公开(公告)号：WO2022150534A1

公开(公告)日：2022-07-14

申请号：PCT/US2022/011527

申请日：2022-01-07

Applicant: UNIVERSITY OF CINCINNATI

Inventor： ABDALLAH, Shaaban

IPC: B64C27/10 ,  B64C11/28 ,  B64C11/48 ,  B64C19/00 ,  B64C27/08 ,  B64C27/22

Abstract: A propulsion system (50) is disclosed. The propulsion system (50) includes a first propeller (52), a second propeller (54), and a third propeller (56). The first propeller (52), the second propeller (54), and the third propeller (56) are arranged to rotate about a common axis and the second propeller (54) is disposed between the first propeller (52) and the third propeller (56). The first and third propellers (52, 56) are configured to rotate about the common axis in a first direction (A) and the second propeller (54) is configured to rotate about the common axis in a second direction (B) opposite to the first direction (A). A first motor (60) may be coupled to the first and third propellers (52, 56) and a second motor (64) may be coupled to the second propeller (54). A first shaft (58) and second shaft (62) may be arranged along the common axis, wherein the first and third propellers (52, 56) are coupled to the first shaft (58) and the second propeller (54) is coupled to the second shaft (62).

公开(公告)号：WO2022113086A1

公开(公告)日：2022-06-02

申请号：PCT/IL2021/051417

申请日：2021-11-29

Applicant: EFIX AVIATION LTD

Inventor： KASTIEL, Efraim

IPC: B64C27/52 ,  B64C39/02 ,  B64C27/08 ,  B64C27/54 ,  B64C27/22

Abstract: Rotorcraft including a fuselage, at least three rotor system arms, a forward propulsion unit for providing forward propulsion to the rotorcraft and a flight control system. Each rotor system arm has a rotor system including a mast having at least two rotor blades and an electric rotor motor coupled to the mast for driving the mast whereupon the rotor blades act as a rotating rotor disc. Each rotor system has an individually controllable collective rotor blade pitch. At least one rotor system has a controllable cyclic rotor blade pitch. The flight control system controls the at least three electric rotor motors, the collective rotor blade pitch of each rotor system, the cyclic rotor blade pitch of the at least one rotor system and the forward propulsion unit in response to an input control indicating a desired maneuver to operate the rotorcraft for takeoff, flight and landing.

公开(公告)号：WO2022033305A1

公开(公告)日：2022-02-17

申请号：PCT/CN2021/108890

申请日：2021-07-28

Applicant: 深圳市道通智能航空技术股份有限公司

Inventor： 梁邦平

IPC: B64C39/02 ,  B64D27/24 ,  B64C27/26 ,  B64C27/22 ,  B64D47/02 ,  B64C29/00

Abstract: 一种无人机控制方法、装置及存储介质，通过获取无人机的飞行控制指令，并根据飞行控制指令确定目标翼尖模式，根据目标翼尖模式调节翼尖（30）与机翼（20）两者的相对角度，从而，无人机通过调节翼尖（30）相对于机翼（20）的角度实现无人机在多旋翼模式和固定翼模式之间自如切换，进而控制无人机的飞行方式，使得无人机在飞行时能根据不同的飞行阶段切换至目标翼尖模式，以适应多种飞行阶段的飞行，提高了无人机飞行的稳定性。

公开(公告)号：WO2021201991A2

公开(公告)日：2021-10-07

申请号：PCT/US2021/017497

申请日：2021-02-10

Applicant: WISK AERO LLC

Inventor： TIGHE, James Joseph ,  TZARNOTZY, Uri ,  LONG, Geoffrey Alan

IPC: B64C27/26 ,  B64C5/02 ,  B64C5/06 ,  B64C5/08 ,  B64C27/22 ,  B64C27/28 ,  B64C27/32 ,  B60L2200/10 ,  B60L50/50 ,  B64C11/00 ,  B64C29/0025 ,  B64D27/24 ,  G05D1/0669 ,  G05D1/102

Abstract: Embodiments provide an electric aircraft with a plurality of lift fan assemblies that are configured to provide vertical lift, and one or more pusher propellers that are configured to provide forward thrust. The lift fan assemblies may be coupled to the wings of the aircraft via one or more support structures, and the wings may be coupled to an upper region of the fuselage. The pusher propeller(s) may be coupled to a tailing end of the fuselage. The lift fan assemblies and the pusher propeller(s) may provide thrust and movement in directions that are orthogonal to one another. A control system coupled to the aircraft may control the lift fan assemblies and the one or more pusher propellers to activate, increase in power, and decrease in power. The lift fan assemblies and the one or more pusher propellers may be operated separately, and may be active at different times.

公开(公告)号：WO2021130719A1

公开(公告)日：2021-07-01

申请号：PCT/IB2020/062437

申请日：2020-12-24

Applicant: LEONARDO S.P.A.

Inventor： PISANI, Paolo ,  MONTAGNA, Federico ,  REGONINI, Roberto ,  PODDA, Daniele

IPC: B64C27/14 ,  B64C27/00 ,  B64D35/00 ,  B64D35/04 ,  B64D35/08 ,  B64C27/22 ,  B64C27/006

Abstract: An aircraft (1) is described comprising a transmission unit (9) with a first module (11, 13, 15) and a lubrication system (25, 25'); the first module (11, 13, 15) comprises a casing (20) and a movable member (17, 18, 19); the lubrication system (25, 25') comprises a header (26), a nozzle (27, 28) fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing (20) of the first module (11, 13, 15), a collection tank (30, 100') for the lubricating fluid injected by the nozzle (27, 28), and recirculation means (35) designed to cause the recirculation of the lubricating fluid from the collection tank (30, 100') to the feed header (26); the first module (11, 13, 15) comprises a valve (60, 60') available in a first configuration, in which it enables the outflow of said lubricating fluid from said module (11) to the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module (11) from the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is less than the threshold value.

公开(公告)号：WO2021039653A1

公开(公告)日：2021-03-04

申请号：PCT/JP2020/031691

申请日：2020-08-21

Applicant: 株式会社デンソー

Inventor： 岩川　輝 ,  橋本　真梨子 ,  杉田　俊 ,  竹村　優一

IPC: B64C27/22 ,  B64D5/00

Abstract: 電動垂直離着陸機（１００、１００ａ～１００ｄ）は、複数の回転翼（３０）と各回転翼を回転駆動させるモータ（１１１）を有する複数の電駆動システム（１０）と、複数の回転翼と電駆動システムとが配置された機体（２０）と、機体における上方側と下方側とのうちの少なくとも一方に設けられ、他の電動垂直離着陸機である他機と連結するための連結部（２９、ＣＰ１～ＣＰ４、ＣＰｂ、ＣＰｃ、ＣＰｄ１、ＣＰｄ２）と、を備える。

公开(公告)号：WO2021030630A2

公开(公告)日：2021-02-18

申请号：PCT/US2020/046240

申请日：2020-08-13

Applicant: UNMANNED AEROSPACE LLC

Inventor： SHAANAN, Gad

IPC: B64C27/08 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C27/82 ,  B64C27/14 ,  B64C27/54 ,  B64C27/10 ,  B64C27/32 ,  B64C27/02 ,  B64C11/46 ,  B64C29/00 ,  B64C7/00

Abstract: Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation.

公开(公告)号：WO2020190223A1

公开(公告)日：2020-09-24

申请号：PCT/TR2019/050183

申请日：2019-03-21

Applicant: AÇIKEL, Gürkan

Inventor： AÇIKEL, Gürkan

IPC: B64C1/00 ,  B64C25/00 ,  B64C27/22 ,  B64C29/00

Abstract: VTOL aircraft that takeoff and land as a multirotor and cruises as airplane. The aircraft comprises two major parts: First; winged carrier frame comprises wings, engines, propellers and landing gears. Second; tilting fuselage comprises cockpit, cabin and tail. Winged carrier frame is basically X/H frame multirotor that its thruster carrying arms are wing shaped. Aircraft vertically takeoff as multirotor after gaining safe altitude and forward airspeed then changes its flying axis that wings and thrust direction parallel to horizon. Lift generated by wings and thrust generated by thrusters that aircraft has basic airplane flying characteristics. Fuselage tilted to keep payload parallel to the horizon. Speed reduced, winged carrier frame and fuselage returned to multirotor for landing. It is easier to rotate fuselage than thrusters or wings. It is better to adjust thrust levels than vectoring to reduce the moving parts and aerodynamic effects.

公开(公告)号：WO2020107373A1

公开(公告)日：2020-06-04

申请号：PCT/CN2018/118416

申请日：2018-11-30

Applicant: 深圳市大疆创新科技有限公司

Inventor： 韩杰星

IPC: B64C27/22 ,  B64D27/02

Abstract: 一种动力组件、动力系统及无人机。该动力组件包括：发动机、传动机构、发电机以及电池，传动机构包括与发动机的输出轴传动连接的第一驱动轴和第二驱动轴，第一驱动轴用于驱动推进螺旋桨转动，第二驱动轴用于驱动发电机发电；发电机与电池电连接，以便为电池充电；电池用于驱动水平旋翼转动。动力系统包括上述动力组件。无人机包括上述动力系统。该无人机实现了发动机在驱动螺旋浆的同时为电池充电的功能，使得无人机无需配置大电池，延长了无人机的水平飞行时间；由于电池可以驱动水平旋翼，且电池中已亏损的电量可以由发动机进行补充，增加了无人机的悬停次数。

公开(公告)号：WO2018151777A1

公开(公告)日：2018-08-23

申请号：PCT/US2017/059809

申请日：2017-11-02

Applicant: JOBY AVIATION, INC.

Inventor： BEVIRT, Joeben ,  STOLL, Alex ,  MIKIC, Gregor, Veble

IPC: B64C27/08 ,  B64C27/00 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52

Abstract: A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.