公开(公告)号：US09174732B2

公开(公告)日：2015-11-03

申请号：US14144146

申请日：2013-12-30

Applicant: Google Inc.

Inventor： Kenneth Jensen ,  Erik Christopher Chubb ,  Damon Vander Lind

IPC: B64C39/02 ,  F03D5/00 ,  G05D1/10

CPC classification number: B64C39/022 ,  B64C2201/021 ,  B64C2201/148 ,  F03D5/00 ,  F03D5/06 ,  F05B2240/921 ,  G05D1/0866 ,  G05D1/101 ,  Y02E10/70 ,  Y02E10/725

Abstract: A method involves operating an aerial vehicle to travel along a first closed path on a tether sphere while oriented in a crosswind-flight orientation. A tether is connected to the aerial vehicle on a first end and is connected to a ground station on a second end. Further, the tether sphere has a radius corresponding to a length of the tether. The method further involves while the aerial vehicle is in the crosswind-flight orientation, operating the aerial vehicle to travel along a second closed path on the tether sphere, such that a speed of the aerial vehicle is reduced. And the method involves after or while the speed of the aerial vehicle is reduced, transitioning the aerial vehicle from traveling along the second closed path while in the crosswind-flight orientation to a hover-flight orientation.

公开(公告)号：US20150298806A1

公开(公告)日：2015-10-22

申请号：US14485412

申请日：2014-09-12

Applicant: Google Inc.

Inventor： Damon Vander Lind ,  Thomas Van Alsenoy ,  Richard Wayne DeVaul

IPC: B64C39/02 ,  B64D3/00 ,  C07C29/141 ,  B63H9/06 ,  B64F1/36 ,  F03D9/00 ,  B64D47/00

CPC classification number: F03D9/32 ,  B63H9/0685 ,  B63H2009/0692 ,  B64C27/00 ,  B64C31/06 ,  B64C39/022 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/028 ,  B64C2201/145 ,  B64C2201/205 ,  B64C2201/206 ,  B64C2201/208 ,  B64D3/00 ,  B64D47/00 ,  B64F3/02 ,  C07C29/141 ,  F03D5/00 ,  F03D9/008 ,  F03D9/11 ,  F03D9/25 ,  F03D80/80 ,  F05B2240/917 ,  F05B2240/921 ,  H02K7/1838 ,  Y02E10/70 ,  Y02E10/725 ,  Y02E10/728

Abstract: A vehicle-based airborne wind turbine system having an aerial wing, a plurality of rotors each having a plurality of rotatable blades positioned on the aerial wing, an electrically conductive tether secured to the aerial wing and secured to a ground station positioned on a vehicle, wherein the aerial wing is adapted to receive electrical power from the vehicle that is delivered to the aerial wing through the electrically conductive tether; wherein the aerial wing is adapted to operate in a flying mode to harness wind energy to provide a first pulling force through the tether to pull the vehicle; and wherein the aerial wing is also adapted to operate in a powered flying mode wherein the rotors may be powered so that the turbine blades serve as thrust-generating propellers to provide a second pulling force through the tether to pull the vehicle

Abstract translation: 一种具有空中翼面的车载机载风力涡轮机系统，多个转子，每个转子具有位于空中飞翼上的多个可旋转叶片，固定在飞行器上并固定在位于车辆上的地面站的导电系绳， 其中所述空中翼适于从通过所述导电系绳传送到所述空中翼的车辆接收电力; 其中所述空中翼适于以飞行模式操作以利用风能以提供穿过所述系绳的第一拉力以拉动所述车辆; 并且其中所述空中翼还适于以动力飞行模式操作，其中所述转子可以被供电，使得所述涡轮机叶片用作推力产生螺旋桨以提供穿过所述系绳的第二拉力以拉动所述车辆

公开(公告)号：US09120560B1

公开(公告)日：2015-09-01

申请号：US13648706

申请日：2012-10-10

Applicant: Latitude Engineering, LLC

Inventor： Charles Justin Armer ,  Bayani R. Birkinbine ,  Thomas J. Cleary ,  Sean C. Culbertson ,  Jason M. Douglas ,  Carlos V. Murphy ,  Manu Singh

IPC: B64C27/08 ,  B64C27/26 ,  B64C29/00

CPC classification number: B64C29/0008 ,  B64C27/08 ,  B64C27/26 ,  B64C29/0016 ,  B64C29/0025 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/021 ,  B64C2201/088

Abstract: A vertical take-off and landing aircraft includes a fixed wing airframe having opposed left and right wings extending from left and right sides, respectively, of a fuselage having opposed leading and trailing extremities and an empennage located behind the trailing extremity. Four fixed, open and horizontal, vertical take-off and landing (VTOL) thrust rotors are mounted to the airframe in a quadrotor pattern for providing vertical lift to the aircraft, and a vertical, forward thrust rotor is mounted to the trailing extremity of the fuselage between the trailing extremity of the fuselage and the empennage for providing forward thrust to the aircraft. The four VTOL thrust rotors are coplanar being and operating in a common plane that is parallel relative to, and being level with, top surfaces of the left and right wings in and around a region of each of the four VTOL thrust rotors.

Abstract translation: 垂直起飞和着陆飞机包括具有相对的左翼和右翼的相对的左翼和右翼的固定翼机身，其分别具有相对的前端和后端的机身的左侧和右侧以及位于尾端后面的尾翼。 四个固定的，开放的和水平的，垂直起飞和着陆（VTOL）推力转子以四旋转模式安装在机身上，用于向飞行器提供垂直升力，并且垂直的向前的推力转子安装到 机身尾部之间的机身与向前推进飞机的尾翼之间的机身。 四个VTOL推力转子是共面的，并且在共同的平面中工作，该公共平面相对于左翼和右翼的顶表面平行并且与左翼和右翼的顶表面平行，并且在四个竖井推力转子中的每一个的区域内和周围。

公开(公告)号：US09004402B2

公开(公告)日：2015-04-14

申请号：US14034097

申请日：2013-09-23

Applicant: Aerovel Corporation

Inventor： Brian Theodore McGeer ,  Robert Joseph Heavey, III ,  Damon Lucas McMillan ,  John William Stafford

IPC: B64F1/02 ,  B64F1/04 ,  B64C39/02 ,  B64D37/00 ,  B64F5/00

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/182 ,  B64D37/00 ,  B64F5/00

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched. In one embodiment, for retrieval, the aircraft drops a tether and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured b an end effector. The tether length is adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch, the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with a simple, economical apparatus. It can be used with low risk of damage and requires moderate accuracy in manual or automatic flight control.

Abstract translation: 可以自动检索，维修和启动能够推力飞行的飞机。 在一个实施例中，为了检索，飞行器降低系绳并且以相对较低的速度将系绳拉动以与水平引导件接触。 将系绳拉过引导件，直到引导件被捕获为末端执行器。 系绳长度根据需要进行调整，飞机在导轨上摆动，悬挂在倒立的位置。 沿着导轨翻转系绳，然后将飞机带到对接车厢，飞机停在其中，以便维修。 对于发射，托架正直摆动，末端执行器从引导件释放，飞机起飞进入自由飞行。 因此，可以使用简单，经济的装置自动完成完整的地面处理循环。 它可以在低风险的情况下使用，并且在手动或自动飞行控制中要求中等精度。

公开(公告)号：US08991758B2

公开(公告)日：2015-03-31

申请号：US13892358

申请日：2013-05-13

Applicant: Winehawk Inc.

Inventor： Ernest Earon

IPC: B64C1/00 ,  B64C39/02 ,  B64D47/08

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/127 ,  B64D47/08 ,  B64D2221/00 ,  H05K1/0268 ,  H05K1/14 ,  H05K2201/047 ,  H05K2201/09027 ,  Y10T29/49622

Abstract: An unmanned aerial vehicle, comprising: a fuselage having a first side board and a second side board spaced apart and connected by at least one transverse board; the first side board, the second side board, and the at least one transverse board being printed circuit boards; at least one of the first side board, the second side board, and the at least one transverse board having formed and mounted thereon conductive traces and at least one component, respectively, for controlling and monitoring the unmanned aerial vehicle; first and second wings mounted to the fuselage; and, a tail mounted to the fuselage.

Abstract translation: 一种无人驾驶飞行器，包括：机身，其具有间隔开并通过至少一个横向板连接的第一侧板和第二侧板; 第一侧板，第二侧板和至少一个横向板是印刷电路板; 第一侧板，第二侧板和至少一个横板中的至少一个分别形成并安装有导电迹线和至少一个部件，用于控制和监视无人驾驶飞行器; 第一和第二翼安装在机身上; 和尾部安装在机身上。

公开(公告)号：US20150053819A1

公开(公告)日：2015-02-26

申请号：US13974350

申请日：2013-08-23

Applicant: Becklin Holdings, Inc.

Inventor： Dennis S. Becklin ,  Dean A. Weathers ,  Adrian P. Tayne

IPC: B64C1/26

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/201 ,  Y10T29/49815

Abstract: A system is disclosed including at least one indexing stub secured to a fuselage in the place of one or more wing stubs and including indexing members protruding from opposite sides of the fuselage. A pair of receivers are mounted to a container and define channels to receive the indexing members. The channels may include an upper flared portion and a lower straight portion. The indexing members are lowered into the channels and the flared portions guide the indexing members into the straight portions. In some embodiments, a pair of clamping members are configured to selectively lock the indexing members within the channels. The indexing members may have a cylindrical shape and may be rotatably mounted to the at least one indexing stub.

Abstract translation: 公开了一种系统，其包括至少一个固定到机身的索引短截线代替一个或多个翼桩，并且包括从机身的相对侧突出的分度构件。 一对接收器被安装到容器并且定义用于接收索引构件的通道。 通道可以包括上部扩口部分和下部直线部分。 分度构件下降到通道中，并且扩口部分引导分度构件进入直线部分。 在一些实施例中，一对夹紧构件被配置成选择性地将索引构件锁定在通道内。 分度构件可以具有圆柱形形状并且可以可旋转地安装到至少一个分度桩。

公开(公告)号：US08931739B1

公开(公告)日：2015-01-13

申请号：US12633212

申请日：2009-12-08

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C1/00 ,  B64C3/00 ,  B64C5/00

CPC classification number: B64C39/024 ,  B64C1/34 ,  B64C2201/021

Abstract: A method and apparatus for deploying an aircraft. An inflation system is activated to generate a gas. A fuselage of the aircraft is inflated with the gas. The fuselage comprises a frame for the aircraft and a number of flexible layers associated with the frame in which the number of flexible layers are configured to define a volume for at least a portion of the aircraft when the number of flexible layers are in an inflated configuration.

Abstract translation: 一种用于部署飞行器的方法和装置。 通气系统被激活以产生气体。 飞机的机身用气体充气。 机身包括用于飞机的框架和与框架相关联的多个柔性层，其中柔性层的数量被配置为在柔性层的数量处于膨胀构造中时为飞机的至少一部分限定体积 。

公开(公告)号：US20140339371A1

公开(公告)日：2014-11-20

申请号：US13852315

申请日：2013-03-28

Applicant: W. Morrison Consulting Group, Inc.

Inventor： William M. YATES ,  Robert USSERY ,  Byron YOUNG

IPC: B64D33/00

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/187 ,  B64D5/00 ,  B64D27/24

Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of unmanned aerial vehicle (UAV) packs flying independent of and in proximity to the electric aircraft.

Abstract translation: 电动飞机，包括飞行中可充电电动飞机，以及运行电动飞机的方法，包括通过使用独立于和接近电动飞机飞行的无人驾驶飞行器（UAV）组件来为飞行中的电动飞机充电的方法。

公开(公告)号：US08876039B2

公开(公告)日：2014-11-04

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：US20140319266A1

公开(公告)日：2014-10-30

申请号：US14008707

申请日：2012-03-27

Applicant: Jean-Marc Moschetta ,  Chinnapat Thipyopas

Inventor： Jean-Marc Moschetta ,  Chinnapat Thipyopas

IPC: B64C39/02 ,  B64C19/00 ,  B64C25/36

CPC classification number: B64C39/028 ,  B64C25/36 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/18 ,  B64D45/06

Abstract: A microscale radio-controlled aerial micro-drone vehicle, having a fixed wing (as opposed to a rotary wing) having a propulsion device the vehicle including wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels being located in front of the center of gravity of the micro-drone, the center of gravity of the micro-drone being located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.

Abstract translation: 具有具有推进装置的固定翼（相对于旋转翼）的微型无线电遥控的空中微型无人驾驶车辆，该车辆包括用于在地面上行驶的车轮，其附接到翼的一部分的侧端 。 车轮的旋转轴线Y1位于微型无人驾驶飞机重心的前方，微型无人机的重心位于微型无人机的空气动力学中心的前方。 车轮的旋转轴线Y1与推进装置的推力轴线对准，车轮的尺寸使其半径D / 2大于车轮的旋转轴线Y1和机翼的后缘之间的距离 。