公开(公告)号：US20240208637A1

公开(公告)日：2024-06-27

申请号：US18426110

申请日：2024-01-29

申请人： Anduril Industries, Inc.

发明人： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC分类号： B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/02 ,  B64U10/25 ,  B64U30/12 ,  B64U101/00 ,  B64U101/30

CPC分类号： B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2211/00 ,  B64U10/25 ,  B64U30/12 ,  B64U2101/00 ,  B64U2101/30 ,  Y02T50/10 ,  Y02T50/40

摘要： An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one precondition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one precondition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one precondition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

公开(公告)号：US11738854B2

公开(公告)日：2023-08-29

申请号：US17296205

申请日：2019-12-02

申请人： AIRBUS OPERATIONS LIMITED

发明人： Richard Lowry ,  Neil John Lyons

IPC分类号： B64C7/00 ,  B64C23/06 ,  B64C3/54 ,  B64C21/08

CPC分类号： B64C7/00 ,  B64C3/546 ,  B64C21/08 ,  B64C23/072

摘要： An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a rear portion with a concave surface, such that the fairing acts as a lift-generating surface when the aircraft is in flight.

公开(公告)号：US20180170516A1

公开(公告)日：2018-06-21

申请号：US15383873

申请日：2016-12-19

申请人： The Boeing Company

发明人： Aaron Niemiec ,  Adam Michael Honse ,  Gregory James Garmire ,  Mike Andrew Hritzo

IPC分类号： B64C3/54 ,  B64C3/56 ,  B64D45/00

CPC分类号： B64C3/546 ,  B64C3/56 ,  B64C23/072 ,  B64D45/0005 ,  Y02T50/14 ,  Y02T50/164

摘要： Methods, apparatus, and articles of manufacture to control and monitor a folding wingtip actuation system are disclosed. An example apparatus includes a collection module to obtain flight stage information of an aircraft. The example apparatus further includes a sequence and control module to calculate a first position of a folding wingtip assembly operatively coupled to a wing of the aircraft, determine actions during a first stage and a second stage to complete in sequence to move the folding wingtip assembly, determine a status of a component of the folding wingtip assembly based on a measurement of a sensor, and control a movement of the folding wingtip assembly in accordance with the actions and based on the status.

公开(公告)号：US09902488B2

公开(公告)日：2018-02-27

申请号：US15388396

申请日：2016-12-22

申请人： Area- I Inc.

发明人： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC分类号： B64C3/54 ,  B64C39/02 ,  B64C13/30 ,  B64C3/56

CPC分类号： B64C3/40 ,  B64C1/36 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C11/28 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2211/00 ,  Y02T50/14 ,  Y02T50/44

摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

公开(公告)号：US20170291686A1

公开(公告)日：2017-10-12

申请号：US15388433

申请日：2016-12-22

申请人： Area- I Inc.

发明人： Nicholas Robert Alley ,  Joshua Lemming Steele ,  Jesse Owen Williams ,  Daniel Kuehme ,  Jonathan Caleb Phillips

IPC分类号： B64C5/12 ,  B64C3/56 ,  B64C3/54 ,  B64C39/02 ,  B64C5/02

CPC分类号： B64C3/40 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  B64C5/02 ,  B64C5/12 ,  B64C5/16 ,  B64C13/24 ,  B64C13/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/12 ,  B64C2211/00

摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

公开(公告)号：US09254916B2

公开(公告)日：2016-02-09

申请号：US14128992

申请日：2012-06-06

申请人： Zhaoxi Yang

发明人： Zhaoxi Yang

IPC分类号： B64C29/00 ,  B64C37/00 ,  B64C3/54 ,  B64C39/04

CPC分类号： B64C37/00 ,  B64C3/546 ,  B64C29/00 ,  B64C29/0033 ,  B64C39/04

摘要： A vertical take-off and landing aircraft with tiltable power for use on land and in the air includes: a body (3) provided with a drive device; wheels (8) being controlled to make the body move on the ground; and a front thruster (1) and a rear thruster (2) controlling the body to fly or take off/land, wherein transmission brace rods (5) are arranged on both sides of the body, and a first pivot (9) passes transversely through the body and is connected to the transmission brace rods on both sides of the body; wherein the front thruster is fixed on front ends of the transmission brace rods, and the rear thruster is fixed on rear ends of the transmission brace rods; wherein the central axes of the front and rear thrusters are perpendicular to the plane formed by the two transmission brace rods. By controlling a tilting angle of the front/rear thrusters, this aircraft has two basic functions of vertical take-off/landing and horizontal flight, so as to facilitate conversion between land travel and air flight. During flight in the air, the aircraft body always remains in horizontal state, thereby making the occupants feel comfortable and providing them with broad vision so as to operate the aircraft safely.

摘要翻译： 具有可在陆上和空中使用的可倾斜动力的垂直起降飞机包括：设有驱动装置的主体（3）; 控制车轮（8）使身体在地面上移动; 和前推进器（1）和后推进器（2），其控制身体飞行或脱落/着陆，其中传动支杆（5）布置在主体的两侧，并且第一枢轴（9）横向通过 通过身体连接到身体两侧的传动支杆; 其特征在于，前推进器固定在传动支杆的前端，后推进器固定在传动支杆的后端; 其中前推进器和后推进器的中心轴线垂直于由两个变速器支撑杆形成的平面。 通过控制前后推进器的倾斜角度，该飞机具有垂直起飞/着陆和水平飞行两个基本功能，以便于陆上旅行和空中飞行之间的转换。 在空中飞行时，飞机机身总是保持水平状态，从而使乘客感到舒适，并为他们提供了广阔的视野，以便安全地操作飞机。

公开(公告)号：US20150047337A1

公开(公告)日：2015-02-19

申请号：US13751247

申请日：2013-01-28

申请人： Toyota Motor Engineering & Manufacturing North America, Inc.

发明人： Umesh N. Gandhi

IPC分类号： B64C3/36 ,  B64C3/54

CPC分类号： B64C3/36 ,  B64C3/44 ,  B64C3/546 ,  B64C2003/445 ,  B64C2003/543 ,  Y10T29/49826

摘要： An apparatus and methods for changing the shape of a wing using a plurality of morphing structures. One example method includes coupling a plurality of morphing structures to each other. Each morphing structure includes an anchor, a plurality of hinges, a plurality of shape-memory alloy members wherein each shape-memory alloy member extends from the anchor to a different hinge, a plurality of springs wherein each spring extends from the anchor to a different hinge, and a plurality of rigid members wherein each rigid member extends between two hinges. The method further includes actuating the plurality of shape-memory alloy members in at least some of the morphing structures wherein the shape-memory alloy members contract when actuated to pull against the hinges and anchors within the actuated morphing structures to rotate the rigid members and change the shape of the actuated morphing structure.

摘要翻译： 一种用于使用多个变形结构来改变机翼的形状的装置和方法。 一个示例性方法包括将多个变形结构彼此耦合。 每个变形结构包括锚，多个铰链，多个形状记忆合金构件，其中每个形状记忆合金构件从锚固件延伸到不同的铰链，多个弹簧，其中每个弹簧从锚固件延伸到不同的 铰链和多个刚性构件，其中每个刚性构件在两个铰链之间延伸。 该方法还包括在至少一些变形结构中致动多个形状记忆合金构件，其中形状记忆合金构件被致动时收缩以抵抗致动变形结构内的铰链和锚定件旋转，从而使刚性构件转动 激活的变形结构的形状。

公开(公告)号：US961925A

公开(公告)日：1910-06-21

申请号：US1910549527

申请日：1910-03-15

申请人： WUERTH FREDERICK W

发明人： WUERTH FREDERICK W

CPC分类号： B64C3/546

公开(公告)号：US20240286730A1

公开(公告)日：2024-08-29

申请号：US18575216

申请日：2022-07-06

申请人： Japan Aerospace Exploration Agency

发明人： Daichi WADA

IPC分类号： B64C3/54 ,  G05D1/654 ,  G05D101/15 ,  G05D109/22

CPC分类号： B64C3/546 ,  G05D1/654 ,  B64C2003/543 ,  G05D2101/15 ,  G05D2109/23

摘要： A morphing wing (140) of the present invention includes a link mechanism configured to be deployed in a first direction and retracted in a second direction opposite to the first direction, a plurality of front wing covers (180) mounted on a front side which is one side of the link mechanism perpendicular to the first direction, and a plurality of flight feathers (160) mounted on a rear side which is the other side of the link mechanism perpendicular to the first direction, wherein the front wing covers (180) and the flight feathers (160) are streamlined from the front side toward the rear side, and when the link mechanism is retracted, the flight feathers (160) are retracted inside the adjacent flight feathers (160).

公开(公告)号：US11993372B2

公开(公告)日：2024-05-28

申请号：US17637252

申请日：2020-07-20

申请人： Japan Aerospace Exploration Agency

发明人： Daichi Wada

IPC分类号： B64C3/54 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06

CPC分类号： B64C3/546 ,  B64C9/02 ,  B64C9/04 ,  B64C9/06 ,  B64C2003/543

摘要： A morphing wing includes a pantograph mechanism capable of being extended and contracted in a predetermined direction, a plurality of flight feathers attached to the pantograph mechanism, connection members configured to connect flight feathers adjacent to each other among the plurality of flight feathers, a first rotating mechanism configured to rotate the pantograph mechanism around one axis of a plane that intersects the direction, and a second rotating mechanism configured to rotate the pantograph mechanism around another axis of the plane. Each of the plurality of flight feathers is configured so that an angle formed by adjacent flight feathers connected via the connection members increases as the pantograph mechanism extends.