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    VERTICAL TAKEOFF AND LANDING AERIAL VEHICLE
    21.
    发明申请
    VERTICAL TAKEOFF AND LANDING AERIAL VEHICLE 审中-公开
    垂直起落车和空降车

    公开(公告)号：WO2003004353A2

    公开(公告)日：2003-01-16

    申请号：PCT/US2002/021604

    申请日：2002-07-08

    Applicant: THE CHARLES STARK DRAPER LABORATORY, INC.

    Inventor： PLUMP, John, M. ,  GUPTA, Neil, R.

    IPC: B64C

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

    Abstract: An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.

    Abstract translation: 一种包括具有纵向轴线的环形机身的航空器以及沿着纵向轴线在机身的前缘和后缘之间延伸的管道，同轴地安装在机身的管道内的第一和第二反向旋转的变桨距转子组件 机身，以及至少一个固定在环形机身上的鸭翼，其前缘位于机身的导管之外并且在机身的前缘的轴向前方，其中，所述鸭翼的至少一部分包括控制表面 具有可变的迎角。 本发明提供一种能够垂直起飞并垂直着陆的飞行器，在固定的空间点上长时间悬停，并在密闭区域内操作。 飞行器还具有在悬停和高速前进飞行之间转换的能力。

    AERIAL TRANSPORT METHOD AND APPARATUS
    22.
    发明申请
    AERIAL TRANSPORT METHOD AND APPARATUS 审中-公开
    航空运输方式和装置

    公开(公告)号：WO0068077B1

    公开(公告)日：2001-01-25

    申请号：PCT/US0007237

    申请日：2000-03-16

    Applicant: AEROVIRONMENT INC

    Inventor： MACCREADY PAUL B JR

    IPC: B64C29/02 ,  B64C39/02 ,  B64D1/08 ,  B64D1/22 ,  B64D9/00

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64D1/08 ,  B64D1/22

    Abstract: Apparatus for transporting a load (24) between source and destination locations, comprising an aircraft having a body (11), power plant (12) carried by the body (11) to drive the aircraft both generally vertically and also generally horizontally, the aircraft also having a wing structure (14-15) that has a leading edge remaining presented in the direction of flight; and load pick-up, carry and set-down means (22) connected to the aircraft to elevate the load (24) from the source location, transport the elevated and air-borne load (24) generally horizontally, and set the load (24) down at the destination location, the body (11) and power plant (12) configured for vertical flight mode to elevate and set down the load (24), and for generally horizontal flight mode to transport the elevated load (24) generally horizontally below the level of the aircraft body (11).

    Abstract translation: 用于在源和目的地之间运输负载（24）的设备，包括具有主体（11）的飞行器，由主体（11）承载的发电厂（12），以大致垂直地并且大致水平地驱动飞机 还具有翼片结构（14-15），其具有沿飞行方向保持的前缘; 以及连接到飞行器的负载拾取，携带和设置装置（22）以从源位置提升负载（24），大体水平地输送高空和空载负载（24），并设定负载（ 24）在目的地位置，主体（11）和配置用于垂直飞行模式的发电厂（12）升高和降低负载（24），并且为了大体上水平飞行模式通常运送升高的负载（24） 水平地低于飞机主体（11）的水平面。

    STOL/VTOL FREE WING AIRCRAFT WITH ARTICULATED TAIL BOOM
    23.
    发明申请
    STOL/VTOL FREE WING AIRCRAFT WITH ARTICULATED TAIL BOOM 审中-公开
    STOL /垂直起落架飞机，带有结尾的尾巴

    公开(公告)号：WO1994016942A1

    公开(公告)日：1994-08-04

    申请号：PCT/US1994000590

    申请日：1994-01-21

    Applicant: FREEWING AIRCRAFT CORPORATION

    Inventor： FREEWING AIRCRAFT CORPORATION ,  RUTAN, Elbert, L. ,  SCHMITTLE, Hugh, J.

    IPC: B64C03/38

    CPC classification number: B64C29/02 ,  B64C3/385 ,  B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/187 ,  B64D2201/00 ,  Y10S446/901

    Abstract: A VTOL/STOL free wing aircraft (100) includes a free wing (110) having wings on opposite sides of a fuselage (102) connected to one another respectively adjacent fixed wing inboard or center root sections (117) fixedly attached to the fuselage (102) for free rotation about a spanwise axis (112). Horizontal and vertical tail surfaces (138, 140) are located at the rear end of a boom assembly (120) rotatably connected to the fuselage (102). A gearing (150) or screw rod (160) arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage (102) in relation to the tail boom assembly (120) to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight.

    Abstract translation: VTOL / STOL自由翼飞机（100）包括在机身（102）的相对侧上具有翅片的自由翼（110），它们分别相互连接，分别邻接固定在机身上的固定翼或固定地连接到机身的中心根部（117） 102），用于绕翼展轴线（112）自由旋转。 水平和垂直尾部表面（138,140）位于可旋转地连接到机身（102）的悬臂组件（120）的后端。 由飞行员或遥控操作员控制的传动装置（150）或螺杆（160）布置选择地相对于尾臂组件（120）相对地枢转机身（102），以使得机身能够呈现倾斜或起起落架构 以启用VTOL / STOL航班。

    VTOL-PLANE, AIRCRAFT DRIVE, TYPE OF FLIGHT AND LANDING AREA
    24.
    发明申请
    VTOL-PLANE, AIRCRAFT DRIVE, TYPE OF FLIGHT AND LANDING AREA 审中-公开
    垂直启动和着陆航空器，发动机，类型和着陆

    公开(公告)号：WO1994011246A2

    公开(公告)日：1994-05-26

    申请号：PCT/DE1993001060

    申请日：1993-11-08

    Applicant: HÄRTEL, Martin

    IPC: B64C29/02

    CPC classification number: B64C29/02 ,  B64C17/02 ,  B64C29/0025 ,  B64C29/0091 ,  B64D27/24 ,  B64F1/16 ,  Y02T50/62

    Abstract: Depending on the embodiment, this aircraft is steered by varying the orientation of at least one propeller and/or by pilot (80) body control. It starts with a vertical fuselage (1), goes into an approximately horizontal position as the speed increases and lands again with a vertical fuselage. New motors (3) reduce swaying caused by contra-rotating propellers (2) and ensure a power-neutral counter-rotation. New high energy batteries (6) make electric drives lighter, which in turn allow an intermittent switching on/off and a simultaneous strong/weak propulsion of the same propeller by two motors having a different power. The aircraft may be parked with the lower part of the fuselage inside a hole (91) of a landing area (9), so that it does not tip over. A catching device (93) makes a precise landing more easy.

    A VERTICAL TAKE OFF AND LANDING FLYING MACHINE
    25.
    发明申请
    A VERTICAL TAKE OFF AND LANDING FLYING MACHINE 审中-公开

    公开(公告)号：WO2019145694A1

    公开(公告)日：2019-08-01

    申请号：PCT/GB2019/050162

    申请日：2019-01-22

    Applicant: VB HI-TECH VENTURES LIMITED

    Inventor： BADALASSI, Vittorio

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

    CPC classification number: B64C39/026 ,  B64C11/001 ,  B64C27/20 ,  B64C29/02

    Abstract: The disclosure relates to a vertical take-off and landing, VTOL, flying machine. The machine includes a ducted fan having an intake side and an outlet side, at least two co-axial rotors configured to contra-rotate about a fan axis X when driven in rotation; a primary drive source arranged substantially co-axially with the ducted fan and to the outlet side of the ducted fan; and first and second thrust air ducts configured to split thrust from the ducted fan into a pair of thrust streams and to guide the two respective thrust streams to opposite respective sides of the primary drive source, the ducts being rotatable to direct motion of the machine. A number of configurations of secondary drive sources and alternative thrust sources are provided for improved safety.

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    26.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
    垂直起落架和飞机

    公开(公告)号：WO2017052396A1

    公开(公告)日：2017-03-30

    申请号：PCT/PL2016/000107

    申请日：2016-09-21

    Applicant: MARGAŃSKI, Edward ,  IZDEBSKI, Andrzej

    Inventor： MARGAŃSKI, Edward

    IPC: B64C29/02 ,  B64C39/02 ,  B64C39/12

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

    Abstract: The object of the invention is a vertical take-off and landing aircraft in the manned or unmanned version powered by one or more electric motors which rotate two contra-rotating, fixed-pitch or variable-pitch propellers located at the front. To control the aircraft during vertical and horizontal flights auxiliary horizontal and vertical control and trim surfaces (5) and (7), located in the slipstream of contra-rotating propellers (1) in front of the aircraft's centre of gravity are used, whereas the control and trim surfaces (5) and (7) are suspended in relation to the aircraft on axles (6) and (8) that are located in front of the centre of aerodynamic forces created by them, owing to which the aerodynamic surfaces place themselves in the direction of the flowing control air of the aircraft, while the lift force created by them depends directly on the moments exerted on their axes of rotation (6) and (8), created with the use of linear or angular magneto-dynamic hoists (10) or with the aerodynamic method through auxiliary control tabs (12) installed on the control and trim surfaces (5) and (7).

    Abstract translation: 本发明的目的是一种垂直起飞和着陆飞机，它是由一个或多个电机驱动的载人或无人驾驶飞行器，它们旋转位于前部的两个反向旋转，固定桨距或可变桨距螺旋桨。 为了在垂直和水平航行期间控制飞机，使用位于飞机重心前面的反转螺旋桨（1）的滑流中的辅助水平和垂直控制和装饰表面（5）和（7），而 控制和装饰表面（5）和（7）相对于位于由它们产生的空气动力中心前面的轴（6）和（8）上的飞机悬挂，由此空气动力学表面放置 在飞行器的流动控制空气的方向上，由它们产生的提升力直接取决于施加在其旋转轴线（6）和（8）上的力矩，其使用线性或角度磁动力提升机 （10）或通过安装在控制和装饰表面（5）和（7）上的辅助控制翼片（12）的空气动力学方法。

    DELTA FUSELAGE FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT
    27.
    发明申请
    DELTA FUSELAGE FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT 审中-公开
    用于垂直起落架（VTOL）飞机的DELTA FUSELAGE

    公开(公告)号：WO2016109003A3

    公开(公告)日：2016-09-09

    申请号：PCT/US2015056002

    申请日：2015-10-16

    Applicant: SIKORSKY AIRCRAFT CORP

    Inventor： ALBER MARK R ,  GAYAGOY CHARLES

    IPC: B64C29/00

    CPC classification number: B64C29/02 ,  B64C1/0009 ,  B64C7/02 ,  B64C23/069 ,  Y02T50/12

    Abstract: A vertical take-off and landing (VTOL) aircraft is provided. The aircraft includes a wing, nacelles supportively disposed at opposite ends of the wing, proprotors respectively attached to each of the nacelles with each of the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and a delta-wing shaped fuselage disposed along the wing between the nacelles.

    Abstract translation: 提供垂直起飞和着陆（VTOL）飞机。 该飞机包括机翼，支撑地设置在机翼的相对端处的机舱，分别附接到每个机舱的推进器，其中每个推进器可旋转以产生垂直飞行中的升力并且在水平飞行中产生推力，并且设置三角翼形机身 沿着机舱之间的机翼。

    DELTA FUSELAGE FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT
    29.
    发明申请
    DELTA FUSELAGE FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT 审中-公开
    DELTA FUSELAGE垂直起飞和着陆（垂直起降）飞机

    公开(公告)号：WO2016109003A2

    公开(公告)日：2016-07-07

    申请号：PCT/US2015/056002

    申请日：2015-10-16

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： ALBER, Mark R. ,  GAYAGOY, Charles

    IPC: B64C27/52

    CPC classification number: B64C29/02 ,  B64C1/0009 ,  B64C7/02 ,  B64C23/069 ,  Y02T50/12

    Abstract: A vertical take-off and landing (VTOL) aircraft is provided. The aircraft includes a wing, nacelles supportively disposed at opposite ends of the wing, proprotors respectively attached to each of the nacelles with each of the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and a delta-wing shaped fuselage disposed along the wing between the nacelles.

    Abstract translation: 提供垂直起降（VTOL）飞机。 该飞机包括机翼，支撑地设置在机翼相对两端的机舱，分别连接到每个机舱的转速传感器，每个转速传感器可旋转以产生竖直飞行中的升力和水平飞行中的推力，并且设置三角翼形状的机身 沿着发动机舱之间的机翼。

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