公开(公告)号：WO2021242535A2

公开(公告)日：2021-12-02

申请号：PCT/US2021/032258

申请日：2021-05-13

Applicant: PTERODYNAMICS INC.

Inventor： PETROV, Val

IPC: B64C29/00 ,  B64C29/02 ,  B64C27/26 ,  B64C3/56 ,  B64C27/28 ,  B64C29/0033 ,  G05D1/102

Abstract: Provided are computer-implemented methods for autonomously controlling an aircraft with vertical take-off and landing capabilities and folding wings that includes controlling a plurality of thrust producing components of an aircraft to cause the aircraft to rise vertically when wings of the aircraft are in a first folded configuration, where when the wings of the aircraft are in the first folded configuration, a leading edge of each wing is oriented in a vertical direction setting motor controller gains based on the wings of the aircraft being in the first folded configuration, and causing the aircraft to align with a direction of airflow when the wings of the aircraft are in the first folded configuration, and controlling thrust producing components and control surfaces and internal articulation mechanisms of the aircraft to cause the aircraft to transition from folded wing configuration to unfolded wing configuration. Systems and computer program products are also provided.

公开(公告)号：WO2021053786A1

公开(公告)日：2021-03-25

申请号：PCT/JP2019/036728

申请日：2019-09-19

Applicant: 株式会社エアロネクスト

Inventor： 鈴木陽一

IPC: B64C29/02 ,  B64C27/08

Abstract: 【課題】ホバリングから水平飛行への効率的かつ安全な移行を可能にした飛行体を提供する。 【解決手段】本発明による飛行体は、翼部と当該翼部に設けられた回転翼とを備える飛行部と、機体部とを備え、前記翼部は、少なくとも進行方向に対して負の迎角を維持可能となるように構成される。前記翼部は、少なくともホバリング時において前記回転翼の回転中心軸に対して負の迎角を維持可能となるように構成される。飛行体は、前記機体部と独立変位可能な搭乗部を備える。前記機体部は、飛行方向に対して水平かつ垂直に延びている。前記搭乗部は、側面視において、前記機体部の略中央に設けられている。かかる構成により、ホバリング時から水平飛行移行へと安全に移行することができる。

公开(公告)号：WO2021029947A2

公开(公告)日：2021-02-18

申请号：PCT/US2020/036936

申请日：2020-06-10

Applicant: SUPPES, Galen J.

Inventor： SUPPES, Galen J.

IPC: B64C3/38 ,  B64C27/52 ,  B64C9/04 ,  B64D35/04 ,  B64C19/02 ,  B64C13/16 ,  B64D27/24 ,  B64D31/02 ,  B64C29/00 ,  B64C17/04 ,  B64C27/28 ,  B64C29/02 ,  B64C13/28 ,  B64C27/26 ,  B64C39/08 ,  B64C39/12 ,  B64C1/26 ,  B64C11/46 ,  B64C15/02 ,  B64D31/12 ,  B64D33/08

Abstract: A multicopter incorporates a front tiltwing, modular single-circuit motor, hybrid electric-fuel engine, modular injection-molded structures, and operational algorithms to reduce weight, increase efficiency, reduce greenhouse gas footprint, and improve safety. The multicopter has three failsafe modes of emergency landing with an engine have two modes of failsafe operation. The dicopter version of the multicopter has inherent flight stability from either propulsor with passive aerodynamic actuation.

公开(公告)号：WO2020141513A3

公开(公告)日：2020-07-09

申请号：PCT/IL2019/051433

申请日：2019-12-30

Applicant: POLARITY MOBILITY AV LTD.

Inventor： ROSEN, Chen

IPC: B64C29/02

Abstract: A VTOL aircraft comprising a plurality of motor assemblies, each configured to generate thrust by movement of air past the motor assembly along a respective axis of thrust of the motor assembly, and a wing, wherein 1) the orientations of the axes of thrust are each fixed, during operation of the aircraft, at a constant respective pitch angle oblique to a pitch orientation of the wing; 2) the plurality of motor assemblies is operable together to both fully support the aircraft in a hovering mode, and to propel the aircraft forward in a forward flight mode; 3) the wing does not intersect with any right cylinder centered on any motor assembly and having a central longitudinal axis aligned with the axis of thrust of the motor assembly and having a radius equal to a radius of a propeller of the motor assembly.

公开(公告)号：WO2020003240A1

公开(公告)日：2020-01-02

申请号：PCT/IB2019/055517

申请日：2019-06-28

Applicant: LEONARDO S.P.A.

Inventor： BIANCO MENGOTTI, Riccardo

IPC: B64C29/02 ,  B64C39/02 ,  B64C39/06 ,  B64C39/08 ,  B64D27/02 ,  G05D1/08

Abstract: A tail sitter aircraft (1') is described that comprises: a fuselage (2) arranged vertically in a take-off/landing position and transversely to a vertical direction in a cruising position of the aircraft; a single wing (4); at least two first engines (15a, 15b) configured to exert respective first thrusts directed along respective first axes (A) on the tail sitter; and at least two second engines (15c, 15d) rotating about respective second axes (A) arranged above said first axes (A) of the first engines (15a, 15b), with reference to said cruising position; the at least two second engines being configured to exert respective second thrusts directed along respective second axes (A) on the tail sitter (1'); the first and second engines being carried by the single wing; the single wing comprises a first portion (5) and a second portion (6) mutually staggered from one another; the second portion being arranged above said first portion, with reference to said cruising position; said first portion comprises two half-wings, extending from opposite lateral sides of the fuselage; the wing further comprises a third portion (30) arranged below said first portion (5) with reference to said cruising position of said aircraft.

公开(公告)号：WO2019204688A1

公开(公告)日：2019-10-24

申请号：PCT/US2019/028259

申请日：2019-04-19

Applicant: HI-LITE AIRCRAFT

Inventor： HYMER, Jeffrey

IPC: B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C29/00 ,  B64C29/02 ,  B64C29/04

Abstract: A VTOL fixed wing aircraft capable of high-speed forward flight. The aircraft has a main wing internally reinforced with front and aft spars. Spar boxed are located in roll-balanced locations along the wing. Each spar box serves as a connection point for a support linkage that supports a leading-edge and trailing-edge propulsion unit. The leading-edge propulsion unit is fitted with a puller propeller and designed for articulated movement between a VTOL position in front of the wing leading edge and a forward flight position below the wing leading edge. The trailing-edge propulsion unit is fitted with a pusher propeller and designed for articulated movement between a VTOL position in behind the wing trailing edge and a forward flight position above the wing leading edge. The propeller includes a propulsor thrust ring having an aerodynamic profile and a thrust nozzle to capture and vector radial air leakage into thrust.

公开(公告)号：WO2019180304A1

公开(公告)日：2019-09-26

申请号：PCT/FI2019/050134

申请日：2019-02-20

Applicant: LENTOLA LOGISTICS OY

Inventor： HOHENTHAL, Markus

IPC: B64C29/02

Abstract: A structure construction (100) for an aircraft (200) comprises first (101) and second (102) fuselage portions and at least one wing (103). In addition the structure construction (100) comprises a supporting structure (104) for supporting the wing (103) and the first fuselage portion (101). T h e supporting structure (104) or the wing (103) comprises also at least one engine (105). Additionally, the supporting structure (104) is configured to be hinged (106) to the second fuselage portion (102) so that said supporting structure (104) allows turning of said wing (103) and said first fuselage portion (101) in relation to said second fuselage portion (102) to a take-off and landing positions and forward flying position.

公开(公告)号：WO2019116101A1

公开(公告)日：2019-06-20

申请号：PCT/IB2018/001569

申请日：2018-12-11

Applicant: SPENCER, Cameron

Inventor： SPENCER, Cameron

IPC: B64C29/02 ,  B64C11/00 ,  B64C27/20 ,  B64C27/52

Abstract: A variable-geometry vertical takeoff and landing (VTOL) aircraft system may transport passengers from a departure point to a destination via partially or fully autonomous flight operations. The VTOL aircraft system may operate in hover-based ascent/descent modes, level-flight cruising modes, and transitional modes between the two. Thrust may be provided by ducted propeller units articulable relative to the fuselage; by articulating the airfoil struts connecting the thrust sources to the fuselage the thrust sources may be manipulated for ascent/descent, transition, and cruising, in order to control ascent, descent, and cruise. More precise thrust control may be achieved by further articulation of the annular propeller ducts relative to the airfoil struts. The airfoil struts and propeller ducts may present a wing-shaped or variably segmented cross section to maximize achievable lift.

公开(公告)号：WO2019108091A1

公开(公告)日：2019-06-06

申请号：PCT/RU2018/000715

申请日：2018-10-31

Applicant: РУКАВИЦЫН, Дмитрий Валентинович

Inventor： РУКАВИЦЫН, Дмитрий Валентинович

IPC: B64C27/08 ,  B64C27/28 ,  B64C29/02

CPC classification number: B64C27/08 ,  B64C27/28

Abstract: Изобретение относится к области авиации, в частности к конструкциям и способам полета пилотируемых летательных аппаратов (ЛА). Индивидуальный ЛА содержит Х-образный корпус, два раздвижных крыла, снабженных закрылками и закрепленных на передних концах корпуса с возможностью поворота по оси, перпендикулярной плоскости корпуса, или четыре раскладных крыла, закрепленных на передних и задних концах корпуса. Четыре крыла выполнены с возможностью раскладываться в плоскость корпуса из положения, перпендикулярного плоскости корпуса. ЛА содержит вертикальный стабилизатор, ручные и ножные элементы управления, расположенные в передней и задней частях корпуса соответственно. Четыре силовых агрегата выполнены с возможностью поворота и попарно закреплены на концах корпуса. Каждый силовой агрегат представляет собой двигатель с воздушными винтами в защитном кожухе. Корпус выполнен с возможностью размещения на нем пилота в положении, в котором фронтальная плоскость пилота параллельна плоскости корпуса. Обеспечивается повышение аэродинамических характеристик благодаря уменьшению лобового сопротивления.

公开(公告)号：WO2019056172A1

公开(公告)日：2019-03-28

申请号：PCT/CN2017/102249

申请日：2017-09-19

Applicant: 深圳市大疆创新科技有限公司

Inventor： 陈锦熙 ,  王坤殿

IPC: G05D1/10 ,  B64C29/02

CPC classification number: G05D1/101

Abstract: 无人机的飞行控制方法、无人机及机器可读存储介质，该方法包括：基于用户的一键启动控制垂直起降固定翼无人机以多旋翼模式起飞，并在该垂直起降固定翼无人机飞行至指定高度后，自动控制该垂直起降固定翼无人机将飞行模式从多旋翼模式切换为固定翼模式，并以固定翼模式飞行；以及，当符合设定降落条件时，该垂直起降固定翼无人机自动将飞行模式从固定翼模式切换回多旋翼模式，并以多旋翼模式降落至指定位置。可以实现在一次操作控制垂直起降固定翼无人机起飞后，由垂直起降固定翼无人机自主完成飞行任务，并自主返航至指定位置，从而使得整个飞行过程一气呵成，提升了用户体验，同时，还可以减少手动操作对无人机续航时间的占用。