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：US09950810B2

公开(公告)日：2018-04-24

申请号：US15080586

申请日：2016-03-25

申请人： The Boeing Company

发明人： Adam Marshall Thoreen ,  Joshua Jay Baer ,  Joseph Adam Sikora ,  Matthew August Lassen ,  Michael Edwin Foster ,  Timothy Patrick Gallagher, Jr.

IPC分类号： B64C3/38 ,  B64D45/00 ,  B64C3/56 ,  B64C13/04 ,  B64C23/06 ,  B64C9/00

CPC分类号： B64D45/0005 ,  B64C3/38 ,  B64C3/56 ,  B64C9/00 ,  B64C13/04 ,  B64C23/065 ,  B64C23/072 ,  B64C2009/005 ,  B64D45/00 ,  Y02T50/14 ,  Y02T50/145 ,  Y02T50/164

摘要： A method and apparatus for a wingtip control system. The wingtip control system comprises a switch system for a flight deck of an aircraft and a controller. The switch system is configured to be placed into an armed state and generate an armed signal. The controller is in communication with the switch system. The controller is configured to receive the armed signal from the switch system, visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft, and generate a movement command to move the wingtip.

公开(公告)号：US20180105256A1

公开(公告)日：2018-04-19

申请号：US15842413

申请日：2017-12-14

申请人： The Boeing Company

发明人： Mark Steven Good ,  Jonathan J. Paul

IPC分类号： B64C3/56 ,  B64C9/24 ,  B64C9/00

CPC分类号： B64C3/56 ,  B64C9/24 ,  B64C2009/005 ,  Y02T50/14

摘要： Example apparatus and methods are disclosed herein for moving control surfaces on an aircraft wing to control airloads during a wing tip folding operation (from a folded position to an extended position or from an extended position to a folded position). An example method includes determining a position of a control surface on a wing of an aircraft. In the example method, the wing has a fixed wing portion and a wing tip moveably coupled to the fixed wing portion. The example method includes determining a change in the position of the control surface from a first position to second position for facilitating movement of the wing tip while the aircraft is not in flight. The example method also includes moving the control surface to the second position and moving the wing tip between an extended position and a folded position.

公开(公告)号：US09919796B2

公开(公告)日：2018-03-20

申请号：US14908850

申请日：2014-08-07

申请人： UNIT 1SRL

发明人： Pietro Giovenga

IPC分类号： B64C27/22 ,  B64C29/00 ,  B64C3/38 ,  B64C3/54 ,  B64D27/08 ,  B64C39/02

CPC分类号： B64C29/0033 ,  B64C3/385 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/08 ,  Y02T50/14

摘要： A convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft includes a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube, a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein, two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit, engines placed behind the cockpit close to the center of gravity, a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage, and a digital flight control system.

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：US09555681B2

公开(公告)日：2017-01-31

申请号：US14241239

申请日：2012-08-22

申请人： {hacek over (S)}tefan Klein

发明人： {hacek over (S)}tefan Klein

IPC分类号： B60F5/02 ,  B64C3/56 ,  B64C37/00 ,  B60F5/00 ,  B64C3/38 ,  B64C3/54 ,  B64C25/04 ,  B64C25/54 ,  B64C25/00

CPC分类号： B60F5/02 ,  B60F5/003 ,  B64C3/385 ,  B64C3/54 ,  B64C3/56 ,  B64C25/04 ,  B64C25/54 ,  B64C37/00 ,  B64C2025/003 ,  Y02T50/14

摘要： Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.

摘要翻译： 地面和空中混合动力运输车辆的变换方法包括以下转换和相互的步骤：倾斜补偿盖（7）。 将整个机翼（1）从围绕两个垂直轴（2）的运输车辆纵向位置扩展到飞行位置。 通过使每个机翼（1）的后部围绕水平轴线（3）倾斜，翼部（1）的后部部分从翼部（1）的顶部前部部分扩展到扩展的飞行位置。 机翼的起飞和着陆倾斜（1）以机翼的角度α= 0到40°开始。 前轮轨道（5）通过将前轮（5）轴向移动朝向机身而减小。 此外，描述了用于地面和空气的相应的混合运输车辆，其包含用于从英镑双轨或四轨车转换成用于起飞和降落在地面或水上的英制飞机的相互转换机制，反之亦然。

公开(公告)号：US20170015407A1

公开(公告)日：2017-01-19

申请号：US15212456

申请日：2016-07-18

申请人： Theodore M. Garver

发明人： Theodore M. Garver

IPC分类号： B64C23/08 ,  F03D1/06 ,  F03D7/02 ,  B64C3/50

CPC分类号： B64C23/08 ,  B64C3/50 ,  B64C23/02 ,  F03D1/0675 ,  F03D7/0232 ,  F05B2240/31 ,  Y02E10/721 ,  Y02T50/14

摘要： A fluid interface device, such as an airfoil assembly, can include a device structure and at least one movable band oriented such that the band moves in a direction of fluid flow. The at least one movable band can be supported on the device structure such that an outer surface of the movable band is exposed along the device structure and is capable of movement relative thereto such that a relative velocity can be maintained between the outer surface and the device structure. The fluid interface device can also include an edge extension disposed along the leading edge of the device structure. An airplane, a wind turbine and a method are also included.

摘要翻译： 诸如翼型组件的流体界面装置可以包括装置结构和至少一个可移动的带定向成使得带沿流体流动的方向移动。 所述至少一个可移动带可以被支撑在所述装置结构上，使得所述可移动带的外表面沿着所述装置结构暴露并且能够相对于其移动，使得可以在所述外表面和所述装置之间保持相对速度 结构体。 流体界面装置还可以包括沿着装置结构的前缘设置的边缘延伸部。 还包括飞机，风力发电机和方法。

公开(公告)号：US09541924B2

公开(公告)日：2017-01-10

申请号：US14737814

申请日：2015-06-12

申请人： SUNLIGHT PHOTONICS INC.

发明人： Sergey V. Frolov ,  John Peter Moussouris ,  Michael Cyrus

IPC分类号： G05D1/10 ,  G05D1/00 ,  G05D1/02 ,  G05D1/06 ,  B64C37/02 ,  B64C3/56 ,  G08G5/00 ,  G08G7/02 ,  B64C29/00

CPC分类号： G05D1/104 ,  B64C3/56 ,  B64C29/0016 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/143 ,  B64C2201/145 ,  B64D1/02 ,  G05D1/0022 ,  G05D1/0027 ,  G05D1/005 ,  G05D1/0212 ,  G05D1/0669 ,  G05D1/102 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0017 ,  G08G5/0021 ,  G08G5/003 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025 ,  G08G5/045 ,  G08G7/02 ,  Y02T50/14

摘要： Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

摘要翻译： 本发明的实施例提供了一种替代的分布式机载运输系统。 在一些实施例中，一种用于分布式机载运输的方法包括：向机载车辆提供机翼和机翼跨度，具有携带乘客或货物中的一个或多个的能力; 机载车辆靠近一个或多个乘客或货物并装载至少一个乘客或货物; 起飞和确定机载飞行方向; 至少定位一个具有大致相同的飞行方向的其他机载车辆; 并将至少一个其他机载车辆接入飞行形成并形成一个舰队，其中机载车辆以相同的速度和方向飞行，并且相邻的机载车辆以小于100个翼跨的距离分开。

公开(公告)号：US09481444B2

公开(公告)日：2016-11-01

申请号：US13611588

申请日：2012-09-12

申请人： Max U. Kismarton

发明人： Max U. Kismarton

IPC分类号： B64C3/26 ,  B64C3/20 ,  B64C3/18 ,  B64C3/44

CPC分类号： B64C3/26 ,  B64C3/18 ,  B64C3/20 ,  B64C2003/445 ,  Y02T50/14

摘要： An aerodynamic lift structure comprises unbalanced composite skin that couples twist and bending.

摘要翻译： 气动提升结构包括不平衡的复合皮肤，其耦合扭曲和弯曲。

公开(公告)号：US20160311522A1

公开(公告)日：2016-10-27

申请号：US15135624

申请日：2016-04-22

申请人： Lilium GmbH

发明人： Daniel Wiegand

IPC分类号： B64C9/20 ,  B64C29/00 ,  B64C9/34 ,  B64D27/26

CPC分类号： B64C1/0009 ,  B64C3/48 ,  B64C29/0025 ,  B64D27/02 ,  B64D27/12 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44

摘要： An aerofoil for an aircraft includes an engine, a first lift body, and a second lift body which is arranged behind the first lift body in the direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil.

摘要翻译： 用于飞行器的翼型机包括发动机，第一升降机体和第二提升机构，其在翼型机的流动方向上布置在第一升降机体的后面。 第二提升机构可相对于第一升降机构枢转，在两个升降机体之间，其中两个升降机体一起限定翼型在流动方向上的细长且基本上连续的横截面，以及起飞/着陆位置 第二提升机构相对于第一升降机构向下成角度以增加机翼的升程。