公开(公告)号：WO03095268A2

公开(公告)日：2003-11-20

申请号：PCT/US0314922

申请日：2003-05-13

Applicant: EAST WEST IND ,  SPINOSA DOMINIC ,  KNOLL FRANK ,  WALSH JEFFREY F

Inventor： SPINOSA DOMINIC ,  KNOLL FRANK ,  WALSH JEFFREY F

IPC: B21K21/16 ,  B60R20060101 ,  B64C27/22 ,  B64C39/00 ,  B64D11/06 ,  B64D25/06 ,  B64D25/10 ,  B60R

CPC classification number: B64D25/10 ,  B64D25/06 ,  Y10T29/49716 ,  Y10T29/49895 ,  Y10T408/08

Abstract: A method and kit for retrofitting an inertia reel door onto the seat back of a preconstructed ejection seat is disclosed. The method includes removing existing rivets from the seat back exposing rivet holes. Alignment holes are then drilled into the seat back. An aperture is cut into the seat back along flanges of an upper support bracket and a drogue chute bracket. A doubler is aligned with the rivet holes and alignment holes in the seat back and then attached to the seat back. A track is attached to a wall of the aperture and an inertia reel is mounted to the track. An inertia reel door is attached to the doubler.

Abstract translation: 公开了一种用于将惯性卷轴门改装到预先构造的弹射座椅的座椅靠背上的方法和套件。 该方法包括从座椅背部去除暴露铆钉孔的现有铆钉。 然后将对准孔钻进座椅靠背。 沿着上支撑支架的凸缘和锥形滑槽支架将孔径切割成座椅靠背。 倍增器与座椅靠背中的铆钉孔和对准孔对准，然后连接到座椅靠背。 轨道连接到孔的壁上，并且惯性卷轴安装到轨道上。 惯性卷轴门连接到倍加器。

公开(公告)号：WO2023060679A1

公开(公告)日：2023-04-20

申请号：PCT/CN2021/129539

申请日：2021-11-09

Applicant: 广东汇天航空航天科技有限公司

Inventor： 王谭 ,  梁毅诚 ,  史翊辰 ,  娄津源 ,  曹雪宇 ,  王伟民

IPC: B64C27/22 ,  B64C11/48

Abstract: 公布了一种飞行器（1）、一种机翼组件和飞行汽车，飞行器（1）包括机身（10）、机翼组件（20）、倾转连接件（30）和旋翼组件（50）。机翼组件（20）包括固定部（21）和折转部（23），固定部（21）设置于机身（10），折转部（23）可活动地连接于固定部（21），并且相对固定部（21）可折转；倾转连接件（30）可转动地设置于机翼组件（20）；旋翼组件（50）与倾转连接件（30）传动连接，以在倾转连接件（30）的带动下改变空间角度。本飞行器的机翼组件的折转部相对固定部可折转，使得机翼组件能够折叠，提高了飞行器在停泊及转场过程中的灵活性；另外，旋翼组件可以在倾转连接件的带动下改变空间角度，使得飞行器还具有垂直起飞及降落及平飞的功能，能够充分满足各场景出行需求。

公开(公告)号：WO2022271429A1

公开(公告)日：2022-12-29

申请号：PCT/US2022/032110

申请日：2022-06-03

Applicant: KITTY HAWK CORPORATION

Inventor： FRANK, Evan, E. ,  SRIDHARAN, Ananth ,  PAUL-DUBOIS-TAINE, Arthur

IPC: B64C29/00 ,  B64C11/06 ,  B64C11/46 ,  B64C27/20 ,  B64C27/22 ,  B64C27/26 ,  B64C13/26 ,  B64C29/0033 ,  B64D27/26

Abstract: A vehicle includes a fuselage, a wing, a pylon that is coupled to the wing, and a tractor tiltrotor. The tractor tiltrotor is coupled to the pylon and is located forward of the wing; the tractor tiltrotor tilts upwards during a hover mode. There is also a pusher tiltrotor where the pusher tiltrotor is coupled to the pylon and is located aft of the wing; the pusher tiltrotor tilts downwards during the hover mode. The tractor tiltrotor and the pusher tiltrotor rotate about a longitudinal and coaxial axis of rotation in a cruise mode.

公开(公告)号：WO2022048543A1

公开(公告)日：2022-03-10

申请号：PCT/CN2021/115736

申请日：2021-08-31

Applicant: 深圳市道通智能航空技术股份有限公司

Inventor： 汪康利

IPC: B64C27/22 ,  B64C27/52

Abstract: 一种飞行控制方法、无人机（100）及存储介质，飞行控制方法应用于无人机（100），通过确定无人机（100）所处环境的风力方向，若无人机（100）的机头方向与风力风向存在角度，则调整无人机（100）的机头方向与风力方向相对，从而将风力由侧风变成头风，然后，控制倾转旋翼（40）产生与风力大小相同、方向相反的水平矢量力以抵抗风力。

公开(公告)号：WO2021260459A1

公开(公告)日：2021-12-30

申请号：PCT/IB2021/054604

申请日：2021-05-26

Applicant: LEONARDO S.P.A. ,  POLITECNICO DI MILANO

Inventor： BOTTASSO, Luigi ,  POGGI, Stefano ,  WOODY, Phil ,  LOSI, Fabrizio ,  NAVA, Alessandro ,  SARTORI, Sergio ,  SIMONETTA, Roberto ,  AIROLDI, Alessandro ,  BOIOCCHI, Matteo

IPC: B64C27/12 ,  F16D3/70 ,  F16D21/02 ,  F16D3/62 ,  F16D3/72 ,  F16D3/74 ,  F16D3/50 ,  B64C27/22 ,  B64C29/0033 ,  F16D3/725

Abstract: A rotor (8, 8', 106''', 106'''', 106''''', 106'''''') for an aircraft (1, 100) is described, comprising an input shaft (10, 108) rotatable around a first axis (C, I); an output member (15, 112) rotatable around a second axis (D, J); a coupling element (20, 20', 20'', 20''') functionally interposed between the input shaft (10, 108) and the output member (15, 112) and adapted to transmit the motion from the input shaft (10, 108) to the output member (15, 112); the coupling element (20, 20', 20'', 20''') is configured to allow, in use, a fixed or variable inclination between the respective first and second axes (C, I, D, J); the coupling element (20, 20', 20'', 20''') comprises at least a first corrugated element (21, 22, 25, 120''', 121''', 120'''', 121'''', 122'''') made of an elastically deformable material; the first corrugated element (21, 22, 25; 120''', 121'''; 120'''', 121'''', 122'''') allows the inclination through elastic deformation.

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：WO2021072070A1

公开(公告)日：2021-04-15

申请号：PCT/US2020/054778

申请日：2020-10-08

Applicant: KITTY HAWK CORPORATION

Inventor： SINHA, Pranay ,  VANDER LIND, Damon

IPC: B64C11/46 ,  B64C27/22 ,  B64C27/28 ,  B64C29/00 ,  B64C11/28 ,  B64C27/26 ,  B64C27/52 ,  B64C27/82

Abstract: A short takeoff and landing (STOL) vehicle which comprises a tail having a surface and a fuselage having a surface, where the tail and the fuselage have a continuity of surfaces where the surface of the tail is directly coupled to the surface of the fuselage. The vehicle further includes a forward-swept wing having a trailing edge and a rotor that is attached to the trailing edge of the forward-swept wing via a pylon, where the rotor has a maximum downward angle from horizontal that is less than or equal to 60° and the STOL vehicle takes off and lands using at least some lift from the forward-swept wing and at least some lift from the rotor.

公开(公告)号：WO2021016871A1

公开(公告)日：2021-02-04

申请号：PCT/CN2019/098405

申请日：2019-07-30

Applicant: 深圳市大疆创新科技有限公司

Inventor： 段武阳 ,  林灿龙 ,  张子豪

IPC: G05D1/00 ,  G05D3/12 ,  B64C27/22

Abstract: 本发明提供了一种无人飞行器控制方法、控制装置及计算机可读存储介质，其中，无人飞行器包括固定翼动力系统和旋翼动力系统，控制方法包括：在无人飞行器处于从固定翼动力系统工作状态切换至旋翼动力系统工作状态的减速过程中，确定无人飞行器的观测俯仰姿态；根据观测俯仰姿态控制旋翼动力系统以使无人飞行器的俯仰姿态角小于或等于最大俯仰姿态角。从而，可以避免无人飞行器在工作状态切换的减速过程中发生失稳倾翻，保证工作状态切换的稳定性，可以提升飞行安全性。

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.

公开(公告)号：WO2020202143A1

公开(公告)日：2020-10-08

申请号：PCT/IL2020/050378

申请日：2020-03-29

Applicant: COLUGO SYSTEMS LTD

Inventor： REGEV, Amit

IPC: B64C27/22 ,  B64C29/00

Abstract: A multirotor aircraft that comprises a body, at least three motors and at least one wing that is connected to the body. The wing is designed to be folded and unfolded during flight of the multirotor aircraft and designed to change during the flight a low-drag creation position to a lift creation position, and vice versa. At least one motor has a greater motor power than another motor and the distance from the strong motor to the center of gravity of the multirotor aircraft is shorter than the distance from the another motor to the center of gravity. The wing is positioned in the geometric area between the motors.