an upper aerofoil structure which with the winglet essentially forms the closed surface. There is also disclosed an aircraft wing tip device having a sigmoid shaped (e.g. S-shaped) aerofoil structure blending in with a main wing of the aircraft.
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公开(公告)号：US20230227149A1
公开(公告)日：2023-07-20
申请号：US17943060
申请日：2022-09-12
发明人： Nicholas R. Guida
CPC分类号： B64C23/072 , B64C5/10 , B64C13/16 , B64C23/076 , Y02T50/10
摘要： An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.
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公开(公告)号：US09889920B2
公开(公告)日：2018-02-13
申请号：US15045318
申请日：2016-02-17
发明人： Matthew Harding , Stefan Napier , Nicola Marongiu , Robert Ian Thompson , Nick Livings , Stephen Paul Briancourt , Sylvain Boye
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/14 , Y02T50/164
摘要： An aircraft wing comprises a fixed wing and a wing tip device at the tip thereof. The wing tip device is configurable between: a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce the span. The wing comprises an actuation assembly for moving the wing tip device. The actuation assembly is arranged to move the wing tip device in a two-stage movement comprising a first stage in which the wing tip device is translated away from the flight configuration in a linear movement only, and a second, subsequent stage, in which the wing tip device is rotated to the ground configuration.
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公开(公告)号：US09623960B2
公开(公告)日：2017-04-18
申请号：US13955639
申请日：2013-07-31
申请人： Gabor Devenyi
发明人： Gabor Devenyi
CPC分类号： B64C23/076 , B64C23/072 , B64C39/10 , Y02T50/164
摘要： The present invention relates to a wing for an aircraft. The wing includes a main wing section extending from an inboard end to an outboard end along a lateral axis of the wing, the inboard end for connecting the main wing section to the aircraft. The wing also includes a wing tip having a proximal end and a distal end, the wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely rotate about a wing tip rotational center with respect to the main wing section.
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公开(公告)号：US20170066528A1
公开(公告)日：2017-03-09
申请号：US15295262
申请日：2016-10-17
CPC分类号： B64C23/072 , B64C3/56 , Y02T50/164 , Y10T29/49826
摘要： A wing tip device for attachment to a wing tip of a powered aircraft including: a first mounting formation, a second mounting formation spaced apart in a spanwise direction relative to the first mounting formation, a third mounting formation spaced apart in a chordwise direction relative to the first and second mounting formations, wherein each of the first, second and third mounting formations are configured for attachment to at least one of a wing spar and a wing rib, and, at least one of the mounting formations is configured to permit movement of a portion of the wing tip device in the spanwise direction relative to a portion of the wing tip.
摘要翻译： 一种用于附接到动力飞行器的翼尖的翼尖装置，包括：第一安装结构，相对于第一安装结构沿翼展方向间隔开的第二安装结构，相对于第一安装结构沿着弦方向间隔开的第三安装结构 第一和第二安装结构，其中第一，第二和第三安装结构中的每一个被构造成用于附接到翼梁和翼肋中的至少一个，并且至少一个安装结构被构造成允许 所述翼尖装置的翼展方向的一部分相对于所述翼尖的一部分。
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公开(公告)号：US20170066521A1
公开(公告)日：2017-03-09
申请号：US15265258
申请日：2016-09-14
申请人： The Boeing Company
发明人： Stephen John Fox , Jan A. Kordel , Keith Townsend , Matthew August Lassen , Mark John Gardner , Mark Steven Good
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/14 , Y02T50/164 , Y02T50/54
摘要： An apparatus and method of a wing fold system may include a latch assembly rotating an unfixed portion of a wing, with respect to a fixed portion of the wing, between a flight position of the wing and a folded position of the wing. A first portion of the wing may hold a rotating portion of the latch assembly. A second portion of the wing may hold a secured portion of the latch assembly. The rotating portion of the latch assembly may rotate between an open position and a closed position. A slot in the rotating portion may receive the secured portion of the latch assembly. A securing portion of the rotating portion may secure a secured portion of the latch assembly. The latch assembly may prevent rotation of the second portion when the wing may be in the flight position.
摘要翻译： 机翼折叠系统的装置和方法可以包括闩锁组件，其相对于机翼的固定部分在机翼的飞行位置和机翼的折叠位置之间旋转机翼的未固定部分。 机翼的第一部分可以保持闩锁组件的旋转部分。 机翼的第二部分可以保持闩锁组件的固定部分。 闩锁组件的旋转部分可以在打开位置和关闭位置之间旋转。 旋转部分中的狭槽可以接收闩锁组件的固定部分。 旋转部分的固定部分可以固定闩锁组件的固定部分。 当机翼处于飞行位置时，闩锁组件可以防止第二部分的旋转。
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公开(公告)号：US20170043864A1
公开(公告)日：2017-02-16
申请号：US15306400
申请日：2015-04-02
发明人： Tim AXFORD , Tony FONG , Stuart ALEXANDER
CPC分类号： B64C23/072 , B64C3/185 , B64C3/54 , B64C3/546 , B64C3/56 , Y02T50/14 , Y02T50/164
摘要： An aircraft including a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded inwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (6) is connected to the wing along a hinge axis (14) by spar beams (10 and 12) of the wing tip device, one of the beams being mounted for pivoting about a fixed axis and the other beam being mounted on a spherical bearing (15) to provide greater freedom of movement. Various actuator arrangements may be provided to pivot the wing tip device.
摘要翻译： 一种包括翼（1）和翼尖装置（6）的飞机。 翼尖装置（6）可在飞行期间使用的飞行构型和在地面操作期间使用的地面配置之间移动。 在地面构造中，翼尖装置从飞行构造向内折叠，使得飞行器的跨度减小。 翼尖装置（6）通过翼尖装置的翼梁梁（10和12）沿着铰链轴线（14）连接到机翼，其中一个梁被安装用于围绕固定轴线枢转，另一个梁是 安装在球面轴承（15）上以提供更大的移动自由度。 可以提供各种致动器装置以枢转翼尖装置。
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公开(公告)号：US20170029094A1
公开(公告)日：2017-02-02
申请号：US15301489
申请日：2015-04-02
CPC分类号： B64C23/072 , B64C3/185 , B64C3/54 , B64C3/546 , B64C3/56 , Y02T50/14 , Y02T50/164
摘要： An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.
摘要翻译： 飞机机翼（1）具有与其连接的翼尖装置（3）。 翼尖装置（3）的根部（7）在第一连接（11）处连接到机翼（1）的末端。 外部支柱（9）在机翼（1）和翼尖装置（3）之间延伸，支柱（9）在第二连接（13）处连接到机翼（1）。 第二连接件（13）在第一连接件的内侧，使得在使用过程中产生的翼尖装置（3）上的载荷经由支柱（9）传递到位于内侧的机翼（1）上的位置 其中翼尖装置（3）的根部（7）连接到机翼的尖端。
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9.发明授权Concept of a variable winglet for lateral load reduction for combined lateral and vertical load reduction, and for improving the performance of means of locomotion 有权用于侧向负载减少的可变小翼的概念，用于组合的横向和垂直负载减少，以及用于改善运动手段的性能公开(公告)号：US08757555B2
公开(公告)日：2014-06-24
申请号：US11914411
申请日：2006-05-19
申请人： Vitalij Werthmann , Michael Kordt
发明人： Vitalij Werthmann , Michael Kordt
IPC分类号： B64C23/06
CPC分类号： B64C23/065 , B64C23/072 , Y02T50/164
摘要： A device for adapting aerodynamic characteristics of a wing element, includes a winglet, movably attachable to a wing element. The winglet or parts of the winglet may be rotatable in relation to the wing element such that an associated rotary axis with a main direction of extension of the wing element encompasses an angle that differs from an angle of 90°. In addition, a method is disclosed.
摘要翻译： 用于适应翼元件的空气动力特性的装置包括可移动地附接到翼元件的小翼。 小翼或小翼的部分可以相对于翼元件旋转，使得具有翼元件的主要延伸方向的相关联的旋转轴线包围与90°的角度不同的角度。 此外，公开了一种方法。
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10.发明申请METHOD OF COUPLING AEROFOIL SURFACE STRUCTURES AND AN AEROFOIL ASSEMBLY 有权耦合AEROFOIL表面结构和AEROFOIL组件的方法公开(公告)号：US20130336795A1
公开(公告)日：2013-12-19
申请号：US13907240
申请日：2013-05-31
发明人： Simon John PARKER
IPC分类号： B64C3/00
CPC分类号： B64C3/00 , B64C5/08 , B64C23/065 , B64C23/072 , Y02T50/164 , Y10T29/49337
摘要： A method of attaching first and second aerofoil sections to each other is disclosed. The method comprises the steps of: positioning one aerofoil section in an initial assembly orientation with respect to the other aerofoil section so that hinge elements on each aerofoil section are in alignment with each other, inserting a hinge shaft through said aligned hinge elements to initially couple the aerofoil sections together whilst the aerofoil sections are in their initial assembly orientation; and rotating one aerofoil section relative to the other aerofoil section about a compound angle defined by the hinge shaft into a second orientation in which the aerofoil sections are in their final, assembled orientation relative to each other. An aerofoil assembly is also disclosed.
摘要翻译： 公开了将第一和第二机翼部分相互连接的方法。 该方法包括以下步骤：将一个机翼部分相对于另一机翼部分以初始组装方向定位，使得每个机翼部分上的铰链元件彼此对准，将铰链轴穿过所述对准的铰链元件以开始耦合 机翼部分在一起，而机翼部分处于其初始组装方向; 并且围绕由铰链轴限定的复合角度将一个机翼部分相对于另一机翼部分旋转成第二取向，其中机翼部分相对于彼此处于其最终的组装取向。 还公开了机翼组件。
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