公开(公告)号：WO2008140851A2

公开(公告)日：2008-11-20

申请号：PCT/US2008/055252

申请日：2008-02-28

Applicant: LAWRENCE, John, M.

Inventor： LAWRENCE, John, M.

IPC: B64C29/00 ,  B64C27/08

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

Abstract: A rotorcraft having two coaxial, counter-rotating rotors, one proximate to the forward end of the fuselage and one proximate to the aft end of the fuselage, that generate the forces necessary to lift the craft and maneuver it in the air by adjusting the pitch of the rotor blades throughout their rotation, and a method of flying a dual rotor rotorcraft involving taking off in a vertical orientation, climbing vertically, transitioning to generally horizontal flight, flying horizontally, and subsequently repeating the sequence in reverse to land again in a vertical orientation.

Abstract translation: 旋翼飞机具有两个同轴的反向旋转的转子，一个靠近机身前端，一个靠近机身的后端，产生提升飞机所需的力，并通过调节俯仰 的转子叶片的旋转方法，以及一种使双转子旋翼飞行器飞行的方法，其包括垂直取向垂直移动，垂直攀升，水平飞行大致水平飞行，随后重复反向顺序以在垂直方向上重新着陆 方向。

公开(公告)号：WO2019142014A1

公开(公告)日：2019-07-25

申请号：PCT/IB2018/050313

申请日：2018-01-18

Applicant: AERONES, SIA

Inventor： PUTRĀMS, Jānis

IPC: B64C29/00 ,  B64C39/02 ,  B64C31/02

CPC classification number: B64C39/024 ,  B64C29/00 ,  B64C31/02 ,  B64C2201/042 ,  B64C2201/088

Abstract: The invention relates to electric drones and gliders. The electric drone glider arrangement comprising: a heavy-lift multi-rotor drone with batteries; a manned or unmanned glider; a high voltage generator; an electric cable and rope connecting the drone and the glider; an electric cable and rope connecting the glider and the generator. The cable and rope connecting the glider and the generator being detachably attached to the glider, such that the cable and the rope can be disconnected from the glider once the glider is raised to the sufficient height. The cable and rope connecting the glider and the drone has adjustable length and at both ends is connected to the center of gravity of the drone and the glider.

公开(公告)号：WO2019007433A1

公开(公告)日：2019-01-10

申请号：PCT/CN2018/094912

申请日：2018-07-06

Applicant: TIAN, Yu

Inventor： TIAN, Yu

IPC: B64C27/26

CPC classification number: B64C29/0025 ,  B64C5/08 ,  B64C39/024 ,  B64C39/04 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  G05D1/0858

Abstract: A long-distance drone (100) and a method of improving stability, robustness, endurance and/or durability of the drone (100) and a method of controlling a roll motion of the drone (100) are provided. The drone (100) includes a main body (110), two main wings (113, 114) and two forewings(111, 112), a left linear support (120) spaced apart from said main body (110) connecting the left forewing (111) to the left main wing (113), a right linear support (121) spaced apart from said main body (110) connecting the right forewing (112) to the right main wing (114), at least two propellers (131,132,133) coupled to the left linear support (120), at least two propellers (134,135,136) coupled to the right linear support (121). Therefore, the drone (100) is sufficiently efficient to travel longer distances, and when one propeller (131,132,133,134,135,136) fails, the drone (100) may still function and continue to stay in the air.

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。

公开(公告)号：WO2017040956A1

公开(公告)日：2017-03-09

申请号：PCT/US2016/050144

申请日：2016-09-02

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： SYLVIA, Russell, M.

IPC: B64F1/06 ,  B64C39/02

CPC classification number: B64F1/04 ,  B63G8/28 ,  B63G2008/008 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/088 ,  B64C2201/20 ,  B64C2201/201 ,  B64C2201/205

Abstract: A payload launch system that uses an inflatable air bag ram to launch a payload, such as an unmanned aerial vehicle, from a launch chamber of a launch tube. The air bag ram seals with the interior surface of the launch tube to isolate a dump valve that controls the flow of compressed gas from a gas storage chamber into the air bag ram. The air bag ram sealing with the interior surface of the launch tube isolates the dump valve, both pre-launch and post-launch, from any water or debris carried in with water in which the payload launch system is disposed

Abstract translation: 一种有效载荷发射系统，其使用可充气气囊压头从发射管的发射室发射有效载荷，例如无人驾驶飞行器。 气囊柱塞与发射管的内表面密封，以隔离一个排气阀，其将压缩气体从气体储存室流入气囊冲头。 与发射管的内表面密封的气囊柱塞将排放阀，预发射和发射后的任何水分或污染物与运载有有效载荷发射系统的水一起分离

公开(公告)号：WO2016130716A2

公开(公告)日：2016-08-18

申请号：PCT/US2016/017407

申请日：2016-02-10

Applicant: AEROVIRONMENT, INC.

Inventor： FISHER, Christopher Eugene ,  MUKHERJEE, Jason Sidharthadev ,  LOTT, William Arden

IPC: G06Q10/08 ,  B64D43/00

CPC classification number: G05D1/102 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/123 ,  B64C2201/141 ,  B64C2201/201 ,  B64D47/08 ,  B64F1/005 ,  G06F17/30241 ,  G06Q30/016 ,  G08G5/0021 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0056 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/0078 ,  G08G5/0091 ,  G08G5/025

Abstract: A method of unmanned aerial vehicle (UAV) operation, including: receiving from a customer a first data request (400), the first data request (400) having: a first geographic coverage area, and a refresh rate for the first geographic coverage area, planning a first plurality of flight missions to accomplish the first data request, uploading flight missions data representing the first plurality of flight missions into a UAV pod (404), and deploying the UAV pod (802).

Abstract translation: 一种无人飞行器（UAV）操作的方法，包括：从客户接收第一数据请求（400），所述第一数据请求（400）具有：第一地理覆盖区域和第二地理覆盖区域 计划第一多个飞行任务以完成第一数据请求，将表示第一多个飞行任务的飞行任务数据上传到UAV舱（404），以及部署UAV舱（802）

公开(公告)号：WO2015012935A3

公开(公告)日：2015-05-14

申请号：PCT/US2014036863

申请日：2014-05-05

Applicant: AEROVIRONMENT INC ,  TAYLOR DANA J ,  TOKUMARU PHILLIP T ,  HIBBS BART DEAN ,  PARKS WILLIAM MARTIN ,  GANZER DAVID WAYNE ,  FISHER CHRISTOPHER EUGENE ,  MUKHERJEE JASON SIDHARTHADEV ,  KING JOSEPH FREDERICK

Inventor： TAYLOR DANA J ,  TOKUMARU PHILLIP T ,  HIBBS BART DEAN ,  PARKS WILLIAM MARTIN ,  GANZER DAVID WAYNE ,  FISHER CHRISTOPHER EUGENE ,  MUKHERJEE JASON SIDHARTHADEV ,  KING JOSEPH FREDERICK

IPC: B64C29/02

CPC classification number: B64C29/0025 ,  B64C11/32 ,  B64C27/26 ,  B64C27/54 ,  B64C27/605 ,  B64C29/00 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  G05D1/0858

Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing (115) and first starboard wing (120), a first port swash plate (145) coupled between a first port rotor 155) and first port electric motor (135), the first port electric 5 motor (135) coupled to the first port wing (115), and a first starboard swash plate (150) coupled between a first starboard rotor (130) and first starboard electric motor (140), the first starboard electric motor (140) coupled to the first starboard wing (120).

Abstract translation: 一种用于固定翼飞机的飞行控制装置，包括：第一端口翼（115）和第一右舷翼（120），联接在第一端口转子（155）与第一端口电动机（135）之间的第一端口斜板（145） 联接到第一端口机翼（115）的第一端口电动机（135）以及联接在第一右舷转子（130）和第一右舷电动机（140）之间的第一右舷斜盘（150），第一右舷电动机 马达（140）联接到第一右舷翼（120）。

公开(公告)号：WO2014177591A1

公开(公告)日：2014-11-06

申请号：PCT/EP2014/058767

申请日：2014-04-29

Applicant: REITER, Johannes

Inventor： REITER, Johannes

IPC: B64C29/00 ,  B64C29/02

CPC classification number: B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/108

Abstract: The present invention relates to an aircraft (100) for vertical take-off and landing. A wing arrangement (110) is coupled to a fuselage (101) such that the wing arrangement (110) is tiltable around a longitudinal wing axis of the wing arrangement (110) and such that the wing arrangement (110) is rotatable around the fuselage (101). The wing arrangement (110) is adapted in such a way that, in a fixed-wing flight mode, the wing arrangement (110) does not rotate around the fuselage (101). The wing arrangement (110) is further adapted in such a way that, in a hover flight mode, the wing arrangement (110) is tilted around the longitudinal wing axis with respect to its orientations in the fixed-wing flight mode and that the wing arrangement (110) rotates around the fuselage (101). An engine (120) comprising a drive shaft (121) with an engine rotary axis (122), wherein the engine (120) is coupled to the wing arrangement (110) in such a way that in the hover flight mode the engine rotary axis (122) comprise at least one component which is parallel to a rotary axis (102) of the wing arrangement (110) around the fuselage (101).

Abstract translation: 本发明涉及用于垂直起飞和着陆的飞行器（100）。 机翼装置（110）联接到机身（101），使得机翼装置（110）围绕机翼装置（110）的纵向翼轴可倾斜，并且使得机翼装置（110）可围绕机身旋转 （101）。 机翼装置（110）适于使得在固定翼飞行模式中，机翼装置（110）不围绕机身（101）旋转。 机翼装置（110）进一步适应于使得在悬停飞行模式中，机翼装置（110）相对于其在固定翼飞行模式中的定向围绕纵向翼轴线倾斜，并且机翼 装置（110）绕机身（101）旋转。 一种发动机（120），包括具有发动机旋转轴线（122）的驱动轴（121），其中所述发动机（120）以这种方式联接到所述机翼装置（110），使得在所述悬停飞行模式下，所述发动机旋转轴 （122）包括平行于机身布置（110）围绕机身（101）的旋转轴线（102）的至少一个部件。

公开(公告)号：WO2014177589A1

公开(公告)日：2014-11-06

申请号：PCT/EP2014/058765

申请日：2014-04-29

Applicant: REITER, Johannes

Inventor： REITER, Johannes

IPC: B64C29/02

CPC classification number: B64C29/02 ,  B64C2201/088

Abstract: The present invention describes an aircraft (100) for vertical take-off and landing. The aircraft (100) comprises a fuselage (101) comprising a fuselage nose (103) and a fuselage tail (104), a wing arrangement (110) comprising a longitudinal wing axis and a coupling device (120) which couples the wing arrangement (110) to the fuselage (101), such that the wing arrangement (110), in a fixed-wing flight mode, does not rotate around the fuselage (101), and such that the wing arrangement (110), in a hover flight mode, is tilted around the longitudinal wing axis with respect to its orientation in the fixed-wing flight mode and that the wing arrangement (110) rotates around the fuselage (101). The wing arrangement (110) is coupled to the coupling device (120) such that in the hover flight mode a wing tip of the wing arrangement (110) is movable in a direction to the fuselage nose (103) or to the fuselage tail (104).

Abstract translation: 本发明描述了用于垂直起飞和着陆的飞行器（100）。 飞机（100）包括机身（101），其包括机身前端（103）和机身尾部（104），机翼装置（110）包括纵向翼轴线和联接装置（120） 110），使得机翼装置（110）以固定翼飞行模式不围绕机身（101）旋转，并且使得在悬停飞行中的机翼装置（110） 相对于其在固定翼飞行模式中的定向而围绕纵向翼轴线倾斜，并且机翼装置（110）围绕机身（101）旋转。 机翼装置（110）联接到联接装置（120），使得在悬停飞行模式中，机翼装置（110）的翼尖可沿机身鼻部（103）或机身尾部（103）的方向移动 104）。

公开(公告)号：WO2013060693A3

公开(公告)日：2013-08-15

申请号：PCT/EP2012070992

申请日：2012-10-23

Applicant: DESAULNIERS JEAN-MARC JOSEPH

Inventor： DESAULNIERS JEAN-MARC JOSEPH

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

CPC classification number: B64C39/024 ,  B63G8/001 ,  B63G8/16 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64G1/002 ,  B64G1/24 ,  B64G1/40

Abstract: The invention relates to an active geometric exoskeleton device (FIG. l) for a multi environment, multi mode, vertical or horizontal take off and landing gyropendular piloted craft or drone with compensatory propulsion and fluidic gradient collimation capable of moving in the following various physical environments: on land, in the air, in or under the sea or in space, comprising an active pseudo-rhombohedral annular fairing which 1) protects the various propulsion units and the payload by absorbing impacts, 2) corrects the trim and reorientates the trajectory upon collisions with any obstacle in the physical environment or the terrain, such a craft being provided with upper, intermediate and lower propulsion units, and with a hollow annular vertebral structure incorporating a payload containing the application functions suited to various domains: 1) civil defence emergency preparedness in the context of search and rescue activities, 2) exploration, navigation, transport, surveillance, 3) detection of deposits of hydrocarbons or ores, of boreholes or pump holes on land, under water or in space, 4) supporting and stabilizing a mobile, free or tethered submerged pontoon for a wind turbine or a water turbine, 5) maintenance work, 6) endovascular or intra-cavity navigation and intravention during surgery, 7) land, aerial, underwater or space telecommunications, and 8) deployment of telecommunications infrastructure in free space.

Abstract translation: 本发明涉及一种用于多环境，多模式，垂直或水平起飞和降落的回旋引导飞行器或具有补偿推进和流体梯度准直的主动几何外骨骼装置（图1），其能够在以下各种物理环境中移动 ：在陆地，空中，海上或海下或空间内，包括一个活跃的假菱形环形整流罩，1）通过吸收冲击来保护各种推进单元和有效载荷，2）纠正修剪并重新定位轨迹 与物理环境或地形中的任何障碍物的碰撞，这种飞行器具有上部，中间和下部推进单元，并且具有包含适用于各种领域的应用功能的有效载荷的中空环形椎骨结构：1）民防应急 在搜救活动中做好准备，2）勘探，导航，运输，监视， 3）在陆地，水下或太空中检测碳氢化合物或矿石，钻孔或泵孔的沉积物; 4）支撑和稳定风力涡轮机或水轮机的移动式，自由或系泊淹没式浮筒; 5）维护工作 6）手术期间血管内或腔内导航和干预措施，7）陆地，空中，水下或空间电信，以及8）在自由空间部署电信基础设施。