公开(公告)号：US12122503B1

公开(公告)日：2024-10-22

申请号：US17948545

申请日：2022-09-20

Applicant: Wisk Aero LLC

Inventor： Geoffrey Alan Long

IPC: B64C11/04 ,  B64C11/46 ,  B64C27/02 ,  B64C27/22

CPC classification number: B64C11/04 ,  B64C11/46 ,  B64C27/021 ,  B64C27/22

Abstract: Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and/or away from an airflow current.

公开(公告)号：US20240101252A1

公开(公告)日：2024-03-28

申请号：US18525850

申请日：2023-12-01

Applicant: Joby Aero, Inc.

Inventor： Alex Stoll ,  Gregor Veble Mikic ,  JoeBen Bevirt

IPC: B64C27/26 ,  B64C3/10 ,  B64C3/32 ,  B64C27/08 ,  B64C27/22 ,  B64C27/52 ,  B64C29/00 ,  B64C39/06

CPC classification number: B64C27/26 ,  B64C3/10 ,  B64C3/32 ,  B64C27/08 ,  B64C27/22 ,  B64C27/52 ,  B64C29/0016 ,  B64C39/06 ,  B64C39/068 ,  B64C2027/8236

Abstract: A vertical take-off and landing aircraft and method which uses fixed rotors for both VTOL and forward flight operations. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the wing. The wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

公开(公告)号：US11926443B2

公开(公告)日：2024-03-12

申请号：US18035443

申请日：2021-11-29

Applicant: EFIX AVIATION LTD

Inventor： Efraim Kastiel

IPC: B64U10/14 ,  B64C27/22 ,  B64U10/11 ,  B64U30/29 ,  B64U50/19 ,  G05D1/00

CPC classification number: B64U10/14 ,  B64C27/22 ,  B64U10/11 ,  B64U30/29 ,  B64U50/19 ,  G05D1/102

Abstract: Rotorcraft including a fuselage, at least three rotor system arms, a forward propulsion unit for providing forward propulsion to the rotorcraft and a flight control system. Each rotor system arm has a rotor system including a mast having at least two rotor blades and an electric rotor motor coupled to the mast for driving the mast whereupon the rotor blades act as a rotating rotor disc. Each rotor system has an individually controllable collective rotor blade pitch. At least one rotor system has a controllable cyclic rotor blade pitch. The flight control system controls the at least three electric rotor motors, the collective rotor blade pitch of each rotor system, the cyclic rotor blade pitch of the at least one rotor system and the forward propulsion unit in response to an input control indicating a desired maneuver to operate the rotorcraft for takeoff, flight and landing.

公开(公告)号：US11853054B2

公开(公告)日：2023-12-26

申请号：US17603193

申请日：2021-10-12

Applicant: Aergility Corporation

Inventor： James E. Vander Mey ,  Lawrence Winston Yonge, III

IPC: B64C27/02 ,  G05D1/08 ,  B64C11/50 ,  B64C27/10 ,  B64C27/12 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C27/00 ,  B64C27/14 ,  B64D27/24 ,  H02K1/27 ,  B64C11/48 ,  B64C27/82

CPC classification number: G05D1/0858 ,  B64C11/50 ,  B64C27/006 ,  B64C27/02 ,  B64C27/021 ,  B64C27/025 ,  B64C27/027 ,  B64C27/028 ,  B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C11/48 ,  B64C2027/8236 ,  B64D27/24 ,  H02K1/27

Abstract: A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

公开(公告)号：US11829161B2

公开(公告)日：2023-11-28

申请号：US17603180

申请日：2020-04-10

Applicant: Aergility Corporation

Inventor： James E. Vander Mey ,  Lawrence Winston Yonge, III

IPC: B64C27/10 ,  G05D1/08 ,  B64C11/50 ,  B64C27/02 ,  B64C27/12 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C27/00 ,  B64C27/14 ,  B64D27/24 ,  H02K1/27 ,  B64C11/48 ,  B64C27/82

CPC classification number: G05D1/0858 ,  B64C11/50 ,  B64C27/006 ,  B64C27/02 ,  B64C27/021 ,  B64C27/025 ,  B64C27/027 ,  B64C27/028 ,  B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/22 ,  B64C27/26 ,  B64D31/00 ,  B64C11/48 ,  B64C2027/8236 ,  B64D27/24 ,  H02K1/27

Abstract: A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

公开(公告)号：US20180093770A1

公开(公告)日：2018-04-05

申请号：US15831003

申请日：2017-12-04

Applicant: Amazon Technologies, Inc.

Inventor： Ricky Dean Welsh ,  Daniel Buchmueller ,  Fabian Thomas Hensel ,  Gur Kimchi ,  Louis LeRoi LeGrand, III ,  Brandon William Porter ,  Walker Chamberlain Robb ,  Joshua White Traube

IPC: B64C39/02 ,  B64C29/00 ,  B64C27/22 ,  B64C27/24

CPC classification number: B64C39/024 ,  B64C27/22 ,  B64C27/24 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pushing motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor may be engaged and the pushing propeller will aid in the horizontal propulsion of the UAV.

公开(公告)号：US09845150B2

公开(公告)日：2017-12-19

申请号：US13764697

申请日：2013-02-11

Applicant: Kitty Hawk Corporation

Inventor： Ilan Kroo

IPC: B64C27/22 ,  B64C3/56 ,  B64C29/00

CPC classification number: B64C27/22 ,  B64C3/56 ,  B64C29/00 ,  B64C29/0025 ,  B64C39/08 ,  Y02T50/14 ,  Y02T50/145

Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

公开(公告)号：US09834303B2

公开(公告)日：2017-12-05

申请号：US13966726

申请日：2013-08-14

Applicant: Bell Helicopter Textron Inc.

Inventor： David R. Bockmiller ,  James E. Kooiman

IPC: B64C27/22 ,  B64C29/00 ,  B64F5/40

CPC classification number: B64C27/22 ,  B64C29/0033 ,  B64F5/40 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A quill shaft is configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft includes a first splined portion configured for coupling to an output gear of the fixed gearbox, and a second splined portion configured for coupling to an input gear of the spindle gearbox. The spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor aircraft can selectively operate in a helicopter mode and airplane mode.

公开(公告)号：US20170305565A1

公开(公告)日：2017-10-26

申请号：US15407449

申请日：2017-01-17

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Matthew Carl VanBuskirk ,  Andrew G. Baines ,  Keith Alan Stanney

IPC: B64D27/26 ,  F16C17/26 ,  F16C17/02 ,  B64D35/00 ,  B64C29/00 ,  B64C27/26 ,  B64C3/32 ,  F16H57/02

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64C27/22 ,  B64C27/26 ,  B64C29/0033 ,  B64D35/00 ,  B64D2027/266 ,  B64F5/40 ,  F16C17/02 ,  F16C17/26 ,  F16H2057/02043 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a journal bearing that provides a stiff coupling with the pylon assembly.

公开(公告)号：US20170297693A1

公开(公告)日：2017-10-19

申请号：US15513726

申请日：2015-09-21

Applicant: Sikorsky Aircraft Corporation

Inventor： Matthew T. Luszcz ,  Matthew A. White ,  Kenneth S. Wittmer

IPC: B64C27/57 ,  B64C27/605 ,  B64C27/10

CPC classification number: B64C27/57 ,  B64C27/10 ,  B64C27/22 ,  B64C27/605

Abstract: A system and method for counteracting a rotor moment of one or more rotors of a coaxial rotor helicopter includes receiving signals with a processor indicative of a displacement command from a controller during a flight maneuver; receiving one or more signals with the processor from a sensor indicative of an airspeed and air density for the helicopter; determining a commanded rate of acceleration for the helicopter during the flight maneuver; and adjusting with one or more control servos a cyclic pitch for the one or more rotors to counteract the rotor moment during the flight maneuver.