WO2025106962A1 - Aéronef vtol à aile en flèche négative avec propulseurs de sustentation intégrés - Google Patents

Aéronef vtol à aile en flèche négative avec propulseurs de sustentation intégrés Download PDF

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Publication number
WO2025106962A1
WO2025106962A1 PCT/US2024/056366 US2024056366W WO2025106962A1 WO 2025106962 A1 WO2025106962 A1 WO 2025106962A1 US 2024056366 W US2024056366 W US 2024056366W WO 2025106962 A1 WO2025106962 A1 WO 2025106962A1
Authority
WO
WIPO (PCT)
Prior art keywords
propulsors
aircraft
vtol
vtol aircraft
wing tip
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
PCT/US2024/056366
Other languages
English (en)
Inventor
Neil Clark WINSTON
Robert Allen Winston
Clark William Fuller
Raymond Andrew MCCAULEY
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hop Flyt Inc
Original Assignee
Hop Flyt Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hop Flyt Inc filed Critical Hop Flyt Inc
Publication of WO2025106962A1 publication Critical patent/WO2025106962A1/fr
Anticipated expiration legal-status Critical
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/12—Canard-type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/20—Vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/294—Rotors arranged in the UAV body

Definitions

  • the present invention relates to aircraft design.
  • the present invention relates to a fixed wing vertical takeoff and landing forward swept wing aircraft design that incorporates tilting wingtip propulsors and embedded centerline propulsors to create a symmetrical layout of propulsors about the vehicle center of gravity during VTOL flight.
  • the present inventors have found that a symmetrical layout of propulsors about the aircraft center of gravity (CG) is desired.
  • One method to achieve such a configuration is to use a combination of propulsors embedded in the fuselage along the vehicle centerline, and tilting wingtip propulsors for dual use in VTOL and fixed wing flight.
  • the forward swept configuration combined with wingtip propulsors allows the aircraft to minimize drag producing effects caused by wingtip vortices, increasing the effective aspect ratio and efficiencies during fixed wing flight. Further, this combination reduces the risk of tip stall and enables excellent control authority at the high angles of attack required for maximum endurance flight conditions.
  • the present invention relates to an aircraft capable of VTOL and fixed wing flight, using a combination of thrust symmetrical embedded lift propulsors along the fuselage centerline and tilting wingtip propulsors.
  • the aircraft is designed to provide a thrust symmetrical layout of propulsors about their respective axis during VTOL flight.
  • Embodiments of the present invention may use a forward swept wing, with the sweep angle of the wing selected such that the two wingtip motors are laterally aligned about the vehicle center of gravity.
  • the wingtip propulsors augment lift of the vehicle in VTOL flight and provide control of the vehicle’s roll axis.
  • the embedded lift propulsors consist of propellers shrouded by a duct, embedded in the fuselage, and located along the vehicle centerline, longitudinally symmetric about the center of gravity. The embedded lift propulsors provide the majority thrust during VTOL flight, and aid in pitch control.
  • the resulting VTOL flight control system decouples pitch and roll control axis.
  • the embedded lift propulsors may provide pitch control, while the wingtip propulsors may stabilize the roll axis.
  • the large lever arm provided by the wingtip propulsors further aids stability and disturbance rejection during VTOL maneuvers.
  • the tilting actuation of the wingtip propulsors may allow for yaw control via thrust vectoring, as well as longitudinal velocity control.
  • the aircraft may use tilting wingtip propulsors in a forward configuration to provide thrust.
  • Retracting doors may be used to cover the ducts surrounding the embedded lift propulsors to reduce drag during fixed wing flight.
  • a canard located near the front of the aircraft may provide a balancing moment, and the incidence angle of the entire surface can be adjusted for trim.
  • Fixed wing flight controls are provided by control surfaces along the trailing edge of the main wing, adjustment of canard incidence angle, and differential thrust from the wingtip propulsors.
  • each of the propulsors is configured for direct drive from a respective motive source and the motive sources are electrically powered, use internal combustion, and/or use a hybrid power system.
  • the techniques described herein relate to a VTOL aircraft wherein the doors for each duct opening include a pair of doors pivotably hinged to the fuselage and may be operated by a door actuator mechanism having: a dual arm servo; a first lever arm coupled to a first door of a pair of doors; a second lever arm coupled to a second door of the pair of doors; and push/pull linkages coupling the first and second lever arms to the dual arm servo.
  • the techniques described herein relate to a VTOL aircraft wherein thrusts of the fore and aft propulsors are configured to be controlled independently to effect a pitch control of the aircraft; incremental tilting and thrust of the left and right wing tip propulsors are independently controllable to effect a yaw control of the aircraft; and thrust of the left and right wing tip propulsors are independently controllable to effect a roll control of the aircraft in the VTOL flight mode.
  • VTOL vertical take-off and landing
  • a fuselage defining fore and aft sections, left side and right side, topside and bottom side, and having a longitudinal centerline and a center of gravity; a forward swept wing extending from said left side and right side of the fuselage having a left wing tip and a right wingtip; a left wing tip propulsor and a right wing tip propulsor disposed at the left wing tip and right wing tip respectively, said left and right wing tip propulsors incrementally tiltable between a forward thrust position and a vertical thrust position; fore and aft vertical ducts, each having a top opening and a bottom opening; fore and aft propulsors disposed within the fore and aft vertical ducts, respectively, configured to provide vertical lift, wherein the fore and aft propulsors define a longitudinal axis through the center of gravity;
  • FIG. 1 illustrates a planform view of an exemplary embodiment of the aircraft in a VTOL configuration showing the layout of the aircraft and propulsors.
  • FIG. 2 illustrates an isometric view of an exemplary embodiment of the aircraft in a VTOL configuration.
  • FIG. 3 illustrates an isometric view of an exemplary embodiment of the aircraft in a fixed wing flight configuration.
  • FIG. 4 illustrates a detailed semi-transparent isometric view of the left wingtip propulsor tilt mechanism in an exemplary embodiment.
  • FIG. 5 illustrates a front section view along cut line 5-5 shown in FIG. 1 of the rear embedded lift propulsor mechanism in the fuselage in an exemplary embodiment.
  • any reference to an “embodiment” or “some embodiments” means that a particular element, feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the inventive concepts disclosed herein.
  • the appearances of the phrase “in some embodiments” in various places in the specification are not necessarily all referring to the same embodiment, and embodiments of the inventive concepts disclosed may include one or more of the features expressly described or inherently present herein, or any combination of sub-combination of two or more such features, along with any other features which may not necessarily be expressly described or inherently present in the instant disclosure.
  • FIG. 1 is a planform view of an exemplary embodiment of the aircraft 90 in a VTOL configuration showing the layout of the aircraft and propulsors.
  • the arrangement of the aft embedded lift propulsor 100 and forward embedded lift propulsor 110 within aft duct 102 and forward duct 112, respectively, along the vehicle centerline can be seen with symmetric placement about the vehicle center of gravity 140.
  • the two embedded lift propulsors are shrouded by a duct and fully embedded in the fuselage.
  • the forward swept wing 150 is shown, with the sweep angle of the wing selected such that the right wingtip motor 120 and left wingtip motor 130 are laterally aligned about the vehicle center of gravity 140.
  • FIG. 3 is an isometric of the aircraft 90 in a fixed wing flight configuration.
  • the aircraft 90 uses the propulsors 120 and 130 on the right wingtip tilt mechanism 300 and left wingtip tilt mechanism 310, respectively, tilted forward to provide thrust and yaw control in fixed wing flight.
  • ailerons 320 located along the trailing edges of the wing 150 provide roll control.
  • Forward upper duct doors 220 and forward lower duct doors 222 and aft upper duct doors 230 and aft lower duct doors 232 are used to cover duct 102 and duct 112 surrounding the embedded lift propulsors, creating a streamlined fuselage to reduce drag.
  • a canard 350 is located near the front of the aircraft and may provide a balancing moment and trim the aircraft pitch axis.
  • the entire canard 350 may rotate and/or an elevator 360 on a trailing edge of the canard may provide the balancing moment and aircraft pitch trim.
  • FIG. 4 is a semi-transparent isometric detail view of the left wingtip tilt mechanism 310.
  • the mechanism 310 may consist of a left wingtip propulsor 130 with attached wingtip propulsor fairing 400.
  • the propulsor 130 and fairing 400 rotate about a protruding cylindric spar 410 located at the end of the main portion of the swept wing 150. Rotation is achieved by using a geared servo mechanism 430.
  • a right wingtip tilt mechanism is similar in design.
  • FIG. 5 is a front section view taken along cut-line 5-5 shown in FIG. 1 of an aft embedded propulsor door mechanism.
  • a forward embedded propulsor door mechanism may be similar in design.
  • Each mechanism may include a set of top doors 230 and bottom doors 232 of the fuselage. Operation of the doors may use a configuration of adjustable linkages 520 that push/pull lever arms 530 that are attached to each door segment. Actuation of the linkages may be made using a dual arm servo 540.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Transmission Devices (AREA)

Abstract

L'invention concerne un aéronef conçu pour un décollage et un atterrissage verticaux (VTOL) et un vol à voilure fixe. La structure de l'aéronef comprend un fuselage caréné, une aile en flèche négative et un canard, présentant une configuration de propulseurs intégrés symétriquement le long du centre longitudinal de gravité de l'aéronef et des hélices inclinables sur les bouts d'aile en flèche négative. De plus, le fuselage comprend des portes vers les conduits de propulsion qui peuvent être ouverts pour un vol vertical et fermés pour un vol vers l'avant.
PCT/US2024/056366 2023-11-16 2024-11-18 Aéronef vtol à aile en flèche négative avec propulseurs de sustentation intégrés Pending WO2025106962A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US202363599870P 2023-11-16 2023-11-16
US63/599,870 2023-11-16

Publications (1)

Publication Number Publication Date
WO2025106962A1 true WO2025106962A1 (fr) 2025-05-22

Family

ID=95743549

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2024/056366 Pending WO2025106962A1 (fr) 2023-11-16 2024-11-18 Aéronef vtol à aile en flèche négative avec propulseurs de sustentation intégrés

Country Status (1)

Country Link
WO (1) WO2025106962A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040026563A1 (en) * 2002-02-08 2004-02-12 Moller Paul S. Vertical take-off and landing vehicles
US20150274289A1 (en) * 2014-03-31 2015-10-01 The Boeing Corporation Vertically landing aircraft
US20180354613A1 (en) * 2017-06-08 2018-12-13 Airbus Defence and Space GmbH Aerial vehicle
US20190144107A1 (en) * 2017-11-13 2019-05-16 Bell Helicopter Textron Inc. Segmented Duct for Tilting Proprotors
US20190270517A1 (en) * 2016-10-27 2019-09-05 Mono Aerospace Ip Ltd Vertical take-off and landing aircraft
US10696390B2 (en) * 2016-09-08 2020-06-30 Hop Flyt Inc Aircraft having independently variable incidence channel wings with independently variable incidence channel canards
US20210031909A1 (en) * 2019-07-30 2021-02-04 Rolls-Royce Plc Lift rotor system
US20210300540A1 (en) * 2020-03-28 2021-09-30 Textron Innovations Inc. Ducted Fans having Fluidic Thrust Vectoring
US20230257114A1 (en) * 2022-02-15 2023-08-17 Chung Kiak POH Airplane that performs vertical takeoff with a positive pitch angle

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040026563A1 (en) * 2002-02-08 2004-02-12 Moller Paul S. Vertical take-off and landing vehicles
US20150274289A1 (en) * 2014-03-31 2015-10-01 The Boeing Corporation Vertically landing aircraft
US10696390B2 (en) * 2016-09-08 2020-06-30 Hop Flyt Inc Aircraft having independently variable incidence channel wings with independently variable incidence channel canards
US20190270517A1 (en) * 2016-10-27 2019-09-05 Mono Aerospace Ip Ltd Vertical take-off and landing aircraft
US20180354613A1 (en) * 2017-06-08 2018-12-13 Airbus Defence and Space GmbH Aerial vehicle
US20190144107A1 (en) * 2017-11-13 2019-05-16 Bell Helicopter Textron Inc. Segmented Duct for Tilting Proprotors
US20210031909A1 (en) * 2019-07-30 2021-02-04 Rolls-Royce Plc Lift rotor system
US20210300540A1 (en) * 2020-03-28 2021-09-30 Textron Innovations Inc. Ducted Fans having Fluidic Thrust Vectoring
US20230257114A1 (en) * 2022-02-15 2023-08-17 Chung Kiak POH Airplane that performs vertical takeoff with a positive pitch angle

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