公开(公告)号：US20240076031A1

公开(公告)日：2024-03-07

申请号：US18457837

申请日：2023-08-29

申请人： HONDA MOTOR CO., LTD.

发明人： Yuji Ishitsuka

IPC分类号： B64C11/02 ,  B64C29/00

CPC分类号： B64C11/02 ,  B64C29/0025

摘要： A rotor support device includes: a mount supporting a rotor and including a joint portion protruding outward; a connecting member; and a reinforcing member. The connecting member includes an end portion connected to the joint portion and including a notch and a protruding portion formed by forming the notch. The protruding portion is overlapped with a part of the outer peripheral surface of the joint portion located on the side of a first direction perpendicular to the protruding direction of the joint portion, and is detachably connected to the joint portion. The reinforcing member is overlapped with the connecting member and another part of the outer peripheral surface of the joint portion located on the side of a second direction opposite to the first direction, and is detachably connected to the joint portion and the connecting member.

公开(公告)号：US11921521B2

公开(公告)日：2024-03-05

申请号：US17182438

申请日：2021-02-23

申请人： Volocopter GmbH

发明人： Burak Yüksel ,  Sebastian Mores

IPC分类号： G05D1/00 ,  B64C13/16 ,  B64C29/00 ,  G08G5/00

CPC分类号： G05D1/0858 ,  B64C13/16 ,  B64C29/005 ,  G08G5/0052

摘要： A method of controlling an aircraft having multiple configurations is provided, wherein each configuration is controlled by a different control law implemented by a flight control device and transition from one configuration to another configuration is achieved by gradually blending out a control law for one configuration and by gradually increasing an impact of a control law for another configuration in the flight control device based on an estimated flight condition of the aircraft by dynamically adjusting, in the flight control device, respective maximum and minimum limit values of control volumes, which control volumes are defined by parameter ranges of control parameters in connection with a corresponding control law for the one configuration and for the other configuration, respectively.

公开(公告)号：US11919632B2

公开(公告)日：2024-03-05

申请号：US17702558

申请日：2022-03-23

申请人： HYUNDAI MOTOR COMPANY ,  KIA CORPORATION

发明人： Youn Sic Nam ,  Myeong Man Park ,  Kwan Ho Moh ,  Keon Woo Kim

IPC分类号： B64C29/00 ,  B64C39/06

CPC分类号： B64C29/0033 ,  B64C39/066

摘要： An air mobility device improves propulsion due to the Coandă effect when flying so as to increase a flying range and reduces noise when flying.

公开(公告)号：US11913470B2

公开(公告)日：2024-02-27

申请号：US16754064

申请日：2018-08-29

申请人： JAPAN AEROSPACE EXPLORATION AGENCY

发明人： Masashi Harada

IPC分类号： F04D29/40 ,  F04D19/00 ,  F04D29/38 ,  B64C11/18 ,  B64C29/00

CPC分类号： F04D29/403 ,  B64C11/18 ,  B64C29/00 ,  F04D19/002 ,  F04D29/384

摘要： [Object] To maximize static thrust of a ducted fan. [Solving Means] This ducted fan 1 includes a duct 10, a fan 20, a motor 30, a housing 40, and stators 50. The fan 20 includes a hub 21 disposed concentric with the duct 10 and four blades 22 arranged at equal intervals on the outer circumference of the hub 21. A chord length CL of the blade 22 gradually decreases toward a tip 22A from the root. In contrast, the chord length CL of the blade 22 increases to the tip 21B from a tip vicinity portion 22B.

公开(公告)号：US11912430B2

公开(公告)日：2024-02-27

申请号：US17732354

申请日：2022-04-28

申请人： BETA AIR, LLC

发明人： Nicholas Moy ,  Collin Freiheit ,  Joshua E. Auerbach

IPC分类号： B64D43/00 ,  G08G5/00 ,  B64C29/00 ,  B64D27/24

CPC分类号： B64D43/00 ,  B64C29/00 ,  G08G5/0039 ,  B64D27/24

摘要： In an aspect of the present disclosure a pilot display system for an aircraft includes a sensor configured to measure an aircraft position and generate a position datum based on the aircraft position, a display incorporated in the aircraft, and a computing device communicatively connected to the sensor and the display, the computing device configured to receive a flight path including a transition point, determine, from the position datum, the aircraft position relative to the transition point, and command the display to display a visual representation of the aircraft position relative to the transition point.

公开(公告)号：US20240062660A1

公开(公告)日：2024-02-22

申请号：US18324610

申请日：2023-05-26

申请人： Joby Aero, Inc.

发明人： Ian Villa

IPC分类号： G08G5/00 ,  G06Q10/047 ,  B64C29/00 ,  G06Q10/0631 ,  G01C21/20 ,  G01C21/34 ,  G05D1/02

CPC分类号： G08G5/003 ,  G08G5/0013 ,  G06Q10/047 ,  B64C29/00 ,  G06Q10/06315 ,  G01C21/20 ,  G08G5/0034 ,  G08G5/0043 ,  B64C29/0016 ,  G01C21/3461 ,  G05D1/0202 ,  G08G5/0039 ,  B64C29/0025 ,  B64C29/0033 ,  B64C2220/00 ,  G05D1/102

摘要： Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft may be noisy. To accommodate this, the aircraft may utilize onboard sensors, offboard sensing, network, and predictive temporal data for noise signature mitigation. By building a composite understanding of real data offboard the aircraft, the aircraft can make adjustments to the way it is flying and verify this against a predicted noise signature (via computational methods) to reduce environmental impact. This might be realized via a change in translative speed, propeller speed, or choices in propulsor usage (e.g., a quiet propulsor vs. a high thrust, noisier propulsor). These noise mitigation actions may also be decided at the network level rather than the vehicle level to balance concerns across a city and relieve computing constraints on the aircraft.

公开(公告)号：US20240059409A1

公开(公告)日：2024-02-22

申请号：US17820302

申请日：2022-08-17

申请人： HONEYWELL INTERNATIONAL INC.

发明人： Pedro Alexandre Tonet Fleig ,  Ondrej Karas

IPC分类号： B64C29/00 ,  B64C27/26 ,  G05D1/10

CPC分类号： B64C29/0008 ,  B64C27/26 ,  G05D1/102 ,  B64C39/024

摘要： Aircraft and methods of operating the aircraft to provide for increased descent angles. The aircraft includes a fuselage having fixed wings, a horizontal thrust source coupled to the fuselage and configured to selectively generate and supply horizontal thrust to the aircraft, a vertical thrust source coupled to the fuselage and configured to selectively generate and supply vertical thrust to the aircraft, the vertical thrust source including a vertical thrust rotor that is configured to selectively operate in a locked mode, in which the vertical thrust rotor cannot rotate freely in response to contact of airflow therewith, and an unlocked mode, in which the vertical thrust rotor can rotate freely in response to contact of airflow therewith, and a controller configured to selectively supply a command to the vertical thrust source that causes the vertical thrust rotor to operate in the unlocked mode.

公开(公告)号：US11905009B2

公开(公告)日：2024-02-20

申请号：US17826163

申请日：2022-05-27

申请人： Joby Aero, Inc.

发明人： Gregor Veble Mikic ,  JoeBen Bevirt ,  Jeremy Bain ,  Alex Stoll

IPC分类号： B64C11/18 ,  B64C29/00 ,  B64C11/30 ,  B64C13/16 ,  G05D1/00

CPC分类号： B64C29/0033 ,  B64C11/18 ,  B64C11/303 ,  B64C13/16 ,  G05D1/102

摘要： The rotary airfoil 100 defines a cross section and a span, wherein the cross section is a function of the point along the span (e.g., spanwise point) and defines an upper surface and a lower surface at each spanwise point. The rotary airfoil 100 also defines, at a cross section, a lift coefficient (CL) that is a function of the angle of attack at which the airfoil is rotated through the air. The system can optionally include: a rotor hub to mount the rotary airfoil, a tilt mechanism to pivot the rotary airfoil between a forward configuration and a hover configuration, and a pitching mechanism to change the angle of attack of the rotary airfoil 100.

公开(公告)号：US11905007B2

公开(公告)日：2024-02-20

申请号：US17340811

申请日：2021-06-07

申请人： Archer Aviation, Inc.

发明人： Geoffrey C. Bower

IPC分类号： B64C29/00 ,  B64C23/06 ,  B64C39/10 ,  B64D27/24

CPC分类号： B64C29/0033 ,  B64C23/069 ,  B64C39/10 ,  B64D27/24

摘要： A passenger vertical take-off and landing aircraft includes a flying wing comprising a passenger compartment, a first set of rotors positioned at least partially forward of a leading edge of the flying wing, and a second set of rotors positioned at least partially rearward of a trailing edge of the flying wing. The first set of rotors may include at least four rotors and the second set of rotors may comprise at least two rotors. The first set of rotors, the second set of rotors, both, or neither may be tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.

公开(公告)号：US11905004B2

公开(公告)日：2024-02-20

申请号：US17190081

申请日：2021-03-02

申请人： Hyundai Motor Company ,  Kia Motors Corporation

发明人： Woo Suk Jung ,  Hee Kwang Lee ,  Hyun Seok Hong ,  Hyun Woo Jun

IPC分类号： B64D27/24 ,  B64D35/02 ,  B64D31/12 ,  B64D31/10 ,  B64D33/02 ,  B64D31/00 ,  B64D27/02 ,  B64C29/00 ,  B64C27/82 ,  B64C27/32 ,  B60L58/12 ,  B60L53/00

CPC分类号： B64C27/82 ,  B60L53/00 ,  B60L58/12 ,  B64C27/32 ,  B64C29/0025 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D31/10 ,  B64D31/12 ,  B64D33/02 ,  B64D35/02 ,  B60L2200/10 ,  B64C2027/8227 ,  B64D2027/026 ,  B64D2033/0213

摘要： In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.