公开(公告)号：US12071231B2

公开(公告)日：2024-08-27

申请号：US18467322

申请日：2023-09-14

Applicant: Wisk Aero LLC

Inventor： Zouhair Mahboubi ,  Gabe Hoffmann ,  Olivier Toupet ,  Herve Martins-Rivas

IPC: B64C29/00 ,  B64C27/28 ,  G05D1/00

CPC classification number: B64C29/00 ,  B64C27/28 ,  B64C29/0025 ,  G05D1/0808 ,  G05D1/085 ,  G05D1/101 ,  G05D1/102

Abstract: Techniques to control flight of an aircraft are disclosed. In various embodiments, a set of inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is determined.

公开(公告)号：US20240140598A1

公开(公告)日：2024-05-02

申请号：US18496850

申请日：2023-10-28

Applicant: Leviation Technology, Inc.

Inventor： Johnny Tseng-Pei Doo ,  William Doo ,  Tseng-Hua Tsiang

IPC: B64C27/10 ,  B64C27/28 ,  B64C27/52

CPC classification number: B64C27/10 ,  B64C27/28 ,  B64C27/52

Abstract: A compound vertical takeoff and landing aircraft includes a fuselage with a modular payload configuration for passenger, cargo, or medical transport functions; contra-rotating main rotors mounted on an upper side of the fuselage and driven by at least one motor; and a plurality of tiltable thrusters mounted respectively at a forward section and at an aft section of the fuselage, each tiltable thruster being powered by one or more separate motors. The motors driving the contra-rotating main rotors and the tiltable thrusters may all be electric. The tiltable thrusters may be ducted or unducted and may each be provided with one or more control surfaces at an aft end. Battery modules may be located underneath a floor of the fuselage and may be arranged in one or more groups of batteries so as to so as to facilitate removal and replacement of the batteries.

公开(公告)号：US11919631B2

公开(公告)日：2024-03-05

申请号：US17170242

申请日：2021-02-08

Applicant: Archer Aviation, Inc.

Inventor： Geoffrey C. Bower

IPC: B64C29/00 ,  B64C27/28

CPC classification number: B64C29/0033 ,  B64C27/28

Abstract: A vertical take-off and landing aircraft may include a fuselage; at least one wing connected to the fuselage; a first plurality of proprotors mounted to the at least one wing, positioned at least partially forward of a leading edge of the at least one wing, and 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; and a second plurality of proprotors mounted to the at least one wing, positioned at least partially rearward of a trailing edge of the at least one wing, and 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; wherein the first plurality of proprotors and the second plurality of proprotors are independently tiltable.

公开(公告)号：US11814153B2

公开(公告)日：2023-11-14

申请号：US17552052

申请日：2021-12-15

Applicant: Bell Textron Inc.

Inventor： Kyle Thomas Cravener ,  Andrew Maresh ,  Jonathan Andrew Knoll

IPC: B64C11/28 ,  B64C29/00 ,  B64C27/28 ,  B64C11/04

CPC classification number: B64C11/28 ,  B64C11/04 ,  B64C27/28 ,  B64C29/0033

Abstract: A system for retaining a folded proprotor blade in flight. The system includes a mounting plate, a first arm coupled to the mounting plate at an acute angle relative to the mounting plate, and a first deformable pad affixed to the first arm and adapted to contact the folded proprotor blade.

公开(公告)号：US20180273169A1

公开(公告)日：2018-09-27

申请号：US15990610

申请日：2018-05-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Steven Ray Ivans ,  Nathan Gabriel Wu

IPC: B64C29/00 ,  B64C7/02 ,  B64C11/00 ,  B64C3/38

CPC classification number: B64C29/0033 ,  B64C3/38 ,  B64C5/08 ,  B64C7/02 ,  B64C27/28 ,  B64C29/02 ,  Y02T50/14

Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.

公开(公告)号：US20180215465A1

公开(公告)日：2018-08-02

申请号：US15884238

申请日：2018-01-30

Applicant: Joseph Raymond Renteria

Inventor： Joseph Raymond Renteria

IPC: B64C29/00 ,  B64C25/10 ,  B64C27/02 ,  B64C27/26 ,  B64C27/28

CPC classification number: B64C29/0033 ,  B64C25/10 ,  B64C27/02 ,  B64C27/04 ,  B64C27/20 ,  B64C27/26 ,  B64C27/28 ,  B64C29/0025 ,  Y02T50/44

Abstract: A rotatable thruster aircraft includes a fixed wing; rotatable thruster assemblies, each including first and second thrusters that provide rotation via differential thrust; and vertical lift thrusters, optionally connected via an elongated member; and an aircraft control unit, including a processor, a non-transitory memory, an input/output component, and a power manager that controls specific power applied to the thrusters.

公开(公告)号：US20180057158A1

公开(公告)日：2018-03-01

申请号：US15674708

申请日：2017-08-11

Applicant: AIRBUS HELICOPTERS

Inventor： Michel VIALLE ,  Sylvain BERTHALON

IPC: B64C27/82 ,  B64C27/26 ,  B64C27/605 ,  B64C27/06

CPC classification number: B64C27/82 ,  B64C27/06 ,  B64C27/26 ,  B64C27/28 ,  B64C27/605 ,  B64C2027/8227

Abstract: A rotorcraft having a fuselage surmounted by a main rotor. The rotorcraft has a first propeller and a second propeller driven in rotation respectively about a first secondary axis of rotation and a second secondary axis of rotation. A mobility system turns the second propeller relative to the fuselage, the mobility system turning the second secondary axis of rotation relative to the fuselage from a first position where the second propeller exerts thrust in a first direction to a second position where the second propeller exerts thrust in a second direction opposite to the first direction.

公开(公告)号：US20180022462A1

公开(公告)日：2018-01-25

申请号：US15719807

申请日：2017-09-29

Applicant: Bell Helicopter Textron Inc.

Inventor： James Elbert King ,  Jeffrey Matthew Williams ,  Christopher R. Jackson ,  Andrew G. Baines ,  James Everett Kooiman

IPC: B64D27/26 ,  B64C29/00 ,  B64C3/32 ,  B64C27/26 ,  B64D35/00 ,  F16H57/02 ,  F16C17/02 ,  F16H57/021

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64C27/14 ,  B64C27/26 ,  B64C27/28 ,  B64C29/0033 ,  B64D27/12 ,  B64D35/00 ,  B64D35/08 ,  B64D2027/264 ,  B64D2027/266 ,  F16C17/02 ,  F16H57/021 ,  F16H2057/02043 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A pedestal assembly receives a pylon assembly of a tiltrotor aircraft having an airframe including a fuselage and a wing. The pedestal assembly includes inboard and outboard tip ribs that extend above the wing and respectively define inboard and outboard slots. The pedestal assembly also includes inboard and outboard bearing cartridges. The inboard bearing cartridge is received within the inboard slot, is coupled to the inboard tip rib and includes an inboard bearing assembly. The outboard bearing cartridge is received within the outboard slot, is coupled to the outboard tip rib and includes an outboard bearing assembly. The inboard and outboard bearing assemblies are operable to receive the pylon assembly therein such that the pylon assembly is rotatably mounted between the inboard and outboard tip ribs to selectively operate the tiltrotor aircraft between a helicopter mode and an airplane mode.

公开(公告)号：US09856029B2

公开(公告)日：2018-01-02

申请号：US15407486

申请日：2017-01-17

Applicant: Bell Helicopter Textron Inc.

Inventor： James Elbert King ,  Jeffrey Matthew Williams ,  Christopher R. Jackson ,  Andrew G. Baines ,  James Everett Kooiman

IPC: B64D27/26 ,  B64C29/00 ,  B64C27/26 ,  B64C3/32 ,  B64D35/00 ,  F16C17/02 ,  F16H57/021 ,  F16H57/02

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64C27/14 ,  B64C27/26 ,  B64C27/28 ,  B64C29/0033 ,  B64D27/12 ,  B64D35/00 ,  B64D35/08 ,  B64D2027/264 ,  B64D2027/266 ,  F16C17/02 ,  F16H57/021 ,  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 tip ribs extend above the wing and define slots. Inboard and outboard bearing cartridges are received in respective slots. The inboard and outboard bearing cartridges respectively include inboard and outboard bearing assemblies. A pylon assembly is rotatably coupled between the inboard and outboard bearing assemblies. 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.

公开(公告)号：US20170217595A1

公开(公告)日：2017-08-03

申请号：US15409971

申请日：2017-01-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Tyler Wayne Baldwin ,  John Elton Brunken, JR. ,  Matthew Carl VanBuskirk ,  Bart Marcus Shafer ,  Bruce Bennett Bacon

IPC: B64D27/26 ,  B64D27/12 ,  B64C29/00

CPC classification number: B64D27/26 ,  B64C27/28 ,  B64C29/0033 ,  B64D27/12 ,  B64D2027/262

Abstract: An engine mount assembly for coupling an engine to an airframe includes a torsion bar, a lateral movement control assembly and a vertical movement control assembly. The torsion bar has a torsional stiffness and is coupled between the engine and the airframe such that torsional movement of the engine causes torsion in the torsion bar. The lateral movement control assembly has a lateral stiffness and is coupled between the torsion bar and the airframe such that lateral movement of the engine causes rotation of the torsion bar which reacts on lateral movement control assembly. The vertical movement control assembly has a vertical stiffness and is coupled between the engine and the airframe such that vertical movement of the engine reacts on the vertical movement control assembly. The engine mount assembly, thereby enables torsional, lateral and vertical movement of the engine to be independently controlled.