公开(公告)号：WO1998002350A1

公开(公告)日：1998-01-22

申请号：PCT/US1997010932

申请日：1997-07-14

Applicant: McDONNELL, William, R.

IPC: B64C29/02

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/12 ,  Y02T50/82

Abstract: An aircraft (12) adapted for flight in helicopter mode with its longitudinal axis oriented generally vertically and in airplane mode with its longitudinal axis oriented generally horizontally is provided with the capability of launching and landing with the tail end (202) directed skyward. The invention also includes improvements to the controllability and efficiency of aircraft (12) in helicopter mode provided by the stabilizer wings (24, 26, 28) and relative rotation of the fuselage section (14) about the aircract's longitudinal axis. The aircraft (12) may have an elongate boom (83) for engagement with a base structure (81). The base structure (81) may be attached to a building, a trailer transporter, a ship or some other structure.

Abstract translation: 一种适于以直升机模式飞行的飞行器（12）具有其纵向轴线大致垂直定向并且在其纵向轴线大致水平地定向的飞行模式中的飞行器（12）被提供具有朝向天空的尾端（202）发射和着陆的能力。 本发明还包括对由稳定翼（24,26,28）提供的直升机模式的飞机（12）的可控性和效率的改进以及机身部分（14）绕着绕线的纵向轴线的相对旋转。 飞行器（12）可以具有用于与基部结构（81）接合的细长悬臂（83）。 基部结构（81）可以附接到建筑物，拖车运输装置，船舶或其他结构上。

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：WO2017123346A2

公开(公告)日：2017-07-20

申请号：PCT/US2016/065148

申请日：2016-12-06

Applicant: AAI CORPORATION

Inventor： WILLFORD, Neal H.

CPC classification number: B64C39/024 ,  B64C25/34 ,  B64C27/50 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64D17/80 ,  G05D1/0055 ,  G05D1/0816 ,  G05D1/0858

Abstract: A technique is directed to operating an unmanned aerial vehicle (UAV) having a fuselage defining a flight direction of the UAV and wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage. The technique involves providing, while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, thrust from propulsion units of the wing plate assemblies to fly the UAV along a vertical takeoff path. The technique further involves maneuvering, after the UAV flies along the vertical takeoff path, the UAV to align the flight direction along a horizontal flight path that is perpendicular to the vertical takeoff path. The technique further involves providing, after the UAV flies along the horizontal flight path, thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path.

Abstract translation: 一种技术涉及操作具有限定UAV的飞行方向的机身的无人驾驶飞行器（UAV）以及在由机身限定的飞行方向上推进UAV的翼板组件。 该技术涉及在由UAV的机身限定的飞行方向垂直指向地面上的起飞位置的同时提供来自翼板组件的推进单元的推力以沿着垂直起飞路径飞行UAV。 该技术还涉及操纵，在UAV沿着垂直起飞路径飞行后，UAV沿着垂直于垂直起飞路径的水平飞行路径对准飞行方向。 该技术还涉及在UAV沿着水平飞行路径飞行之后提供来自翼板组件的推进单元的推力以沿着垂直着陆路径降落UAV。

公开(公告)号：WO2017035503A1

公开(公告)日：2017-03-02

申请号：PCT/US2016/049086

申请日：2016-08-26

Applicant: MARTIN UAV, LLC

Inventor： MORRIS, Stephen

IPC: B64C29/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/141 ,  B64C2201/162

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract translation: 飞机包括机身，机翼，风扇和控制器。 机翼和管道风扇耦合到机身。 控制器可操作以以垂直飞行模式，水平飞行更多地控制飞行器，并且将飞行器从垂直飞行模式转换到水平飞行模式。

公开(公告)号：WO2016184358A1

公开(公告)日：2016-11-24

申请号：PCT/CN2016/081978

申请日：2016-05-13

Applicant: 江苏数字鹰科技发展有限公司

Inventor： 陈乐春

IPC: B64C27/22 ,  B64C1/00

CPC classification number: B64C29/02 ,  B64C1/00 ,  B64C5/02 ,  B64C9/00 ,  B64C27/22 ,  B64C2009/005 ,  G05D1/0858

Abstract: 一种基于双飞控系统的固定结构式垂直起降飞机，包括飞机结构和飞控系统。飞机结构包括机身（1-1，2-1）、固定翼、舵机系统（4）以及安装在机身（1-1，2-1）周侧或固定翼端部的多台发动机（1-9，2-6）；飞控系统包括多旋翼飞控系统（1）和固定翼飞控系统（2），多旋翼飞控系统（1）和固定翼飞控系统（2）相对独立或整合在同一个飞控系统内。通过计算机控制多旋翼飞控系统（1）和固定翼飞控系统（2）对舵机系统（4）、发动机（1-9，2-6）的输出通道的开启和关断实现在两种飞行模式之间自由切换，既能够以多旋翼方式垂直起降，又能够以固定翼方式高速巡航。该飞机结构简单、可靠性强，操控灵活，成本低廉，不仅适用于无人机，而且适用于载人机，并可广泛应用于民航和军事等领域。

公开(公告)号：WO2016003530A3

公开(公告)日：2016-03-10

申请号：PCT/US2015027565

申请日：2015-04-24

Applicant: NORTHROP GRUMMAN SYSTEMS CORP

Inventor： CREASMAN SON F

IPC: B64C3/56 ,  B64C3/54 ,  B64C25/04 ,  B64C29/00 ,  B64C29/02

CPC classification number: G05D1/102 ,  B64C3/546 ,  B64C3/56 ,  B64C9/00 ,  B64C11/48 ,  B64C25/04 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/102 ,  B64C2201/108 ,  B64F1/007 ,  G05D1/0011

Abstract: One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV)(12). The VTOL UAV (12) includes a flight control system configured to provide avionic control of the VTOL UAV (12) in a hover mode and in a level-flight mode. The VTOL UAV (12) also includes a body (18) encapsulating an engine and the flight control system. The VTOL UAV (12) further includes a propeller disk (14) coupled to the engine and configured to provide vertical thrust in the hover mode and to provide horizontal thrust for flight during the level-flight mode.

Abstract translation: 一个示例性实施例包括垂直起飞和着陆（VTOL）无人机（UAV）（12）。 VTOL UAV（12）包括飞行控制系统，其配置为以悬停模式和级别飞行模式提供垂直起降无人机（12）的航空电子控制。 VTOL UAV（12）还包括封装发动机和飞行控制系统的主体（18）。 VTOL UAV（12）还包括联接到发动机的螺旋桨盘（14），并配置成在悬停模式下提供垂直推力并在水平飞行模式期间提供用于飞行的水平推力。

公开(公告)号：WO2016013933A1

公开(公告)日：2016-01-28

申请号：PCT/NL2015/050531

申请日：2015-07-21

Applicant: ATMOS UAV B.V.

Inventor： HULSMAN, Sander ,  DE GROOT, Jurjen ,  MILIS, Maarten ,  DOKTER, Dirk Lucas Eduard ,  BOUMAN, Joost Leon ,  KNOOPS, Ruud

IPC: B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,1 2) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof.

Abstract translation: 一种飞机，特别是具有机翼飞行模式和悬停飞行模式的无人机，包括具有左（6），中（7）和右翼部分（8）的机翼结构（4）。 支撑结构从机翼结构（4）延伸，并且具有上部和下部支撑部分。 左右翼部（6,8）和上下支撑部（18,20）中的每一个具有推力单元（10,12,22,24）。 左翼翼部分和右翼尖部分分别围绕基本上在机翼结构的长度方向延伸的轴线相对于左翼翼基部和右翼基部旋转。 左翼翼部分（6）和右翼部分（6）的推力单元（10,1 2）设置在相应的翼尖部分，特别是在其四肢处。

公开(公告)号：WO2015099603A1

公开(公告)日：2015-07-02

申请号：PCT/SG2013/000548

申请日：2013-12-24

Applicant: SINGAPORE TECHNOLOGIES AEROSPACE LTD

Inventor： CHAN, Keen Ian

IPC: B64C27/08 ,  B64C27/10 ,  B64C29/02 ,  B64C25/32 ,  B64C39/10 ,  B64C11/46 ,  B64C39/02 ,  A63H27/127 ,  A63H27/133 ,  A63H27/18

CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C11/48 ,  B64C27/08 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/141

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

Abstract translation: 能够进行垂直和水平飞行模式的无人驾驶飞行器（UAV），组装无人机的方法以及组装无人机的零件套件。 无人机包括细长的机翼结构，其具有沿着细长机翼结构的最长尺寸的细长轴线，细长机翼结构在大致中途点处具有中间位置; 连接结构从细长机翼结构基本上垂直延伸，连接结构在细长轴的第一位置处从细长机翼结构的中间位置偏移; 和至少三组螺旋桨，其中至少两组螺旋桨安装在连接结构上，并且其中至少一组螺旋桨安装在远离连接结构的相反方向偏离中间位置的第二位置 。

公开(公告)号：WO2014025444A2

公开(公告)日：2014-02-13

申请号：PCT/US2013/042026

申请日：2013-05-21

Applicant: ARLTON, Paul E. ,  ARLTON, David J.

Inventor： ARLTON, Paul E. ,  ARLTON, David J.

IPC: B64C27/10

CPC classification number: B64C27/10 ,  B64C27/24 ,  B64C27/26 ,  B64C27/605 ,  B64C29/02 ,  B64C39/024 ,  B64C2027/8236 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/205 ,  B64C2201/206

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract translation: 旋转翼车辆包括具有细长管状骨架或芯体的主体结构，以及具有转子的反向旋转同轴转子系统，每个转子具有单独的电动机，以围绕公共转子旋转轴线驱动转子。 转子系统用于在定向飞行中移动旋翼机。

公开(公告)号：WO2013012456A2

公开(公告)日：2013-01-24

申请号：PCT/US2012/030459

申请日：2012-03-23

Applicant: PAGE, Mark, Allan ,  MCCUE, Matthew, Robert ,  GODLASKY, Robert, Anthony

Inventor： PAGE, Mark, Allan ,  MCCUE, Matthew, Robert ,  GODLASKY, Robert, Anthony

IPC: B64C27/24

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。