公开(公告)号：US20240208643A1

公开(公告)日：2024-06-27

申请号：US18550257

申请日：2021-03-17

Applicant: AERONEXT INC.

Inventor： Yoichi SUZUKI

IPC: B64C27/24 ,  B64C3/38 ,  B64D9/00

CPC classification number: B64C27/24 ,  B64C3/38 ,  B64D9/00

Abstract: A flight vehicle with a more basic structure and safety measures according to the invention comprises a main body part; a propulsion part provided with one or more propulsion means; a connection part connecting the main body part and the propulsion part in a displaceable manner within a predetermined range; and a wing part provided on at least one of the main body part or the propulsion part. With such a configuration, a flight vehicle with a more basic structure and safety measures can be provided.

公开(公告)号：US11084577B2

公开(公告)日：2021-08-10

申请号：US16062787

申请日：2016-12-16

Applicant: Răzvan Sabie ,  Iosif Ţăposu

Inventor： Răzvan Sabie ,  Iosif Ţăposu

IPC: B64C29/00 ,  B64C27/20 ,  B64C15/02 ,  B64C27/24 ,  B64C27/82 ,  B64C39/00

Abstract: The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetermined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground.

公开(公告)号：US10723449B2

公开(公告)日：2020-07-28

申请号：US16180004

申请日：2018-11-04

Applicant: Dawei Dong

Inventor： Dawei Dong

IPC: B64C27/16 ,  B64C27/02 ,  B64C27/24 ,  B64C25/00

Abstract: A helicopter uses electric propeller torque arm as power source directly driving main rotor to rotate. The helicopter may be battery powered. The helicopter may be without an engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor and a fuel supply system. The main design goal is to have the output shaft of the high-energy motor being coaxial with the main rotor shaft or having output shafts of a plurality of motors as close as possible to the main rotor shaft. The centrifugal force of the motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arm of the plurality of torque arms includes a propeller and a driving system. In the case of a malfunction, the helicopter's main rotor will spin like a maple leaf and will facilitate the spin autorotation landing.

公开(公告)号：US10421538B2

公开(公告)日：2019-09-24

申请号：US15540890

申请日：2015-12-28

Applicant: Joseph B. Seale ,  Walker M. Sloan

Inventor： Joseph B. Seale ,  Walker M. Sloan

IPC: B64C27/24 ,  B64C27/16 ,  B64C27/18 ,  B64C29/00

Abstract: An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

公开(公告)号：US20180093770A1

公开(公告)日：2018-04-05

申请号：US15831003

申请日：2017-12-04

Applicant: Amazon Technologies, Inc.

Inventor： Ricky Dean Welsh ,  Daniel Buchmueller ,  Fabian Thomas Hensel ,  Gur Kimchi ,  Louis LeRoi LeGrand, III ,  Brandon William Porter ,  Walker Chamberlain Robb ,  Joshua White Traube

IPC: B64C39/02 ,  B64C29/00 ,  B64C27/22 ,  B64C27/24

CPC classification number: B64C39/024 ,  B64C27/22 ,  B64C27/24 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pushing motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor may be engaged and the pushing propeller will aid in the horizontal propulsion of the UAV.

公开(公告)号：US20180086445A1

公开(公告)日：2018-03-29

申请号：US15280961

申请日：2016-09-29

Applicant: Ampaire, Inc.

Inventor： Cory Michael Combs

IPC: B64C29/00 ,  B64C27/24 ,  B64C27/18 ,  B64C9/00 ,  B64C3/44

CPC classification number: B64C29/0025 ,  B64C3/44 ,  B64C9/00 ,  B64C9/38 ,  B64C27/18 ,  B64C27/24 ,  B64C30/00

Abstract: An oblique rotor-wing aircraft may be capable of vertical take-off and landing, subsonic cruise, transonic cruise, and/or supersonic cruise. The oblique rotor-wing aircraft may comprise one or more of a fuselage, a rotor-wing, a thrust-vectored propulsion system, a locking mechanism, and/or other components. The rotor-wing may be rotatably coupled to the fuselage. The rotor-wing may rotate about an axis in a first flight mode for vertical takeoff and landing. The oblique rotor-wing aircraft may include a thrust-vectored propulsion system that drives the rotation of the rotor-wing about the axis. The thrust-vectored propulsion system may include multiple, separately operable propulsion systems coupled to the rotor-wing and/or the fuselage. The oblique rotor-wing aircraft may comprise a locking mechanism that locks the rotor-wing at an angle oblique to the fuselage responsive to initiation of a second flight mode. The rotor-wing may be fixed at an angle oblique to the fuselage during the second flight mode.

公开(公告)号：US09896197B2

公开(公告)日：2018-02-20

申请号：US14723720

申请日：2015-05-28

Applicant: Eugene H Vetter ,  James W Vetter ,  Paul A Vetter

Inventor： Eugene H Vetter ,  James W Vetter ,  Paul A Vetter

IPC: B64C27/30 ,  B64C27/10 ,  B64C27/24 ,  B64C27/26

CPC classification number: B64C27/30 ,  B64C27/10 ,  B64C27/24 ,  B64C27/26

Abstract: A hybrid VTOL/high speed aircraft may comprise systems and functions for in flight configuration changes from high lift helicopter or VTOL mode to fixed or swing-wing high speed aircraft mode to accommodate a variety of functions or missions.

公开(公告)号：US09878785B2

公开(公告)日：2018-01-30

申请号：US14258003

申请日：2014-04-21

Applicant: The Boeing Company

Inventor： Steven D. Richardson

IPC: B64C27/82 ,  B64C3/38 ,  B64C15/02 ,  B64C15/14 ,  B64C27/18 ,  B64C27/24 ,  B64C27/26

CPC classification number: B64C27/82 ,  B64C3/385 ,  B64C15/02 ,  B64C15/14 ,  B64C27/18 ,  B64C27/24 ,  B64C27/26 ,  Y02T50/14

Abstract: A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.

公开(公告)号：US09810224B2

公开(公告)日：2017-11-07

申请号：US14342406

申请日：2012-08-17

Applicant: Eric Chantriaux ,  Pascal Chretien

Inventor： Eric Chantriaux ,  Pascal Chretien

IPC: B64C27/14 ,  B64C27/24 ,  F04D13/06 ,  B64D27/24 ,  B64D35/08 ,  B64D35/02

CPC classification number: F04D13/06 ,  B64C27/14 ,  B64C2201/042 ,  B64D27/24 ,  B64D35/02 ,  B64D35/08 ,  B64D2221/00 ,  Y02T50/44 ,  Y02T50/64

Abstract: Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: ·Pr=the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft, ·Pim=the maximum mechanical power capable of being delivered by the electric motor element on level i, to the rotating shaft, for instance Pim

公开(公告)号：US20170197709A1

公开(公告)日：2017-07-13

申请号：US15259219

申请日：2016-09-08

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Axel FINK ,  Martin BLACHA

IPC: B64C27/26 ,  B64C27/24 ,  B64C3/18 ,  B64C27/82 ,  B64C3/16 ,  B64C25/10 ,  B64C1/26 ,  B64C27/06 ,  B64C25/34

CPC classification number: B64C27/26 ,  B64C1/26 ,  B64C3/16 ,  B64C3/185 ,  B64C25/10 ,  B64C25/34 ,  B64C27/06 ,  B64C27/24 ,  B64C27/82 ,  B64C39/068 ,  B64C2027/8236 ,  B64C2027/8263

Abstract: A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.