公开(公告)号：US12103675B2

公开(公告)日：2024-10-01

申请号：US17956344

申请日：2022-09-29

申请人： Youngsub Ahn

发明人： Youngsub Ahn

IPC分类号： B64C29/04 ,  B60L50/60 ,  B64C1/00 ,  B64C11/00 ,  B64C39/02 ,  B64D27/24 ,  B64D35/06 ,  B64D35/08 ,  B64U20/60 ,  B64U20/75 ,  B64U30/294 ,  B64U50/14 ,  G05D1/00 ,  B64U30/20 ,  B64U50/19

CPC分类号： B64C29/04 ,  B60L50/66 ,  B64C1/00 ,  B64C11/001 ,  B64C39/024 ,  B64D27/24 ,  B64D35/06 ,  B64D35/08 ,  B64U20/60 ,  B64U20/75 ,  B64U30/294 ,  B64U50/14 ,  G05D1/0016 ,  B60L2200/10 ,  B64C2001/0081 ,  B64U30/20 ,  B64U50/19 ,  B64U2201/20

摘要： A propeller-enclosed airlifting air tube apparatus contains a unique multi air-tube structure that functions as a plurality of air outtakes to produce stable lift force with one or more propellers enclosed in the apparatus. By encapsulating the propellers within the outer shells, the airlifting air tube apparatus is able to reduce potential bodily harm and property damage risks during a flight operation in a densely-populated environment or in another environment involving tight spaces. The airlifting air tube apparatus encapsulates one or more pairs of contra-rotating propellers inside a drone casing to enhance operational safety while minimizing the overall footprint of the apparatus. Furthermore, the airlifting air tube apparatus incorporates a novel airflow control dish-based flight control steering unit configured to change directions and altitudes of the apparatus by dynamically adjusting the airflow to each outtake air tube with the airflow control dish.

公开(公告)号：US12071228B1

公开(公告)日：2024-08-27

申请号：US16814117

申请日：2020-03-10

申请人： Snap Inc.

发明人： Simon Saito Haagen Nielsen

IPC分类号： B64C27/20 ,  B64C11/00 ,  B64C11/18 ,  B64C39/02 ,  B64U30/20

CPC分类号： B64C27/20 ,  B64C11/001 ,  B64C11/18 ,  B64C39/024 ,  B64U30/20

摘要： A flight-capable drone that can optionally comprise: a body; a plurality of propellers each coupled to and having a fixed rotational axis relative to the body, and a plurality of propeller guards. The plurality of propellers operably configured to enable flight along a flight path. During the flight path the plurality of propellers are pitched forward at an angle relative to the flight path. The plurality of propeller guards are fixedly coupled to the body and have a least a part-annular extent. Each one of the plurality of propeller guards positioned radially adjacent a tip of a corresponding one of the plurality of propellers to protect the corresponding propeller from contact. The plurality of propeller guards are configured as an airfoil along at least a portion of the part-annular extent thereof to generate lift during flight along the flight path.

公开(公告)号：US12043367B2

公开(公告)日：2024-07-23

申请号：US17920875

申请日：2021-04-21

申请人： Dr. Ing. h.c. F. Porsche Aktiengesellschaft

发明人： Guan Chew ,  Michael Fürstner ,  Stefan Bender ,  Mikel Fauri ,  Malte Rotermund

IPC分类号： B64C11/00 ,  B64C3/14 ,  B64C29/00

CPC分类号： B64C11/001 ,  B64C3/14 ,  B64C29/0025 ,  B64C2003/143

摘要： An aircraft includes a wing having an integrated ducted fan. The ducted fan is enclosed at least in sections by a feed lip. The feed lip has a flat curvature on the bow side and a comparatively strong curvature on the rear side.

公开(公告)号：US20240178723A1

公开(公告)日：2024-05-30

申请号：US18551833

申请日：2022-03-22

申请人： Lilium eAircraft GmbH

发明人： Sébastien Vermeiren ,  Daniel Wiegand ,  Maurice Shortte

IPC分类号： H02K9/19 ,  B64C11/00 ,  B64D27/31 ,  B64D33/08 ,  H02K1/2706 ,  H02K7/00 ,  H02K7/14

CPC分类号： H02K9/19 ,  B64C11/001 ,  B64D27/31 ,  B64D33/08 ,  H02K1/2706 ,  H02K7/003 ,  H02K7/14

摘要： An electric drive with a fan for an aircraft, wherein the electric drive comprises an electric machine, in particular a permanently excited electric machine, with a stator and a rotor, and the propeller comprises a shaft and rotor blades, wherein the rotor blades are attached to the shaft, the rotor comprises a laminated core and magnets, wherein the laminated core forms an annular arrangement around the shaft, and the rotor blades, the shaft, the laminated core and the magnets are connected in a thermally conductive manner so that the rotor blades form a heat sink for the magnets.

公开(公告)号：US11988099B2

公开(公告)日：2024-05-21

申请号：US16900407

申请日：2020-06-12

申请人： General Electric Company

发明人： Darek Tomasz Zatorski ,  Jeffrey Hamel ,  Andrew Breeze-Stringfellow

IPC分类号： B64C11/00 ,  B64C11/18 ,  B64C11/46 ,  B64C11/48 ,  F01D9/02 ,  F01D17/16 ,  F02C6/20 ,  F02K1/46 ,  F02K3/02 ,  B64D27/00

CPC分类号： F01D17/16 ,  B64C11/001 ,  B64C11/18 ,  B64C11/46 ,  B64C11/48 ,  F01D9/02 ,  F02C6/206 ,  F02K1/46 ,  F02K3/025 ,  B64C11/00 ,  B64D2027/005 ,  F05B2240/12 ,  F05B2260/96 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/30 ,  F05D2250/51 ,  F05D2250/52 ,  F05D2260/14 ,  Y02E10/72 ,  Y02T50/60

摘要： An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.

公开(公告)号：US20240150014A1

公开(公告)日：2024-05-09

申请号：US17969616

申请日：2022-10-19

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64C29/04 ,  B64C9/38 ,  B64C11/00 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/12 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04

CPC分类号： B64C29/04 ,  B64C9/38 ,  B64C11/001 ,  B64C15/00 ,  B64C21/00 ,  B64C29/02 ,  B64C39/024 ,  B64C39/12 ,  B64D27/10 ,  B64D27/20 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0273 ,  B64U10/25 ,  Y02T50/10 ,  Y02T50/40

摘要： A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

公开(公告)号：US11945610B2

公开(公告)日：2024-04-02

申请号：US17596993

申请日：2020-06-23

申请人： INTERACTIVE FULLY ELECTRICAL VEHICLES S.R.L.

发明人： Pietro Perlo ,  Davide Penserini

IPC分类号： B64U10/14 ,  B64C11/00 ,  B64C29/00 ,  B64D27/24 ,  B64U10/13 ,  B64U10/20 ,  B64U30/27 ,  B64U50/19 ,  H02K21/24

CPC分类号： B64U10/14 ,  B64C11/001 ,  B64C29/0025 ,  B64D27/24 ,  B64U10/20 ,  B64U30/27 ,  H02K21/24 ,  B64U10/13 ,  B64U50/19

摘要： A drone or an aircraft for personal air mobility includes at least one horizontal planar structure having four ducted propeller rotors with vertical axis, which are substantially coplanar with each other. Each of the rotors has a rotating ring rotatably mounted within a circular opening. The rotating ring is configured as to define an annular wall for ducting of air flow produced by the rotor. Each of the rotors has one or more blades which extend towards the central axis of the rotor, and have tips terminating at a distance from the axis of the propeller, such that each rotor is an annular propeller. The rotating ring of each rotor is controlled by an actuator.

公开(公告)号：US11897623B2

公开(公告)日：2024-02-13

申请号：US17553014

申请日：2021-12-16

申请人： North University of China

发明人： Tiehua Ma ,  Yanbing Zhang ,  Yaoyan Wu ,  Changxin Chen ,  Bin Jiao

IPC分类号： H02K1/27 ,  B64D27/24 ,  B64C11/00 ,  B64C29/00

CPC分类号： B64D27/24 ,  B64C11/001 ,  B64C29/0016

摘要： A ducted fan device integrated with a permanent magnet synchronous disc flat wire motor for a flying copter car, including a rotor system, a stator system, an air intake/exhaust control system, a detection system, a driving system and a power supply system. The stator system includes a motor shell, and flat wire coils respectively arranged on an upper end face and a lower end face of an inner wall of the motor shell are connected in series. The rotor system is arranged inside the stator system, including axial flow and radial flow composite integrated blades and permanent magnets. A part of centrifugal blades are replaced by the permanent magnets which are located on an outer side.

公开(公告)号：US11820509B2

公开(公告)日：2023-11-21

申请号：US17026530

申请日：2020-09-21

申请人： Hop Flyt, Inc.

发明人： Robert Allen Winston ,  Clark William Fuller

IPC分类号： B64C39/06 ,  B64C29/00 ,  B64C11/00 ,  B64C3/32

CPC分类号： B64C39/066 ,  B64C11/001 ,  B64C29/0033 ,  B64C3/32

摘要： An embodiment of the invention provides a method where retractable ducts or shrouds are extended over propeller(s) that are fixed in wing channels on an aircraft during takeoff and landing to increase flight safety and efficiency. Fully extending the duct or shroud during takeoff increases lift and upward thrust, while retracting the duct or shroud and stowing the duct or shroud inside of the wing during forward cruise decreases aircraft drag and increases lift. Duct or shroud extension during takeoff also enables critical safety and noise cancellation functionality. The method provided for safe and efficient takeoff can be applied in reverse order for safe and efficient landing.

公开(公告)号：US20230331382A1

公开(公告)日：2023-10-19

申请号：US18028753

申请日：2020-09-30

申请人： NIPPON TELEGRAPH AND TELEPHONE CORPORATION

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

IPC分类号： B64C39/02 ,  B64C11/00

CPC分类号： B64C39/024 ,  B64C11/001

摘要： A propeller guard 2 includes a propeller guard body 10 configured to surround a propeller 30 of a flight vehicle 20; and a repulsion mechanism 40 including a first end 45 and a second end 46 and provided to protrude on the propeller guard body 10 through the first end 45, in which the repulsion mechanism 40 includes a mechanism to separate the propeller guard body from an object in response to contact of the second end with the object.