公开(公告)号：US11639217B2

公开(公告)日：2023-05-02

申请号：US16980296

申请日：2019-03-13

申请人： INNOSTAR

发明人： Jean-Michel Simon ,  Philippe Roesch

IPC分类号： B64C27/30 ,  B64C27/26

摘要： An aerodyne comprises a fuselage, a fixed wing , a thruster for cruising flight, and a rotary wing for stages of vertical flight and held stationary during cruising flight. The rotary wing includes at least two contrarotating single-blades disposed at the top of the fuselage and hinged about respective axes perpendicular to the rotor axes of rotation. A maneuvering procedure for maneuvering the aerodyne includes a transition stage between a stage of vertical flight and a stage of cruising flight, wherein in the transition stage, when the speed of each single-blade is less than a threshold speed of rotation, the pitch of each single-blade is such that it no longer provides any lift force and the transverse hinge of the single-blade to its rotor axis is held locked in a position such that the single-blade is perpendicular to the rotor shaft.

公开(公告)号：US11618550B2

公开(公告)日：2023-04-04

申请号：US17220097

申请日：2021-04-01

申请人： The Boeing Company

发明人： Michael J. Duffy ,  Matthew S. Stauffer

IPC分类号： B64C11/28 ,  B64C39/02 ,  B64C11/04 ,  B64C27/30 ,  B64C29/00 ,  B64C27/26 ,  B64C27/473 ,  B64U30/10 ,  B64U30/20 ,  B64U70/80

摘要： A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.

公开(公告)号：US11597505B1

公开(公告)日：2023-03-07

申请号：US16860370

申请日：2020-04-28

申请人： SiFly Aviation, Inc.

发明人： Brian L. Hinman ,  Phil Frank

IPC分类号： B64C27/26

摘要： An improved rotorcraft of the type having a fuselage and a set of N≥4 rotors. The rotorcraft includes a structural support system affixed to the fuselage and mounting the set of rotors. The support system is configured as a set of airfoils that provide lift when the fuselage is in level flight. The fuselage has a central longitudinal axis that defines the direction of forward flight of the rotorcraft. Each of the rotors defines a corresponding rotational plane, that is tilted forward in the direction of the forward flight, when the central longitudinal axis of the fuselage is horizontal. Each airfoil may be positioned so that a majority of its length is disposed beneath the rotational plane of its corresponding rotor. When the rotorcraft is at a cruise speed, the airfoils are configured to provide lift that approximately matches the lift provided by the rotors.

公开(公告)号：US11591077B2

公开(公告)日：2023-02-28

申请号：US17334311

申请日：2021-05-28

申请人： SUBARU CORPORATION ,  Japan Aerospace Exploration Agency

发明人： Wataru Kobayashi ,  Hirotaka Hayashi ,  Mizuki Nakamura ,  Masafumi Sasaki ,  Yasutada Tanabe ,  Noboru Kobiki ,  Hideaki Sugawara

IPC分类号： B64C27/26 ,  B64C27/00 ,  B64C13/50

摘要： Provided is a vibration control system for a compound helicopter with a rotor and a fixed wing. The fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing. The vibration control system periodically moves the movable flap so as to periodically change lift of the fixed wing such that vibration aerodynamically generated by the fixed wing is in anti-phase with vibration caused by rotation of the rotor.

公开(公告)号：US11535368B2

公开(公告)日：2022-12-27

申请号：US17396709

申请日：2021-08-08

申请人： Shanghai Autoflight Co., Ltd.

发明人： Yu Tian

IPC分类号： B64C27/26 ,  B64C27/28 ,  B64C39/02

摘要： A vertical takeoff and landing aerial vehicle. A left linear support and a right linear support of the unmanned aerial vehicle are respectively provided with a first group of multiple lift propellers and a second group of lift propellers, and the aerial vehicle is provided with a left dorsal fin and a right dorsal fin. By arranging a plurality of lift propellers, a left dorsal fin, and a right dorsal fin on the vertical takeoff and landing aerial vehicle provided by the disclosure, the aerial vehicle is higher in stability in the flight process.

公开(公告)号：US20220402601A1

公开(公告)日：2022-12-22

申请号：US17746591

申请日：2022-05-17

申请人： AIRBUS HELICOPTERS

发明人： Kamel ABDELLI

IPC分类号： B64C27/57 ,  B64C27/26 ,  B64D31/12 ,  B64D35/04

摘要： A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

公开(公告)号：US20220297828A1

公开(公告)日：2022-09-22

申请号：US17573353

申请日：2022-01-11

申请人： AeroVironment, Inc.

发明人： Henry Thome Won ,  Quentin Lindsey

IPC分类号： B64C27/26 ,  B64D27/06 ,  B64C29/02 ,  B64C39/02

摘要： Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

公开(公告)号：US11449057B2

公开(公告)日：2022-09-20

申请号：US16868647

申请日：2020-05-07

申请人： AIRBUS HELICOPTERS

发明人： Kamel Abdelli

IPC分类号： G01D7/00 ,  G05D1/02 ,  B64C27/26

摘要： A method of facilitating piloting a hybrid rotorcraft having at least one propulsive rotor provided with a plurality of first blades and a lift rotor provided with a plurality of second blades, the hybrid rotorcraft having a power plant. The method includes a step of displaying on a single indicator a first pointer, the position of which along a movement path varies as a function of a first power from the power plant that is consumed by the propulsive system, and of displaying a second pointer, the position of which varies as a function of a second power of the power plant that is consumed by the lift rotor, a variable space between the first pointer and the second pointer representing a power margin from the power plant that is not used so long as the first pointer is situated between the first end and the second pointer.

公开(公告)号：US11325699B2

公开(公告)日：2022-05-10

申请号：US16833618

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

摘要： A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

公开(公告)号：US20220097846A1

公开(公告)日：2022-03-31

申请号：US17465365

申请日：2021-09-02

申请人： Endurant Systems, LLC

发明人： Gregory Leonard McAdoo

IPC分类号： B64C39/02 ,  B64C27/08 ,  B64D27/24 ,  B64C27/26 ,  B64C29/00 ,  B64C39/04 ,  H02J7/14 ,  H02J7/34 ,  B64D45/00 ,  H02K7/18

摘要： UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.