公开(公告)号：US12065239B2

公开(公告)日：2024-08-20

申请号：US17940073

申请日：2022-09-08

申请人： Airbus SAS ,  Airbus Operations SAS

发明人： Andrew Booth ,  Julien Laverne ,  Alistair Forbes

IPC分类号： B64C3/10 ,  B64D37/04

CPC分类号： B64C3/10 ,  B64D37/04

摘要： An aircraft comprising a fuselage, first and second wings positioned on either side of the fuselage, wherein each wing includes an inner part connected to the fuselage and an outer part continuing the inner part, the end of each inner part connected to the fuselage having a height greater than half the height of the fuselage and extending over a length greater than or equal to half of a distance separating the nose and the tail of the fuselage.

公开(公告)号：US11987352B2

公开(公告)日：2024-05-21

申请号：US17974741

申请日：2022-10-27

申请人： COFLOW JET, LLC

发明人： Gecheng Zha

IPC分类号： B64C3/10 ,  B64C3/14 ,  B64C3/36 ,  B64C21/02 ,  F15D1/00 ,  B64C29/00

CPC分类号： B64C3/10 ,  B64C3/141 ,  B64C3/36 ,  B64C21/025 ,  F15D1/0055 ,  B64C2003/143 ,  B64C29/0075 ,  B64C2230/04 ,  B64C2230/06

摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

公开(公告)号：US11603182B1

公开(公告)日：2023-03-14

申请号：US17881677

申请日：2022-08-05

申请人： The United States of America as represented by the Secretary of the Navy

发明人： Richard E Dooley

IPC分类号： B64C3/48 ,  B64C3/18 ,  B64C13/30 ,  B64F5/10 ,  B64C3/10

摘要： A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.

公开(公告)号：US11535375B2

公开(公告)日：2022-12-27

申请号：US16628731

申请日：2018-07-06

申请人： ISTANBUL TEKNIK UNIVERSITESI ,  MITOS MIKRODALGA GORUNTULEME SISTEMLERI MUHENDISLIK SANAYI VE TICARET LIMITED SIRKETI

发明人： Guray Ali Canli ,  Ibrahim Akduman ,  Ismail Kurtoglu ,  Mehmet Cayoren ,  Pelin Yavuz Gundogdu ,  Ibrahim Ozkol ,  Hasan Ercan ,  Muhammet Tarik Tamyurek

IPC分类号： B64C29/02 ,  B64D27/02 ,  B64C39/02 ,  B64B1/40 ,  B64B1/58 ,  B64C3/38 ,  B64C5/00 ,  B64C19/00 ,  B64C39/08 ,  B64D27/04 ,  B64D27/24 ,  B64D35/04 ,  B64C3/10 ,  B64C3/16 ,  B64C17/06

摘要： An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.

公开(公告)号：US11511851B2

公开(公告)日：2022-11-29

申请号：US16356738

申请日：2019-03-18

申请人： Aviation Partners, Inc.

发明人： Louis B. Gratzer

IPC分类号： B64C23/06 ,  B64C11/18 ,  B64C3/10 ,  B64C27/46

摘要： A method for improving performance in an aircraft having a winglet coupled to a wing, the winglet having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The method includes coupling a wing tip to the winglet. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle.

公开(公告)号：US20220144420A1

公开(公告)日：2022-05-12

申请号：US17454927

申请日：2021-11-15

申请人： Joby Aero,Inc.

发明人： Mark Moore ,  John Conway Badalamenti ,  Ian Villa ,  Adam Warmoth ,  David Josephson

IPC分类号： B64C29/00 ,  B64C9/02 ,  G05D1/08 ,  B64C11/48 ,  B64C3/10 ,  B64D27/24 ,  B64D35/06

摘要： A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.

公开(公告)号：US11312481B2

公开(公告)日：2022-04-26

申请号：US16630239

申请日：2017-07-12

申请人： The Aircraft Performance Company GmbH

发明人： Hans-Jorg Petscher ,  Volker Kassera

IPC分类号： B64C23/06 ,  B64C3/10 ,  B64C3/56

摘要： A wing for an airplane has an outer wing end and an inner side of the wing for mounting to the airplane. The outer wing has at least two winglets connected to the wing, including an upstream winglet preceding a downstream winglet in a flight direction of the wing. The first winglet and the second winglet are mutually inclined, as seen against the flight direction, by a relative dihedral angle.

公开(公告)号：US20220111957A1

公开(公告)日：2022-04-14

申请号：US17475280

申请日：2021-09-14

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64C29/04 ,  B64C3/10 ,  B64C39/12 ,  B64C39/06 ,  B64D33/04 ,  B64C5/06 ,  B64C15/12

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 tad conduit is fluidly coupled to the generator. First and second fore ejectors are 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 includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

公开(公告)号：US11279479B2

公开(公告)日：2022-03-22

申请号：US16833638

申请日：2020-03-29

申请人： Textron Innovations Inc.

发明人： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Matthew Edward Louis

IPC分类号： B64C29/00 ,  B64D27/16 ,  B64C11/48 ,  B64D35/06 ,  B64C11/00 ,  B64D35/02 ,  B64C27/22 ,  B64D33/04 ,  B64D35/04 ,  B64C3/10 ,  B64C19/00 ,  B64C27/26 ,  B64C27/30 ,  B64C9/20 ,  B64C21/08 ,  B64C27/78 ,  B64C21/04 ,  B64C39/10 ,  B64C9/18 ,  B64C15/02 ,  B64C15/14 ,  B64C21/00

摘要： An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.

公开(公告)号：US11124306B2

公开(公告)日：2021-09-21

申请号：US16042328

申请日：2018-07-23

申请人： General Electric Company

发明人： Kurt David Murrow ,  Darek Tomasz Zatorski

IPC分类号： B64D27/24 ,  B64D29/04 ,  B64C3/10 ,  B64D27/08 ,  B64C29/00 ,  B64C3/32 ,  B64D35/02 ,  B64C3/38 ,  B64D33/04 ,  B64D31/06 ,  B64D27/02 ,  B64D27/26 ,  H02K7/18

摘要： An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.