公开(公告)号：WO2019091549A1

公开(公告)日：2019-05-16

申请号：PCT/EP2017/078489

申请日：2017-11-07

Applicant: SCHIERLE, Diego

Inventor： SCHIERLE, Diego

IPC: B64C3/56 ,  B64C27/30 ,  B64C29/00

CPC classification number: B64C27/30 ,  B64C3/56 ,  B64C29/0016

Abstract: Um ein Luftfahrzeug (100) zu schaffen, welches einerseits ein einfaches Starten und Landen auf beengtem Raum und andererseits eine hohe Reichweite sowie eine hohe Reisegeschwindigkeit ermöglicht, wird vorgeschlagen, dass das Luftfahrzeug Folgendes umfasst: Einen Rumpf (102), welcher eine Kabine (104) zur Beförderung wenigstens einer Person aufweist, wenigstens ein erstes mit dem Rumpf verbundenes Tragflügelpaar (110), wobei das erste Tragflügelpaar zwei Tragflügel (114) umfasst, welche an dem Rumpf festgelegt sind und auf einander gegenüberliegenden Seiten von dem Rumpf weg ragen, wobei jeder Tragflügel des ersten Tragflügelpaars einen relativ zum Rumpf feststehenden Tragflügelteil (116) und einen an dem jeweiligen feststehenden Tragflügelteil angeordneten, zwischen einer eingeklappten Stellung und einer ausgeklappten Stellung klappbaren Tragflügelteil (118) aufweist, ein zweites Tragflügelpaar (112), welches zwei Tragflügel (120) umfasst, die an dem Rumpf festgelegt sind und auf einander gegenüberliegenden Seiten von dem Rumpf weg ragen, wobei die beiden Tragflügel des zweiten Tragflügelpaars oberhalb der beiden Tragflügel des ersten Tragflügelpaars angeordnet sind und jeweils einen relativ zum Rumpf feststehenden Tragflügelteil (122) und einen an dem jeweiligen feststehenden Tragflügelteil angeordneten, zwischen einer eingeklappten Stellung und einer ausgeklappten Stellung klappbaren Tragflügelteil (124) aufweisen.

公开(公告)号：WO2013126117A1

公开(公告)日：2013-08-29

申请号：PCT/US2012/067783

申请日：2012-12-04

Applicant: AURORA FLIGHT SCIENCES CORPORATION

Inventor： PARKS, Robert

IPC: G05D1/10 ,  B64C29/00

CPC classification number: B64C29/0016 ,  B64C11/30 ,  B64C29/0025 ,  B64C29/0083 ,  B64C29/0091 ,  B64D27/24 ,  G05D1/102

Abstract: A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans (102c) arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans (102c) may be kept at full throttle, a second group of lift fans (102c) may be throttled to balance thrust and/or weight, and a third group of lift fans (102c) may be shut off.

Abstract translation: 一种能够在VTOL飞机过渡期间提高效率的系统和方法。 一种垂直起降飞机能够操作多个升降风扇（102c），其布置成可分开控制的组，其中，垂直起降飞机最初具有垂直飞行但转换到水平飞行。 可以将第一组提升风扇（102c）保持在全速节气门，第二组提升风扇（102c）可以被节流以平衡推力和/或重量，并且可以关闭第三组提升风扇（102c） 。

公开(公告)号：WO2006093641A2

公开(公告)日：2006-09-08

申请号：PCT/US2006/004478

申请日：2006-02-09

Applicant: HONEYWELL INTERNATIONAL INC. ,  GOOSSEN, Emray, R.

Inventor： GOOSSEN, Emray, R.

IPC: B64C39/02 ,  B64C27/20 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components (203), engine (10), and avionics/payload pods (300, 302) are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan (201 ), stator (102), and control vane design. Assembly connections between ducted fans (203) and electronic modules are also identical. An engine (10) or APU drives the dual ducted fans (203) through a splined shaft (601) to a differential (600) or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator (102) hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms (603) on each of the splined shafts (601) between the differential (600) and ducted fans (203). In the electric motor case relative speed is through electronic speed control. The fans (201 ) are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract translation: 其中管道部件（203），发动机（10）和航空电子设备/有效载荷舱（300,302）能够被快速拆卸以适合于共同的背包装系统的双管道风扇装置。 风扇（201），定子（102）和控制叶片设计中的每个风管都是相同的。 管道风扇（203）和电子模块之间的组装连接也是相同的。 发动机（10）或APU通过花键轴（601）驱动双管道风扇（203）至差速器（600）或通过电动机。 能量通过安装在定子（102）轮毂上的单个齿轮传递到涵道风扇。 通过位于差速器（600）和管道式风扇（203）之间的每个花键轴（601）上的单独的摩擦或发电机负载控制制动机构（603）来控制单个管道式风扇的相对速度。 在电动机的情况下，相对速度是通过电子调速。 风扇（201）反转以实现扭矩平衡。 对于有效载荷的变化，电子模块位置对于纵向重心是垂直可变的。

公开(公告)号：WO2019150128A1

公开(公告)日：2019-08-08

申请号：PCT/GB2019/050282

申请日：2019-02-01

Applicant: MOHSENI, Seyed Mohammad ,  SAMAD AEROSPACE LIMITED

Inventor： MOHSENI, Seyed Mohammad

IPC: B64C29/00 ,  B64C39/10

CPC classification number: B64C29/0008 ,  B64C29/0016 ,  B64C29/0025 ,  B64C29/0033 ,  B64C39/10

Abstract: A VTOL aircraft is having four electric fans (3a, 3b, 4a, 4b) distributed around the centre of gravity of the aircraft. Of the four electric fans, two (3a, 3b) are set into openings through the body (1)and two (4a, 4b) are rotatable about an axis to provide either horizontal thrust or vertical thrust. Optionally a multi-mode hybrid turbine engine (5) may be provided at the rear of the aircraft.

公开(公告)号：WO2018191083A1

公开(公告)日：2018-10-18

申请号：PCT/US2018/026128

申请日：2018-04-04

Applicant: SWIFT ENGINEERING, INC.

Inventor： MOLDOVAN, Matthew

IPC: B64C11/48

CPC classification number: B64C11/48 ,  B64C29/0016 ,  B64C29/02 ,  B64C31/024 ,  B64D27/24 ,  F05D2220/328

Abstract: A propulsion system for an aircraft may include two coaxial propellers to operate in two different flight conditions. Each propeller may be attached to a driveshaft via corresponding one-way devices that allow each propeller to be driven in one direction but spin freely in the other direction. A reversible motor may selectively rotate the driveshaft in one direction to cause one propeller to operate while the other spins freely. For example, one propeller may be operated for one flight condition (such as vertical lift) and the other propeller may be operated for another flight condition (such as horizontal flight). Another propulsion system may include a propeller, a one-way bearing, a motor, and a generator. The one-way bearing may allow the motor to drive the propeller in one direction and to spin freely in the other direction to drive the generator with incoming airflow during a gliding phase of flight.

公开(公告)号：WO2017173159A1

公开(公告)日：2017-10-05

申请号：PCT/US2017/025165

申请日：2017-03-30

Applicant: RUSSELL, David, Wayne

Inventor： RUSSELL, David, Wayne

IPC: G01S5/00 ,  G05D1/00 ,  B64C13/50 ,  G05D1/10 ,  G06G7/76

CPC classification number: B64C39/02 ,  B60F5/02 ,  B64C29/0016 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/187 ,  B64C2201/208 ,  G05D1/00 ,  G05D1/0022 ,  G05D1/0061 ,  G05D1/10 ,  G05D1/101 ,  G05D1/102 ,  G08G5/0013 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025

Abstract: Unmanned Aerial Vehicles also known as UAVs or Drones, either autonomous or remotely piloted, are classified as drones by the US Federal Aviation Administration (FAA) as weighing under 212 pounds. The system described herein details Autonomous Flight Vehicles (AFV) which weigh over 212 pounds but less than 1,320 pounds which may require either a new classification or a classification such as Sport Light Aircraft, but without the requirement of a pilot due to the safe autonomous flight system such as the Safe Temporal Vector Integration Engine or STeVIE. Safe Autonomous Light Aircraft (SALA) are useful as drone carriers, large scale air package or cargo transport, and even human transport depending on the total lift capability of the platform.

Abstract translation: 美国联邦航空管理局（FAA）将无人机（也称为无人机或无人驾驶飞机）称为无人机或遥控飞机，其重量不超过212磅。 本文描述的系统详细描述重量超过212磅但少于1,320磅的自主飞行器（AFV），其可能需要新的分类或分类，例如运动轻型飞机，但由于安全自主飞行而不需要飞行员 系统，如安全时间矢量集成引擎或STeVIE。 安全自主轻型飞机（SALA）可用作无人机载体，大型空中包裹或货物运输，甚至是人力运输，具体取决于平台的总提升能力。

公开(公告)号：WO2016201362A3

公开(公告)日：2017-01-19

申请号：PCT/US2016037074

申请日：2016-06-10

Applicant: SUNLIGHT PHOTONICS INC

Inventor： FROLOV SERGEY V ,  MOUSSOURIS JOHN PETER ,  CYRUS MICHAEL

IPC: B64C37/02 ,  G05D1/10 ,  G08G5/00

CPC classification number: 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 ,  Y02T50/145

Abstract: 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.

Abstract translation: 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：WO2017004777A1

公开(公告)日：2017-01-12

申请号：PCT/CN2015/083393

申请日：2015-07-06

Applicant: SZ DJI TECHNOLOGY CO., LTD.

Inventor： ZHENG, Dayang ,  WANG, Lei ,  WANG, Wentao ,  ZHAN, Juncheng ,  XU, Bogao

IPC: H01M8/04

CPC classification number: H01M8/0656 ,  B64C29/0016 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  H01M8/04156 ,  H01M8/04201 ,  H01M8/04208 ,  H01M8/04216 ,  H01M8/04753 ,  H01M8/04761 ,  H01M8/04776 ,  H01M8/0662 ,  H01M2250/20 ,  H01M2250/402 ,  Y02B90/12 ,  Y02T90/32

Abstract: Systems, methods and devices are provided herein for removing a byproduct of a fuel cell from a vehicle. The vehicle comprises a fuel cell (530) and a venting system (560). The fuel cell (530) is in communication with a fuel storage container (510). The fuel is configured to generate electricity and a byproduct, by reacting a first fuel from the fuel storage container (510) with a second fuel through an electrochemical reaction. The venting system (560) is configured to expose the byproduct to forced convection.

Abstract translation: 本文提供了用于从车辆去除燃料电池的副产物的系统，方法和装置。 车辆包括燃料电池（530）和排气系统（560）。 燃料电池（530）与燃料储存容器（510）连通。 燃料被配置成通过电化学反应使来自燃料存储容器（510）的第一燃料与第二燃料反应而产生电和副产物。 排气系统（560）构造成将副产品暴露于强制对流。

公开(公告)号：WO99035035A1

公开(公告)日：1999-07-15

申请号：PCT/US1999/000228

申请日：1999-01-07

IPC: B64C29/00 ,  B64C39/06 ,  B64C27/00 ,  B64C39/00

CPC classification number: B64C29/0016 ,  B64C39/064

Abstract: Vertical lift in an aircraft (1) is produced by driving a column of air downwardly, through an annular thrust-flow channel (10) which is formed in the body (fuselage (2)) of the aircraft (1). The aircraft (1) also has an aerodynamic shape which is capable of developing lift responsive to forward flight. The annular thrust-flow channel (10) is provided with a flow control mechanism (80) which is capable of directing the developed air flow in varying orientations between a substantially vertical (axial) orientation for developing stationary, vertical lift (i.e., hovering) and a vectored (angled) orientation for developing a vertical component (63) for producing lift and a horizontal component (62) for producing forward (or rearward) flight, or flight to either side.

Abstract translation: 通过在飞机（1）的主体（机身（2））中形成的环形推流通道（10）向下驱动一列空气来生产飞机（1）中的垂直升降机。 飞机（1）还具有能够响应于向前飞行而发展升力的空气动力学形状。 环形推力流动通道（10）设置有流量控制机构（80），该流量控制机构能够在大致垂直（轴向）取向之间以不同的方向引导展开的气流，用于展开静止的垂直升降（即悬停） 以及用于产生用于产生升降机的垂直部件（63）和用于产生向前（或向后）飞行或向任一侧飞行的水平部件（62）的向量（成角度）取向。

公开(公告)号：WO2019110830A1

公开(公告)日：2019-06-13

申请号：PCT/EP2018/084051

申请日：2018-12-07

Applicant: ZIPAIR ,  CHARRON, Chrystelle

Inventor： CHARRON, Chrystelle ,  ZAPATA, Frankie

IPC: B64C15/00 ,  B64C27/20 ,  B64C29/00 ,  B64C39/02

CPC classification number: B64C39/026 ,  B64C15/00 ,  B64C27/20 ,  B64C29/0016

Abstract: A propulsion device, including a platform configured to support a passenger thereon; a thrust engine coupled to the platform, wherein the thrust engine is configured to provide a thrust output substantially along a first axis; a deflector assembly positioned proximate the thrust output, wherein the deflector assembly includes two deflecting guides to divert the thrust output into at least two thrust vectors angled with respect to the first axis; an actuator coupled to each deflecting guide to controllably adjust a position of the deflecting guides with respect to the thrust engine; and a controller in communication with the actuator, wherein the controller is configured to operate the actuator in response to one or more signals from at least one of the passenger and a sensor coupled to the platform.