公开(公告)号：US11591109B2

公开(公告)日：2023-02-28

申请号：US16540127

申请日：2019-08-14

Applicant: TOYOTA JIDOSHA KABUSHIKI KAISHA ,  SkyDrive Inc.

Inventor： Kenichi Yamamoto ,  Toshio Ando

IPC: B64D45/00 ,  B64C27/20 ,  B64C27/80

Abstract: Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

公开(公告)号：US11591071B2

公开(公告)日：2023-02-28

申请号：US17195744

申请日：2021-03-09

Applicant: ETH Zurich

Inventor： Mark W. Mueller ,  Sergei Lupashin ,  Raffaello D'Andrea ,  Markus Waibel

IPC: G05D1/00 ,  G05D1/08 ,  G05D3/00 ,  G06F7/00 ,  B64C13/24 ,  B64C27/20 ,  B64C39/02 ,  B64C27/08 ,  B64D45/00 ,  B64C27/32

Abstract: According to a first aspect of the invention, there is provided a method for operating a multicopter experiencing a failure during flight, the multicopter comprising a body, and at least four effectors attached to the body, each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure. The method may comprise the step of identifying a failure wherein the failure affects the torque and/or thrust force produced by an effector, and in response to identifying a failure carrying out the following steps, (1) computing an estimate of the orientation of a primary axis of said body with respect to a predefined reference frame, wherein said primary axis is an axis about which said multicopter rotates when flying, (2) computing an estimate of the angular velocity of said multicopter, (3) controlling one or more of said at least four effectors based on said estimate of the orientation of the primary axis of said body with respect to said predefined reference frame and said estimate of the angular velocity of the multicopter. The step of controlling one or more of said at least four effectors may be performed such that (a) said one or more effectors collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein (i) the torque along said primary axis causes said multicopter to rotate about said primary axis, and (ii) the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and (b) such that said one or more effectors individually produce a thrust force along said primary axis.

公开(公告)号：US11554862B2

公开(公告)日：2023-01-17

申请号：US16655541

申请日：2019-10-17

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Uwe Kiesewetter ,  Christian Reichensperger ,  Lukasz Paluszek ,  Klaus Kicker

IPC: B64C27/28 ,  B64C27/20 ,  B64C29/00

Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

公开(公告)号：US11541997B2

公开(公告)日：2023-01-03

申请号：US16744897

申请日：2020-01-16

Applicant: Maglev Aero Inc.

Inventor： Ian Morris Randall

IPC: B64C27/20 ,  H02K1/2786 ,  H02N15/00 ,  F01D5/02 ,  B64C27/10 ,  B64C27/72 ,  B64D27/24 ,  H02K1/17 ,  H02K1/2793 ,  B64C29/00 ,  B64C13/50 ,  H02K21/22 ,  B64C27/32 ,  H02K1/18 ,  H02K11/21 ,  B64C27/473 ,  H02K21/24 ,  B64C13/26 ,  B64D35/02 ,  B64D35/04 ,  H02K1/28 ,  H02K16/00 ,  B64C27/68 ,  B64C27/00 ,  B64C29/02 ,  B64C27/14 ,  B64C27/80 ,  B64C39/02 ,  B64D35/06

Abstract: Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

公开(公告)号：US11530038B2

公开(公告)日：2022-12-20

申请号：US16646520

申请日：2019-08-20

Applicant: Hangzhou Zero Zero Technology Co., Ltd.

Inventor： Zhaozhe Wang ,  Tong Zhang

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

Abstract: An assembly for an aerial system includes a wing support foldably connected to a first and second side of a body of the aerial system, a protection structure coupled to the wing support and disposed over propellers coupled to the wing support, wherein at least one of the protection structure and the wing support includes at least one of a positioning hook and a positioning groove, wherein the protection structure and wing support are fixed relative to each other with the at least one of the positioning hook and the positioning groove.

公开(公告)号：US20220380035A1

公开(公告)日：2022-12-01

申请号：US17488160

申请日：2021-09-28

Applicant: HOVERSURF, INC.

Inventor： Aleksandr V. Atamanov

IPC: B64C29/00 ,  B64D27/24 ,  B64C27/20 ,  B64C11/00 ,  B64C1/06

Abstract: Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting in-ring propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting in-ring propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

公开(公告)号：US20220380032A1

公开(公告)日：2022-12-01

申请号：US17767055

申请日：2019-10-08

Applicant: A.L.I. Technologies Inc.

Inventor： Yasuhiro ARAKAWA ,  Yutaka TAKAGI ,  Takafumi OBA ,  Takeru SHIROTA ,  Yuki TAKIZAWA ,  Hiroshi NAKANO

IPC: B64C27/20 ,  B64C13/04 ,  B64C27/08

Abstract: To provide an aerial vehicle that can realize ease of operation during driving. An aerial vehicle according to the present technology includes: a vehicle body extending in a front-rear direction; a saddle section provided on an upper side of the vehicle body; a grip section provided on the front side of the saddle section in the vehicle body; and a rotary wing section which is provided in the vehicle body and which generates lift and/or thrust with respect to the vehicle body; wherein an operation section for performing operations pertaining to actions relating to ascent and/or propulsion of the vehicle body is provided in the grip section.

公开(公告)号：US11505313B2

公开(公告)日：2022-11-22

申请号：US16666610

申请日：2019-10-29

Applicant: Bell Textron Inc.

Inventor： Guy Bernard ,  Randy Aloysius

IPC: B64C27/52 ,  F16H25/20 ,  B64C29/00 ,  B64C27/20

Abstract: A method of displacing rotors of an aircraft between a hover mode and an aircraft mode includes rotating a spindle drivingly connected to the rotors about a spindle axis to displace the rotors between the hover and aircraft modes until a component displaceable with the spindle abuts against a downstop of the aircraft and applies a load against the downstop. The method includes passively maintaining the component against the downstop to maintain the load applied against the downstop. An aircraft is also disclosed.

公开(公告)号：US11485486B2

公开(公告)日：2022-11-01

申请号：US15596170

申请日：2017-05-16

Applicant: The University of Toledo

Inventor： Chunhua Sheng ,  Qiuying Zhao

IPC: B64C27/32 ,  B64C27/20 ,  F15D1/00 ,  B64C11/00 ,  B64C29/00 ,  B64C21/02 ,  B64C21/08

Abstract: Systems, methods, lift fans, and aircraft involving active flow control of a ducted fan or fan-in-wing configuration are described.

公开(公告)号：US20220340271A1

公开(公告)日：2022-10-27

申请号：US17239061

申请日：2021-04-23

Applicant: ROHR, INC.

Inventor： JOSE S. ALONSO-MIRALLES

IPC: B64C27/20 ,  B64C27/46 ,  G10K11/32 ,  G10K11/28

Abstract: An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise a first shield configured to be disposed around a rotor of the UAM vehicle, the first shield having an annular shape, the first shield configured to be disposed radially outward from a blade tip of a rotary blade, the first shield configured to redirect sound waves from a substantially radial direction to a second direction, the second direction being orthogonal to the radial direction.