公开(公告)号：WO2010050839A1

公开(公告)日：2010-05-06

申请号：PCT/RU2008/000677

申请日：2008-10-31

Applicant: ПАВЛИКОВ, Вячеслав Анатольевич ,  ПОЛИН, Александр Николаевич

Inventor： ПАВЛИКОВ, Вячеслав Анатольевич ,  ПОЛИН, Александр Николаевич

IPC: B64C29/02 ,  B64C39/06

CPC classification number: B64C39/064

Abstract: Изобретение относится к области авиации, а именно, к летательным аппаратам, и предназначено для перевозки грузов и пассажиров, для опыления садов и полей, для охраны лесов и заповедников, как скорая помощь в труднодоступных районах. Летательный аппарат вертикального взлета и посадки содержит корпус обтекаемой формы, по меньшей мере, одно крыло, выполненное в виде кольца, расположенное внутри и/или снаружи корпуса. Внутри корпуса расположены маховик в виде полого диска, снабженный клапанами дистанционного управления, силовая установка, состоящая, по меньшей мере, из одного двигателя и, по меньшей мере, из одного вентиляторного устройства или турбовентиляторного двигателя и эжекторного устройства. Система управления состоит из рулей управления по направлению, по вектору тягу, по крену и тангажу, выполненных в виде профилированных колец и расположенных симметрично относительно друг друга и оси корпуса. Достигается увеличение подъемной силы, повышение аэродинамического качества, безопасности полета, маневренности и снижение расхода топлива.

Abstract translation: 本发明涉及航空，特别涉及飞机，可用于运输货物和乘客，喷洒花园和田地，保护森林和自然保护区以及作为难以到达的地区的救护车。 垂直起飞和着陆飞机包括空气动力体和至少一个设置在机体内部和/或外部的环形翼。 在身体内部布置有飞轮，其具有设置有遥控阀的中空盘的形式，以及由至少一个发动机和至少一个风扇装置或涡轮风扇和喷射装置组成的动力单元。 控制系统包括方向舵，推力矢量控制和滚动和俯仰控制表面，其设计成成形环的形式，并且相对于彼此对称并且相对于主体的轴线对称设置。 本发明可以提高提升力，改善空气动力特性，飞行操作安全性和机动性，并降低燃料消耗。

公开(公告)号：WO2009135260A1

公开(公告)日：2009-11-12

申请号：PCT/AU2009/000566

申请日：2009-05-07

Applicant: ENTECHO PTY LTD ,  CHAPMAN, Greg ,  KAWKA, Jakub ,  SCHLUNKE, Christopher, Kim

Inventor： CHAPMAN, Greg ,  KAWKA, Jakub ,  SCHLUNKE, Christopher, Kim

IPC: B64C29/02 ,  B64C15/02 ,  B64C39/00 ,  B64C7/00 ,  B64C27/20 ,  B64D33/04

CPC classification number: B64C27/20 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108

Abstract: A fluid dynamic device (100) for directing fluid flow to generate thrust comprising a thrust control shroud (130) disposed about a central axis (210) of said fluid dynamic device (100) for directing a fluid flow between an upstream fluid intake region (220) and a downstream fluid exit region (222), forming a fluid exit area, of said shroud (130) to generate thrust wherein a displacement of said fluid exit region (222) of said shroud (130) with respect to said central axis (210) results in a translation of said fluid exit area (222) such that the level of shear stress induced in that part of the shroud (130) disposed laterally to the direction of translation of the shroud (130) is minimised.

Abstract translation: 用于引导流体流动以产生推力的流体动力装置（100），包括围绕所述流体动力装置（100）的中心轴线（210）设置的推力控制罩（130），用于引导流体流在上游流体进入区域 220）和形成所述护罩（130）的流体出口区域的下游流体出口区域（222）以产生推力，其中所述护罩（130）的所述流体出口区域（222）相对于所述中心轴线 （210）的平移导致所述流体出口区域（222）的平移，使得在围绕护罩（130）的平移方向侧向设置的护罩（130）的那部分中引起的剪切应力水平最小化。

公开(公告)号：WO2007129313A3

公开(公告)日：2007-11-15

申请号：PCT/IL2007/000544

申请日：2007-05-03

Applicant: URBAN AERONAUTICS LTD. ,  YOELI, Raphael

Inventor： YOELI, Raphael

IPC: B64C29/02

Abstract: A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles.

公开(公告)号：WO2006041503A3

公开(公告)日：2006-04-20

申请号：PCT/US2004/043178

申请日：2004-12-23

Applicant: BLEVIO, Henry, L.

Inventor： BLEVIO, Henry, L.

IPC: B64C29/02

Abstract: In a preferred embodiment, a vertical takeoff aircraft (100) body having an inverted hemispherical upper portion (120), a generally cylindrical lower portion (142) with a diameter of its upper end slightly greater than a diameter of its lower end but less than a diameter of the lower end of the upper portion (120), and a truncated inverted generally cone-shaped transition portion (140) joining the upper portion (120) and the lower portion (142); and a plurality of vertical columns (150) attached to the aircraft (100) body and spaced apart from the aircraft (100) body, equidistantly disposed about the aircraft (100) body. The present invention also provides novel landing gears (200) for such an aircraft (100) as well as a novel method of adjusting the pitches of rotating blade (160) thereof.

公开(公告)号：WO0234620A8

公开(公告)日：2002-09-19

申请号：PCT/SE0102235

申请日：2001-10-15

Applicant: BUELOW AB AIR TARGET SYSTEM ,  BUELOW KJELL

Inventor： BUELOW KJELL

IPC: B64C27/20 ,  B64C39/02 ,  B64C27/06 ,  B64C27/10 ,  B64C29/02

CPC classification number: A63H27/12 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: An unpiloted rotor-driven aircraft comprising a drive unit (5) having a drive motor connected via a rotor shaft (4) to a rotor member (1) for generating a substantially downwardly directed air stream, a load carrier (7) arranged below the drive unit (5) and connected thereto, and a control means (S) the angular movement of which is independent in relation to the load carrier (7) and which comprises a support member (21) provided with adjustable rudders (25) arranged to be influenced by the air stream generated by the rudder member (1) in order to control the movement of the craft, wherein the rotor shaft (4) comprises a lower rotor shaft (4a) and an upper rotor shaft (4b), which rotor shafts (4a, 4b) are articulately joined to each other by a first joint member (91) that permits limited angular movement between the lower rotor shaft (4a) and the upper rotor shaft (4b).

Abstract translation: 一种无人驾驶的转子驱动的飞行器，其包括具有经由转子轴（4）连接到转子构件（1）以用于产生基本上向下的气流的驱动马达的驱动单元（5），设置在该转子构件 驱动单元（5）并与其连接，以及控制装置（S），其角运动相对于所述负载承载件（7）是独立的并且包括设有可调节方向舵（25）的支撑构件（21） （4）包括下转子轴（4a）和上转子轴（4b），所述转子轴（4b）由所述方向舵构件（1）产生的气流影响以控​​制所述飞行器的运动，其中，所述转子轴 轴（4a，4b）通过允许在下转子轴（4a）和上转子轴（4b）之间的有限的角运动的第一接头构件（91）而彼此铰接地连接。

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：WO2022200883A1

公开(公告)日：2022-09-29

申请号：PCT/IB2022/051877

申请日：2022-03-03

Applicant: INTERACTIVE FULLY ELECTRICAL VEHICLES S.R.L.

Inventor： PERLO, Pietro ,  PENSERINI, Davide

IPC: B64C29/02 ,  B64C29/00 ,  B64C39/06 ,  B64D27/24 ,  B64D35/04 ,  B64D35/08 ,  B63H20/00

Abstract: An aircraft, in particular a personal air mobility aircraft or a drone, comprising one or more annular propellers (2), with one or more blades (3) extending radially from a rotor ring body (2A) towards the axis (4) of the rotor ring (2A), and one or more belt transmissions (5), which connect the rotor ring (2A) of each annular propeller (2) with the output shaft of a motor unit (P) including an electric motor. Various alternative techniques are provided to support the rotor ring (2A) in rotation. Various aircraft configurations are envisaged, including a vertical take-off and horizontal flight configuration. The aircraft surfaces are covered by groups of photovoltaic solar cells (PV) connected both to a main battery pack (201) for powering the electric motors (M) that drive the annular propellers, and to an auxiliary electric battery (202) for powering the on-board electrical circuit, by means of DC-DC converters (203) controlled by an electronic board (204).

公开(公告)号：WO2021242390A2

公开(公告)日：2021-12-02

申请号：PCT/US2021/024530

申请日：2021-03-26

Applicant: JUMP AERO INCORPORATED

Inventor： DIETRICH, Carl ,  LOZANO, Brian ,  MYJAK, Jeff ,  SPERRY, Jen

IPC: B64C29/02 ,  B64C27/26 ,  B64C13/50 ,  B64D45/06 ,  G05D1/08 ,  B64C25/32 ,  B64C9/00

Abstract: Disclosed embodiments include a blown flying wing tailsitter aircraft leveraging distributed electric propulsion to enable a combination of exceptional aerodynamic performance and high bandwidth control in both vertical (hovering) and horizontal flight. A pilot in one disclosed embodiment may be in the prone position during cruise and standing during vertical flight phase to enable greater aerodynamic efficiency with minimal engineering complexity and a small landing footprint. Batteries may be disposed in a high-volume wing sealed off from the piloted compartment to increase the safety of the pilot while distributing the inertial load of batteries and motors across the wingspan, thus enabling a lighter and simpler structure. Propellers may be above head- level for operational safety when the aircraft is standing on the ground.

公开(公告)号：WO2021201927A2

公开(公告)日：2021-10-07

申请号：PCT/US2020/063697

申请日：2020-12-08

Applicant: KYMATICS, LLC

Inventor： ANDREWS, Joseph, John

IPC: B64C27/22 ,  B64C27/26 ,  B64C27/30 ,  B64C27/32 ,  B64C29/02 ,  B64C2027/7266 ,  B64C27/473 ,  B64C27/72 ,  B64C29/0025

Abstract: A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

公开(公告)号：WO2020247148A2

公开(公告)日：2020-12-10

申请号：PCT/US2020/032107

申请日：2020-05-08

Applicant: DETROIT AIRCRAFT CORPORATION

Inventor： RIMANELLI, Jon ,  LOKHANDWALA, Qhase

IPC: B64C29/02 ,  B64C3/38 ,  B64C27/28 ,  B64C27/08 ,  B64C27/22 ,  B64C27/24 ,  B64C2211/00 ,  B64C29/0033 ,  B64C3/385 ,  B64D27/24

Abstract: An electrically powered vertical takeoff and landing aircraft (EVTOL) includes a payload module, a plurality of electrical power sources, a wing, and a plurality of electric thrust generators. The wing is pivotally attached to the payload module and is configured to pivot about a pivot axis, relative to the payload module, to transition between vertical flight and horizontal flight. The electric thrust generators are operatively attached to the wing, where each one is operatively connected to a different electrical power source. The electric thrust generators operate to provide thrust to the aircraft in response to receiving electric power from the electrical power sources. The electric thrust generators pivot, with the wing, about the pivot axis, relative to the payload.