公开(公告)号：US12208888B2

公开(公告)日：2025-01-28

申请号：US18269179

申请日：2021-05-25

Applicant: TUSAS—TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI

Inventor： Burhan Sahin

IPC: B64C27/50 ,  B64C11/00 ,  B64C11/28 ,  B64C27/00

Abstract: A rotary wing aircraft has a body (2), a rotor (3) positioned so as to extend outward from within the body (2) and to rotate about its axis, at least one blade (4) extending outward from the rotor (2) and providing lift and/or thrust force to the body (2) by its movement, at least one outer blade (401) positioned in the blade (4) and providing lift and/or thrust force to the body (2), and at least one mechanism (5) enabling the outer blade (401) to switch from a retracted first position in which the it is almost entirely located in the blade (4) to a second position in which it extends outward from the blade (4) by moving linearly under the influence of the centrifugal force generated during the movement of the rotor (2).

公开(公告)号：US12195167B2

公开(公告)日：2025-01-14

申请号：US18451619

申请日：2023-08-17

Applicant: University of Kansas

Inventor： Ronald Martin Barrett ,  Lauren Nicole Schumacher ,  Patrick Ian McNamee ,  John Austin Haug ,  Joshua Donald Mudd ,  Dalton Bastiaan Prins ,  Nicholas Donald Werner

IPC: B64C11/00 ,  B64C33/00 ,  F01D25/04 ,  B64C27/20

Abstract: A general mounting method for ducted fan propulsors is disclosed. This mounting method uses extremely slender stators that connect the duct ring to the propulsor which is mounted in the middle and drives the rotor, fan or propeller. The slender stators take the form of spokes and as such are so slender that the midspan stresses within the spokes are dominated by axial tension loads rather than the shear loads experienced by conventional stators. The spokes may have an aerodynamic shape and damping methods may be used to retard spoke vibrations and transmission of engine vibrations to the duct and force. The duct itself is also stiffened by the spoke arrangement, thereby reducing low frequency vibration modes.

公开(公告)号：US12151825B2

公开(公告)日：2024-11-26

申请号：US17632773

申请日：2020-08-03

Applicant: CONSEIL ET TECHNIQUE

Inventor： Guy Valembois

IPC: B64D27/24 ,  B64C1/16 ,  B64C11/00 ,  B64C11/48 ,  B64D41/00

Abstract: An aircraft includes a fuselage, a wing structure and a tail assembly, and also at least one propeller having the general shape of a ring. The propeller includes a rotor formed by an annular element having blades projecting outwardly therefrom, and a likewise annular base coaxial to the annular element and on which the annular element can turn under the action of a driver. The base is coaxial to the fuselage and integrated into the shell constituting the fuselage. The blades of the rotor are arranged outside the shell.

公开(公告)号：US12140970B2

公开(公告)日：2024-11-12

申请号：US17344171

申请日：2021-06-10

Applicant: Lockheed Martin Corporation

Inventor： Navid Dadkhah Tehrani

IPC: G05D1/00 ,  B64C11/00 ,  B64C27/10 ,  B64C27/82 ,  B64D31/02 ,  B64D31/06 ,  G08G5/00

Abstract: Systems and methods for controlling a coaxial rotary-wing aircraft including a co-axial main rotor assembly and a pusher-propeller. One system includes an electronic controller configured to receive a reference velocity of the aircraft and receive a reference flight path angle of the aircraft. The electronic controller is also configured to simultaneously control the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft, by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion.

公开(公告)号：US12132358B2

公开(公告)日：2024-10-29

申请号：US17963271

申请日：2022-10-11

Applicant: Airborne Motorworks Inc.

Inventor： Jesse Antoine Marcel

IPC: H02K11/21 ,  B60F5/02 ,  B64C11/00 ,  B64C11/02 ,  B64C11/14 ,  B64C23/02 ,  B64C27/14 ,  B64C27/20 ,  B64C27/24 ,  B64C29/00 ,  B64C37/00 ,  B64D27/34 ,  B64D35/021 ,  B64D35/04 ,  B64D35/08 ,  H02K1/16 ,  H02K7/14 ,  H02K11/30 ,  H02K11/33 ,  H02K16/02

CPC classification number: H02K11/21 ,  B60F5/02 ,  B64C29/0025 ,  B64C37/00 ,  B64D27/34 ,  H02K1/16 ,  H02K7/14 ,  H02K11/30 ,  H02K11/33 ,  H02K16/02 ,  B64C11/001 ,  B64C11/02 ,  B64C11/14 ,  B64C23/02 ,  B64C27/14 ,  B64C27/20 ,  B64C27/24 ,  B64C29/0016 ,  B64C29/0058 ,  B64C29/0083 ,  B64C2203/00 ,  B64D35/021 ,  B64D35/04 ,  B64D35/08

Abstract: An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor creates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

公开(公告)号：US12103678B2

公开(公告)日：2024-10-01

申请号：US18139187

申请日：2023-04-25

Applicant: AeroVironment, Inc.

Inventor： Carlos Thomas Miralles ,  Robert Nickerson Plumb ,  Tony Shuo Tao ,  Nathan Olson

IPC: B64C3/56 ,  B64C3/44 ,  B64C3/50 ,  B64C5/12 ,  B64C9/02 ,  B64C9/08 ,  B64C9/18 ,  B64C9/36 ,  B64C11/00 ,  B64C13/18 ,  B64C13/34 ,  B64C39/02 ,  B64U30/40 ,  B64U40/10 ,  B64C9/00 ,  B64U10/25 ,  B64U20/50 ,  B64U30/12 ,  B64U30/293 ,  B64U70/00 ,  B64U101/15

CPC classification number: B64C3/56 ,  B64C3/44 ,  B64C3/50 ,  B64C5/12 ,  B64C9/02 ,  B64C9/08 ,  B64C9/18 ,  B64C9/36 ,  B64C11/00 ,  B64C13/18 ,  B64C13/34 ,  B64C39/024 ,  B64U30/40 ,  B64U40/10 ,  B64C2009/005 ,  B64U10/25 ,  B64U20/50 ,  B64U30/12 ,  B64U30/293 ,  B64U70/00 ,  B64U2101/15 ,  B64U2201/00 ,  B64U2201/104 ,  B64U2201/20

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

公开(公告)号：US20240278923A1

公开(公告)日：2024-08-22

申请号：US18310679

申请日：2023-05-02

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Ronald Vaughan ,  James N. Quitmeyer ,  Everett Canepa

IPC: B64D31/08 ,  B64C11/00 ,  B64D27/24 ,  B64D31/14 ,  B64D35/08 ,  B64U30/29 ,  B64U50/23

CPC classification number: B64D31/08 ,  B64C11/002 ,  B64D27/24 ,  B64D31/14 ,  B64D35/08 ,  B64U30/29 ,  B64U50/23 ,  B64U10/16

Abstract: A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

公开(公告)号：US12037110B2

公开(公告)日：2024-07-16

申请号：US17564297

申请日：2021-12-29

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Rupert Pfaller ,  Tobias Ries

IPC: B64C27/82 ,  B64C11/00 ,  B64C23/08 ,  B64C27/06 ,  B64C27/16

CPC classification number: B64C27/82 ,  B64C11/001 ,  B64C23/08 ,  B64C27/06 ,  B64C27/16 ,  B64C2027/8236 ,  B64C2027/8254

Abstract: The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

公开(公告)号：US12021421B2

公开(公告)日：2024-06-25

申请号：US17059558

申请日：2019-05-29

Applicant: Rolls-Royce Deutschland Ltd & Co KG

Inventor： Christian Loesch ,  Markus Sons ,  Jens Weidauer

IPC: H02K21/02 ,  B64C11/00 ,  B64D27/02 ,  B64D27/24

CPC classification number: H02K21/028 ,  B64C11/00 ,  B64D27/02 ,  B64D27/24 ,  B64D27/026 ,  H02K2213/06

Abstract: The electric machine includes a rotor and a stator, wherein the stator has stator coils, each with a coil core. The electric machine additionally includes an error-recovery device configured to change a magnetic flux coupling of coil cores with one another by a flux conducting element. The hybrid electric aircraft is a hybrid electric airplane, in particular, and the hybrid electric aircraft has such an electric machine.

公开(公告)号：US12017751B2

公开(公告)日：2024-06-25

申请号：US17475744

申请日：2021-09-15

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  David Marion Ostdiek ,  Darek Tomasz Zatorski

IPC: B64C11/00 ,  B64C11/18 ,  B64C11/48 ,  F01D9/04 ,  F01D17/16 ,  F02C6/20 ,  F02K1/46 ,  F02K3/02 ,  B64D27/00

CPC classification number: B64C11/001 ,  B64C11/18 ,  B64C11/48 ,  F01D9/041 ,  F01D17/16 ,  F02C6/206 ,  F02K1/46 ,  F02K3/025 ,  B64D2027/005 ,  F05B2240/12 ,  F05B2260/96 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2220/36 ,  F05D2250/30 ,  F05D2250/51 ,  F05D2250/52 ,  F05D2260/14

Abstract: A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.