公开(公告)号：US12214873B2

公开(公告)日：2025-02-04

申请号：US18442225

申请日：2024-02-15

Applicant: FLYON Aerosystems Ltd.

Inventor： Oren Tal ,  Reuven Tal

IPC: B64C27/50 ,  B60P3/11 ,  B64C1/14 ,  B64C27/20 ,  B64C29/00 ,  B64D11/00 ,  B64F1/22 ,  B64F1/31

Abstract: An aerial vehicle has a passenger cabin for receiving at least one passenger, a load-bearing structure beneath the cabin, and a propulsion system including a number of propulsion units, which propel the aerial vehicle for powered flight and vertical take-off and landing (VTOL). The propulsion units are preferably carried by support arms attached to the load-bearing structure and extending upwards therefrom so as to support the propulsion units at a level above the cabin. The aerial vehicle is preferably reconfigurable to a compact configuration after landing, with at least some of the propulsion units overlapping the cabin and/or each other, while still allowing passenger transfer in and out of the vehicle, thereby facilitating efficient use of space for implementing a vertiport.

公开(公告)号：US12110103B2

公开(公告)日：2024-10-08

申请号：US17515549

申请日：2021-11-01

Applicant: Xi Wang

Inventor： Xi Wang

IPC: B64C27/10 ,  B64C9/00 ,  B64C11/46 ,  B64C27/20 ,  B64C27/58 ,  B64D27/24 ,  B64D31/00

CPC classification number: B64C27/10 ,  B64C9/00 ,  B64C11/46 ,  B64C27/20 ,  B64C27/58 ,  B64D27/24 ,  B64D31/00

Abstract: The invention is for a VTOL (vertical take-off and landing) rotorcraft with the annular contra-rotating rotary wings and auxiliary propulsor. The rotary wing of the annular contra-rotating rotary wings is driven by a plurality of tangential forces applied at multiple locations of the inner stator hub. The annular contra-rotating rotary wings can be shrouded for the improvement of propulsive efficiency, reduction of noise and protection of the rotary wing. The fuselage is mounted along the center axis of the annular contra-rotating rotary wings to be outside of the thrust slipstream. The auxiliary propulsor includes a quad independent pusher propeller to propel the rotorcraft to reach faster forward speed.

公开(公告)号：US12049317B2

公开(公告)日：2024-07-30

申请号：US16238723

申请日：2019-01-03

Applicant: Wilcox Industries Corp.

Inventor： James W. Teetzel ,  Douglas M. Delorge

IPC: B64D1/16 ,  B64C27/20 ,  B64C39/02 ,  B64D45/00 ,  B64D47/06 ,  B64D47/08 ,  G01S19/42 ,  B64U101/00

CPC classification number: B64D1/16 ,  B64C27/20 ,  B64C39/024 ,  B64D45/00 ,  B64D47/06 ,  B64D47/08 ,  G01S19/42 ,  B64U2101/00

Abstract: In one aspect, an unmanned aerial system for crowd control, includes a chassis for attaching components of the unmanned aerial system and one or more rotary wings, each of the one or more rotary wings drivable by a respective motor. A container stores a pressurized source of a crowd control agent and a nozzle is provided for dispersing the crowd control agent into the air. An electronically controlled valve selectively places the nozzle into fluid communication with the container. In a further aspect, a modular unmanned aerial system for crowd control is provided.

公开(公告)号：US20240075779A1

公开(公告)日：2024-03-07

申请号：US17767383

申请日：2020-11-25

Applicant: AMAZING SUN CO., LTD.

Inventor： KYUNG HEE HAN

IPC: B60F5/02 ,  B64C25/36 ,  B64C25/62 ,  B64C27/20 ,  B64C37/00 ,  B64D17/80 ,  B64D27/24

CPC classification number: B60F5/02 ,  B64C25/36 ,  B64C25/62 ,  B64C27/20 ,  B64C37/00 ,  B64D17/80 ,  B64D27/24

Abstract: The present invention relates to a self-powered drone flying car for land and air, in which a circular riding spherical body (110) that is a commercial space in which a person rides to fly, steer, and control the flying car is formed, a drone wing device (230) that is a flying device is mounted onto the riding spherical body, and a ground driving device for driving on the ground is mounted to a lower portion of the riding spherical body, in order to perform both flying in the air and driving on the ground. Also, an intermediate connection attaching and detaching device (210) is formed between the devices to separate and connect the devices depending on whether the flying device or the ground driving device is necessary.

公开(公告)号：US20240045446A1

公开(公告)日：2024-02-08

申请号：US18376358

申请日：2023-10-03

Applicant: Kitty Hawk Corporation

Inventor： Sebastian Thrun ,  Benjamin Otto Berry

IPC: G05D1/04 ,  B64C27/52 ,  B64C29/00 ,  B64D1/00 ,  B64C27/20 ,  B64C27/08 ,  B64C27/48 ,  B64C27/32

CPC classification number: G05D1/046 ,  B64C27/52 ,  B64C29/0033 ,  B64D1/00 ,  B64C27/20 ,  B64C27/08 ,  B64C27/48 ,  B64C27/32 ,  B64F1/0295

Abstract: During a vertical landing state, it is decided whether to switch from the vertical landing state to a self adjusting state. The VTOL vehicle includes the flight controller, the rotor, and a fuselage where the rotor is coupled to the fuselage via a vertical connector. If it is so decided, there is a switch from the vertical landing state to the self adjusting state. During the self adjusting state, a control signal for a rotor is generated where the control signal causes: (1) the rotor to rotate during the self adjusting state and (2) the VTOL vehicle to remain in a fixed position during the self adjusting state, in response to the control signal, and independent of docking infrastructure. During a rotors off state, a rotor off control signal is generated for the rotor that causes the rotor to turn off.

公开(公告)号：US11851174B2

公开(公告)日：2023-12-26

申请号：US16819671

申请日：2020-03-16

Applicant: FlightWave Aerospace Systems

Inventor： Trent Lukaczyk ,  Michael Colonno

IPC: B64C27/52 ,  B64D27/24 ,  B64C27/20 ,  B64C7/00 ,  B64D31/14 ,  B64C39/02

CPC classification number: B64C27/52 ,  B64C7/00 ,  B64C27/20 ,  B64D27/24 ,  B64D31/14 ,  B64C39/024

Abstract: A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure.

公开(公告)号：US11834162B2

公开(公告)日：2023-12-05

申请号：US17239001

申请日：2021-04-23

Applicant: ROHR, INC.

Inventor： Jose S. Alonso-Miralles

IPC: B64C27/20 ,  B64C1/40 ,  B64C29/00 ,  B64C11/00

CPC classification number: B64C27/20 ,  B64C1/40 ,  B64C11/001 ,  B64C29/0016

Abstract: An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise: a first shroud configured to be disposed around a rotor of the UAM vehicle, the first shroud comprising: a radially inner wall configured to be spaced radially outward from a blade tip of a rotary blade of the rotor, the radially inner wall including a perforated portion; and a hollow chamber defined by an internal surface of the first shroud and the radially inner wall.

公开(公告)号：US11827344B2

公开(公告)日：2023-11-28

申请号：US17116726

申请日：2020-12-09

Applicant: Bell Textron Inc.

Inventor： Alexander Dang Quang Truong ,  Karl Schroeder ,  Michael John Ryan

IPC: B64C27/20 ,  B64C39/02 ,  B64D33/02 ,  B64U10/13 ,  B64U30/20 ,  B64U50/14

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64D2033/0206 ,  B64U10/13 ,  B64U30/20 ,  B64U50/14

Abstract: An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.

公开(公告)号：US20230373616A1

公开(公告)日：2023-11-23

申请号：US18029083

申请日：2020-09-30

Applicant: NIPPON TELEGRAPH AND TELEPHONE CORPORATION

Inventor： Daisuke UCHIBORI ,  Yujin HAMANO ,  Kazuaki WATANABE ,  Masafumi NAKAGAWA ,  Atsushi ARATAKE

IPC: B64C27/20 ,  B64C27/08 ,  B64C27/00

CPC classification number: B64C27/20 ,  B64C27/08 ,  B64C27/006

Abstract: A propeller guard 2 includes: a propeller guard body 10 configured to surround a propeller 30 of a flight vehicle 20; and a rod-shaped body 40 provided on an upper portion of the propeller guard body 10 and including a first end 44 and a second end 41, in which the first end 44 of the rod-shaped body 40 is provided near a peripheral portion of an upper surface of the propeller guard body 10, and the rod-shaped body 40 extends while passing above the upper surface of the propeller guard body 10 as viewed from vertically above.

公开(公告)号：US20230356834A1

公开(公告)日：2023-11-09

申请号：US17922998

申请日：2021-04-29

Applicant: BAE Systems plc

Inventor： David Charles Atkinson

IPC: B64C27/20 ,  B64C27/52 ,  B64C39/02

CPC classification number: B64C27/20 ,  B64C27/52 ,  B64C39/026

Abstract: There is disclosed a rotorcraft comprising: an array of lift devices; a pilot housing; connecting lines attaching the pilot housing to the array of lift devices; and an actuator interface at the pilot housing such that the pilot can 5 steer the rotorcraft.