公开(公告)号：WO00068077A1

公开(公告)日：2000-11-16

申请号：PCT/US2000/007237

申请日：2000-03-16

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。

公开(公告)号：EP3057867B1

公开(公告)日：2018-08-29

申请号：EP14878419.2

申请日：2014-10-10

Applicant: Swift Engineering, Inc.

Inventor： GODLASKY, Robert ,  OGAWA, Nate ,  STREETT, Andrew

IPC: B64C29/00 ,  B64C3/56 ,  B64D27/02 ,  B64C29/02 ,  B64C5/02

CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

公开(公告)号：EP3348476A1

公开(公告)日：2018-07-18

申请号：EP17189253.2

申请日：2017-09-04

Applicant: Cai, Bo

Inventor： Cai, Bo

IPC: B64C39/00

CPC classification number: B64C1/00 ,  B64C25/06 ,  B64C39/005 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2201/02 ,  B64C2201/088 ,  B64C2201/108

Abstract: The invention provides an ellipsoidal aircraft, wherein the housing (8) is provided with an upper cover (1) and a pedestal (6), the pedestal is coaxial with the housing, a whirling arm (2) is arranged at a junction between the upper cover and the housing, and a fixing sleeve (9) internally equipped with a motor (5) is arranged at a middle position of a lower side of the whirling arm. Such design effectively prevents blades and the motor from being damaged due to loosening of the whirling arm during transmission and solves the problem that conventional equipment is easily damaged.

公开(公告)号：EP3263456A1

公开(公告)日：2018-01-03

申请号：EP17179010.8

申请日：2017-06-30

Applicant: Bell Helicopter Textron Inc.

Inventor： OLDROYD, Paul K ,  McCULLOUGH, John Richard

IPC: B64C39/02 ,  B64C29/00 ,  B64D27/06 ,  B64D27/24 ,  B64D31/00 ,  B64D35/08 ,  B64D27/02 ,  B64D27/26

CPC classification number: B64D27/12 ,  B64C11/46 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2211/00 ,  B64D27/06 ,  B64D27/24 ,  B64D27/26 ,  B64D31/00 ,  B64D35/08 ,  B64D2027/026 ,  B64D2027/262 ,  Y02T50/62

Abstract: An aircraft (10) having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft (10) includes an airframe (12) and a versatile propulsion system attached to the airframe (12). The versatile propulsion system includes a plurality of propulsion assemblies (26a-d). A flight control system (40) is operable to independently control the propulsion assemblies (26a-d). The propulsion assemblies (26a-d) are interchangeably attachable to the airframe (12) such that the aircraft (10) has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies (26a-d) from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies (26a-d) from an electric power source.

Abstract translation: 一种具有垂直起降战斗模式和向前飞行模式的飞机（10）。 飞机（10）包括机身（12）和附接到机身（12）的多功能推进系统。 多功能推进系统包括多个推进组件（26a-d）。 飞行控制系统（40）可操作以独立地控制推进组件（26a-d）。 推进组件（26a-d）可互换地附连到机身（12），使得飞机（10）具有液体燃料飞行模式和电动飞行模式。 在液体燃料飞行模式中，能量从液体燃料提供给每个推进组件（26a-d）。 在电动飞行模式中，能量从电源被提供给每个推进组件（26a-d）。

公开(公告)号：EP3260370A1

公开(公告)日：2017-12-27

申请号：EP17176471.5

申请日：2017-06-16

Applicant: Parrot Drones

Inventor： LAVAGEN, Gauthier ,  MARI-MARI, Marc ,  BENATAR, Yoni ,  BARSE, Thomas

IPC: B64C29/00 ,  A63H27/00

CPC classification number: B64C27/26 ,  A63H27/12 ,  B64C3/32 ,  B64C11/46 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/02 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187

Abstract: L'invention concerne un drone à voilure tournante (10) comprenant un corps de drone (12) comprenant une carte électronique contrôlant le pilotage du drone, quatre bras de liaison (16) comprenant fixé solidairement un bloc propulseur (14). Les bras de liaison (16) forment des ailes portantes.

Abstract translation: 本发明涉及一种包括无人驾驶飞机主体（12）的旋翼无人机（10），所述无人驾驶飞机主体包括控制无人驾驶飞机驾驶的电子卡，包括固体固定式推进剂单元（14）的四个连杆臂（16）。 连接臂（16）形成承重翼。

公开(公告)号：EP3230161A1

公开(公告)日：2017-10-18

申请号：EP15808600.9

申请日：2015-12-11

Applicant: Université Pierre et Marie Curie - UPMC ,  Centre National de la Recherche Scientifique

Inventor： MORIN, Pascal ,  GASTE, Olivier ,  PHUNG, Duc-Kien

IPC: B64C3/38 ,  B64C27/22 ,  B64C29/00

CPC classification number: B64C29/0025 ,  B64C3/385 ,  B64C13/28 ,  B64C27/26 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  Y02T50/14

Abstract: The disclosure thus relates to a light unmanned vertical takeoff aerial vehicle (1) which comprises at least two fixed coplanar propulsion devices (7) and at least one wing (3) providing the drone (1) with lift. The coplanar propulsion devices (7) and the wing (3) are each arranged on the framework (10) of the drone (1) such that the plane of the chord of the profile of the wing (3) is substantially parallel to the plane defined by the two coplanar propulsion devices (7). The wing (3) is capable of a pivoting movement with respect to the framework (10) about an axis parallel to the pitch axis of the drone (1). The disclosure also relates to a method for controlling a light unmanned aerial vehicle (1) like the one described hereinabove, which involves a step of controlling the orientation of the wing (3), which uses at least one parameter pertaining to the flight of the drone (1).

Abstract translation: 因此，本公开涉及一种轻型无人垂直起飞架空飞行器（1），其包括至少两个固定共面推进装置（7）和至少一个提供无人驾驶飞机（1）的升降机翼（3）。 共面推进装置（7）和机翼（3）分别布置在无人驾驶飞机（1）的框架（10）上，使得机翼（3）的轮廓翼弦的平面基本平行于平面 由两个共面推进装置（7）限定。 机翼（3）能够围绕平行于无人机（1）的俯仰轴线的轴线相对于框架（10）枢转运动。 本公开还涉及一种用于控制如上文所述的轻型无人驾驶飞行器（1）的方法，其包括控制机翼（3）的方位的步骤，该方法使用至少一个与飞行器 无人机（1）。

公开(公告)号：EP2914490B1

公开(公告)日：2017-05-24

申请号：EP13811348.5

申请日：2013-10-22

Applicant: AIRBUS DEFENCE AND SPACE GMBH

Inventor： STEINWANDEL, Jürgen ,  STAGLIANO, Florian ,  VAN TOOR, Jan

IPC: B64C39/02 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  F02D29/02

CPC classification number: F02D29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/16 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

公开(公告)号：EP3162709A1

公开(公告)日：2017-05-03

申请号：EP15275226

申请日：2015-10-30

Applicant: BAE SYSTEMS PLC

IPC: B64C29/02 ,  B64C37/00 ,  B64C39/02 ,  H04N5/232

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C37/00 ,  B64C2201/088 ,  B64C2201/123 ,  B64C2201/127 ,  H04N5/2252 ,  H04N5/23238 ,  H04N7/185

Abstract: An air vehicle (10) comprising a main body (12) and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12) having a principal axis orthogonal to the longitudinal axis (20) of said wing members, at least a first propulsion device (16a) associated with a first of said wing members arranged and configured to generate a linear thrust relative to the main body in a first direction, and a second propulsion device (16b) associated with a second of said wing members arranged and configured to generate linear thrust relative to said main body in a second, substantially opposite, direction such that said wing members and said main body are caused to rotate about said principal axis, in use, the air vehicle further comprising an imaging system (100) configured to cover a substantially 360o imaging area about said principal axis and comprising at least one electro-optic sensor (102) mounted on a support member (104) and having a field of view (102a) covering a portion of said imaging area, said support member being mounted on said air vehicle, said imaging system (100) further comprising a control module (400) configured to define an object or region of interest in relation to said air vehicle, determine a nominal sensor field of view incorporating said object or region of interest, and obtain sequential image data from a sensor having a field of view matching said nominal field of view as said air vehicle completes a rotary cycle.

Abstract translation: 1。一种飞行器（10），包括主体（12）和从主体（12）大致横向延伸的一对相对的翼部件（14a，14b），所述翼部件具有与所述翼部的纵向轴线 至少第一推进装置（16a）和第二推进装置（16b），所述第一推进装置（16a）与所述翼构件中的第一个相关联，所述第一推进装置布置和构造成相对于主体在第一方向上产生线性推力， 所述翼构件布置和构造成在第二基本相反的方向上相对于所述主体产生线性推力，使得所述翼构件和所述主体围绕所述主轴线旋转，在使用中，所述飞行器还包括 成像系统（100），所述成像系统（100）被配置为覆盖围绕所述主轴的基本上360°的成像区域并且包括安装在支撑构件（104）上并且具有视场（102a）co的至少一个电光传感器（102） 所述成像系统（100）还包括控制模块（400），所述控制模块（400）被配置为限定与所述飞行器相关的目标或感兴趣区域，确定所述成像区域的一部分，所述支撑部件安装在所述飞行器上， 标称感测器视场，并且当所述飞行器完成旋转周期时，从具有与所述标称视场相匹配的视场的传感器获得连续图像数据。

公开(公告)号：EP3162708A1

公开(公告)日：2017-05-03

申请号：EP15275224

申请日：2015-10-30

Applicant: BAE SYSTEMS PLC

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/18

Abstract: An air vehicle (10) comprising a main body (12)and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12), at least a first propulsion device (16) associated with a first of said wing members (14a) and a second propulsion device (16) associated with a second of said wing members (14b), each said propulsion device (16) being arranged and configured to generate linear thrust relative to said main body (12), in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode (Figure 2) and a rotary wing mode (Figure 3), wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body (12) is the same as the direction of thrust generated by the second propulsion device (16), and in said second mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body is opposite to that generated by the second propulsion device (16).

Abstract translation: 1。一种飞行器（10），包括主体（12）和从主体（12）大致横向延伸的一对相对的翼构件（14a，14b），至少第一推进装置（16）与第一 所述翼部件（14a）和与所述翼部件（14b）中的第二翼部件相关联的第二推进装置（16），每个所述推进装置（16）被布置和构造成相对于所述主体（12）产生线性推力， 在使用中，所述飞行器还包括控制模块，所述控制模块用于生成控制信号，所述控制信号被配置成在使用中在固定翼模式（图2）和旋翼模式（图3）之间改变所述飞行器的飞行模式， 其中，在所述固定翼飞行模式中，由所述第一推进装置（16）相对于所述主体（12）产生的推力的方向与由所述第二推进装置（16）产生的推力的方向相同，并且 在所述第二飞行模式中，由第一模式产生的推力的方向 推进装置（16）相对于主体与第二推进装置（16）产生的相反。

公开(公告)号：EP3162707A1

公开(公告)日：2017-05-03

申请号：EP15275222

申请日：2015-10-30

Applicant: BAE SYSTEMS PLC

IPC: B64C29/00 ,  A63H27/00 ,  A63H27/14

CPC classification number: B64C29/00 ,  A63H27/12 ,  A63H27/14 ,  B64C2201/08 ,  B64C2201/088 ,  B64C2201/18

Abstract: A rotary-wing air vehicle comprising a main body (12) and at least two rotor devices (16a, 16b) arranged and configured to generate propulsion and thrust, in use, to lift and propel said air vehicle, said rotor devices (16a, 16b) being arranged and configured relative to said main body (12) such that the blades thereof do not cross through a central vertical axis of said main body (12) defining the centre of mass thereof, wherein said main body (12) is provided with an aperture (100) that extends therethrough to define a channel about said central vertical axis.

Abstract translation: 一种旋转翼飞行器，包括主体（12）和至少两个转子装置（16a，16b），所述转子装置（16a，16b）布置和构造成在使用中产生推进和推力以提升和推进所述飞行器，所述转子装置（16a， 16b）相对于所述主体（12）布置和构造成使得其叶片不穿过限定其质量中心的所述主体（12）的中心竖直轴线，其中提供所述主体（12） 具有穿过其延伸的孔口（100）以限定围绕所述中心竖直轴线的通道。