公开(公告)号：US20140008487A1

公开(公告)日：2014-01-09

申请号：US13710323

申请日：2012-12-10

Applicant: Singapore Technologies Aerospace LTD

Inventor： Yong Wee Liu ,  Hian Beng Kek

IPC: B64C3/56

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102

Abstract: Disclosed herein is a collapsible wing assembly of an unmanned aerial vehicle (UAV) and a method of locking and unlocking the collapsible wing assembly of an unmanned aerial vehicle (UAV). The collapsible wing assembly comprising a centre wing adapted to be attached to the fuselage; and a pair of outboard wings, wherein each of the outboard edges of the centre wing comprises a first attachment structure, and each of the inboard edges of the outboard wings comprises a second attachment structure, wherein the first attachment structure is operable to engage with the second attachment structure and displace the second attachment structure to a captive position towards the trailing edge of the centre wing.

Abstract translation: 本文公开了一种无人飞行器（UAV）的可折叠翼组件以及锁定和解锁无人机（UAV）的可折叠翼组件的方法。 可折叠翼组件包括适于附接到机身的中心翼; 以及一对外侧翼，其中所述中心翼的所述外侧边缘中的每一个包括第一附接结构，并且所述外侧翼的每个内侧边缘包括第二附接结构，其中所述第一附接结构可操作以与 第二附接结构，并且使第二附接结构朝向中心翼的后缘移动到捕获位置。

公开(公告)号：US20130206921A1

公开(公告)日：2013-08-15

申请号：US13397569

申请日：2012-02-15

Applicant: James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler

Inventor： James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler

IPC: B64C29/00

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

公开(公告)号：US08492692B2

公开(公告)日：2013-07-23

申请号：US13097394

申请日：2011-04-29

Applicant: Jeremy F. Fisher

Inventor： Jeremy F. Fisher

IPC: F42B12/56 ,  F42B15/01 ,  F42B15/08 ,  H04B1/59 ,  F42B15/00 ,  H04B1/00

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

公开(公告)号：US20130099050A1

公开(公告)日：2013-04-25

申请号：US13278477

申请日：2011-10-21

Applicant: Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

Inventor： Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

IPC: B64C3/56 ,  B64C3/38

CPC classification number: B64C3/56 ,  B64C2201/102

Abstract: An aircraft wing has hinged ribs, and a skin covering the ribs. The ribs each include plural rib sections, array from the leading edge of the wing, to the trailing edge of the wing, and a lock to hold the rib sections together in a deployed state or condition. The wings are initially in a stowed state, with the ribs and the rib sections having a curved chord, and deploy to the deployed state, in which the ribs have a straightened chord that defines an airfoil state. The wing may have foam material between the ribs to allow the wings to expand in the wingspan direction, for instance after the ribs have been placed in the deployed state.

Abstract translation: 飞机机翼有铰链肋骨和覆盖肋骨的皮肤。 肋条各自包括从翼的前缘到翼的后缘阵列的多个肋部，以及在展开状态或状态下将肋部保持在一起的锁。 翼部最初处于收起状态，肋和肋部具有弯曲的弦，并且部署到展开状态，其中肋具有限定翼型状态的拉直弦。 机翼可以在肋之间具有泡沫材料，以允许翼在翼展方向上膨胀，例如在肋已经处于展开状态之后。

公开(公告)号：US08376279B2

公开(公告)日：2013-02-19

申请号：US12358036

申请日：2009-01-22

Applicant: Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Tomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

Inventor： Robert Parks ,  Adam Woodworth ,  Peter Lively ,  Tomas Vaneck ,  Kimberly Kohlhepp ,  Justin McClellan

IPC: B64C3/56

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/127

Abstract: A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

公开(公告)号：US20120280080A1

公开(公告)日：2012-11-08

申请号：US13462422

申请日：2012-05-02

Applicant: Jacob G. LUBENOW ,  Andrew S. McComas ,  Jeremy A. Zanzig ,  Jeffrey A. Gerhart ,  Alan R. Klug ,  Jonathan P. Clark

Inventor： Jacob G. LUBENOW ,  Andrew S. McComas ,  Jeremy A. Zanzig ,  Jeffrey A. Gerhart ,  Alan R. Klug ,  Jonathan P. Clark

IPC: B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102

Abstract: A folding wing for an aircraft comprises first and second inboard wing sections, and first and second outboard wing sections. The first and second inboard wing sections rotate about a centerline hinge, and a centerline spring applies force to the first and second inboard wing sections to rotate the first and second inboard wing sections from a stowed position to a deployed position. At least one of the first and second inboard wing sections translates along the axis of rotation of the first and second inboard wing sections as they move from the stowed to the deployed positions. The first and second outboard wing sections rotate between the stowed and the deployed positions about first and second outboard hinges.

Abstract translation: 用于飞机的折翼包括第一和第二内侧翼部，以及第一和第二外侧翼部。 第一和第二内侧翼部围绕中心线铰链旋转，并且中心线弹簧对第一和第二内侧翼部施加力，以将第一和第二内侧翼部从收起位置旋转到展开位置。 第一和第二内侧翼部分中的至少一个在它们从收起的位置移动到展开位置时沿着第一和第二内侧翼部的旋转轴线平移。 第一和第二外侧翼部分围绕第一和第二外侧铰链在收起和展开位置之间旋转。

公开(公告)号：US08201773B1

公开(公告)日：2012-06-19

申请号：US12167075

申请日：2008-07-02

Applicant: Jayson T. Durham ,  Joshua Blanchi

Inventor： Jayson T. Durham ,  Joshua Blanchi

IPC: B64C3/56

CPC classification number: B64C39/028 ,  B64C2201/102

Abstract: A composite flexible and aerodynamic load bearing wing structure suitable for compact unmanned vehicles, is described. Flexible printed circuitry and micro fuel cells can be incorporated as, or part of, the flexible aerodynamic structure. Accordingly, the overall system configuration can be optimized with respect to weight, space and size requirements. The flexible aerodynamic structure for the unmanned vehicle may be configured with a flexible dielectric substrate having an electrical contact on at least one surface of the substrate, and a flexible printed circuit disposed upon the substrate. The printed circuit can flex with the substrate and the substrate, with the printed circuit, to form a load lifting aerodynamic wing configuration when unfolded from a folded position.

Abstract translation: 描述了适用于紧凑型无人驾驶车辆的复合柔性和空气动力学承载翼结构。 柔性印刷电路和微型燃料电池可以作为柔性空气动力学结构的一部分或部分结合。 因此，可以根据重量，空间和尺寸要求优化整个系统配置。 用于无人驾驶车辆的柔性空气动力学结构可以配置有在基板的至少一个表面上具有电接触的柔性电介质基板和设置在基板上的柔性印刷电路。 印刷电路可以利用印刷电路与基板和基板一起弯曲，以在从折叠位置展开时形成负载提升空气动力学翼结构。

公开(公告)号：US08089034B2

公开(公告)日：2012-01-03

申请号：US12425844

申请日：2009-04-17

Applicant: Robert E. Hammerquist

Inventor： Robert E. Hammerquist

IPC: F42B10/00

CPC classification number: B64C3/56 ,  B64C2201/102 ,  F42B10/14

Abstract: A wing pivot mechanism that is configured to pivot two wings about a single pivot axis of a vehicle, such as an aircraft. The wing pivot mechanism includes a hub, a set of gears positioned at least partially within an interior region of the hub, and two wings that are rotatably connected to the hub. Each wings includes a gear surface extending therefrom. Each gear of the hub assembly engages a gear of a respective wing such that rotation of the gears of the hub assembly causes rotation of the gears of the wings and pivoting of the wings about the single pivot axis in opposite rotational directions between a stowed position and a deployed position. A releasable locking mechanism is provided for locking the wings in a fixed rotational position in both the deployed position and the stowed position.

Abstract translation: 翼部枢转机构，其构造成围绕诸如飞机的车辆的单个枢转轴线枢转两个翼。 翼枢转机构包括轮毂，至少部分地定位在轮毂的内部区域内的一组齿轮，以及可旋转地连接到轮毂的两个翼。 每个翼包括从其延伸的齿轮表面。 轮毂组件的每个齿轮接合相应机翼的齿轮，使得轮毂组件的齿轮的旋转引起机翼的齿轮的旋转，并且机翼围绕单个枢转轴线以相反的旋转方向在收起位置和 部署位置。 提供了可释放的锁定机构，用于将翼片在展开位置和收起位置两者中固定在固定的旋转位置。

公开(公告)号：US07975774B2

公开(公告)日：2011-07-12

申请号：US12210130

申请日：2008-09-12

Applicant: Osman Ersed Akcasu

Inventor： Osman Ersed Akcasu

IPC: A62C35/02 ,  A62C8/00 ,  A62C27/00 ,  A62C37/10 ,  A62C31/22 ,  F42B10/00

CPC classification number: F41G7/30 ,  A62C3/025 ,  A62C99/009 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/145 ,  B64D1/16 ,  F41G7/346 ,  F41G7/36 ,  F42B12/36 ,  F42B12/50 ,  F42B15/105

Abstract: A guided fire-retardant-containing bomb comprises a container with retractable wings, tail and elevators having the form factor of a conventional release vehicle, where the control surfaces are coupled via a controller to a GPS with inertial guidance control and an ability to receive external instructions, and a charge core to disintegrate and disperse the fire retardant or water.

Abstract translation: 引导阻燃的炸弹包括具有伸缩翼的容器，具有常规释放车辆的形状因子的尾部和电梯，其中控制表面通过控制器耦合到具有惯性引导控制的GPS并具有接收外部的能力 说明书和电荷核心，以分解和分散阻燃剂或水。

公开(公告)号：US20100282917A1

公开(公告)日：2010-11-11

申请号：US11707088

申请日：2007-02-16

Applicant: Hank O'Shea

Inventor： Hank O'Shea

IPC: B64C3/54 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/102

Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

Abstract translation: 本发明的实施例涉及用于配置以调整响应于飞行任务参数车辆纵横比的飞行器的机翼结构。 机翼装置可以包括一对能够在部署到第一翅位置限定第一长宽比的翼组件。 每个翼组件可以具有一个向前内侧机翼枢转地连接到机身和后部内侧机翼枢转地连接到托架上。 前向内侧机翼和每个组件的后部内侧机翼可以连接，形成一个双平面结构。 另外，所述各组件可以包括一组翼外侧配置从内侧翼伸缩到伸出位置翅限定第二纵横比大于第一纵横比更大的。