GB2601453A - An aircraft - Google Patents

An aircraft Download PDF

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Publication number
GB2601453A
GB2601453A GB2203125.6A GB202203125A GB2601453A GB 2601453 A GB2601453 A GB 2601453A GB 202203125 A GB202203125 A GB 202203125A GB 2601453 A GB2601453 A GB 2601453A
Authority
GB
United Kingdom
Prior art keywords
wing
aircraft
rotor
aircraft according
main body
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.)
Granted
Application number
GB2203125.6A
Other versions
GB202203125D0 (en
GB2601453B (en
Inventor
De Graaff Arent-Jan
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.)
GKN Aerospace Services Ltd
Original Assignee
GKN Aerospace Services Ltd
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 GKN Aerospace Services Ltd filed Critical GKN Aerospace Services Ltd
Priority to GB2203125.6A priority Critical patent/GB2601453B/en
Priority claimed from GB1910278.9A external-priority patent/GB2585864B/en
Publication of GB202203125D0 publication Critical patent/GB202203125D0/en
Publication of GB2601453A publication Critical patent/GB2601453A/en
Application granted granted Critical
Publication of GB2601453B publication Critical patent/GB2601453B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • 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
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • 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
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/08—Aircraft not otherwise provided for having multiple wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

A VTOL aircraft with a main body between a pair of wing sections 12, each wing section having a front wing 14 and a rear wing 16. The fore and aft wings each comprise a first end 17, 20 connected to the main body. A second end 18 of the front wing is connected to a second end 22 of the rear wing, defining a loop that connects to the main body in two locations. Starting from the second end of the rear wing, the rear edge of the rear wing diverges away from the front wing. Each wing section comprises a pivotable propulsion unit 30 located between the fore and aft wings. The aircraft may not have a tail fin or tail rotor. The rear wing may be higher than the front wing. The propulsion units may comprise a first rotor 32 and second rotor 34, wherein the first and second rotors are connected to and at least partially accommodated in a recess within the fore and aft wings respectively. The rotors may be located nearer the first end of the respective wing than the second end. The first rotor may connect to the main body.

Description

An Aircraft
Background
The present invention is concerned with an aircraft.
There currently exists a number of different types of aircraft employing a variety of different shapes and sizes. The present invention is directed to a particular aircraft type having a particular type of wing design, which is nominally particularly suited for use in smaller aircraft and also VTOL (vertical take-off and landing) aircraft.
Summary of the Invention
Aspects of the invention are set out in the accompanying claims.
In that respect, in accordance with a first aspect there is provided an aircraft comprising: a main body; a pair of wing sections, each wing section comprising a front wing and a rear wing, wherein the front wing and the rear wing each comprise a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing; wherein the main body is located between the pair of wing sections, and each wing section comprises a propulsion unit located between the front wing and the rear wing of the wing section.
The provision of the pair of wing sections whose front and rear wings each have a second end that are connected to each other, where the propulsion unit is located between these front and rear wings provides an aerodynamic arrangement that is particularly suited for use in smaller aircraft and also VTOL (vertical take-off and landing) aircraft.
It will be appreciated that a variety of different propulsion units may be used for propelling aircraft in use. However, in some embodiments, each propulsion unit may comprise a first rotor and a second rotor, which may in some particular embodiments be pivotable with respect to the front and rear wings as required and/or the rest of the aircraft.
The first rotor in some embodiments may be connected to the front wing and/or connected to the main body.
The front wing may comprise a recess in which the first rotor is at least partially accommodated.
In accordance with some embodiments, the first rotor may be located nearer the first end of the front wing than it is to the second end of the front wing.
The second rotor in some embodiments may be connected to the rear wing.
The rear wing may comprise a recess in which the second rotor is at least partially 20 accommodated In accordance with some embodiments, the second rotor may be located nearer the first end of the rear wing than it is to the second end of the rear wing.
In some embodiments, the rear wing may be located above the front wing in a height direction of the aircraft.
In accordance with some embodiments, to help control and direct the thrust generated from the first and second rotors of each wing section, the second rotor in such embodiments may be located above the first rotor.
In accordance with some embodiments, for each wing portion, the rear wing may comprise a rear edge, wherein starting from the second end of the rear wing in a direction towards the first end of the rear wing, the rear edge of the rear wing extends in a direction away from the front wing.
The main body may comprise a canopy enclosing a cockpit of the aircraft, wherein at least one of the rotors is located beneath the canopy in a height direction of the aircraft. In such embodiments, to reduce the chance of injury to an occupant of the aircraft when it is in use, it may be that each first rotor is located beneath the canopy in a height direction of the aircraft, and/or each second rotor may be located beneath the canopy in a height direction of the aircraft. In some embodiments, each second rotor may be at least partially located behind the canopy in a length direction of the aircraft.
In the broadest sense of the invention, it is envisaged that any type of aircraft may be employed. In some particular embodiments however, the aircraft may be a single-seat aircraft; an unmanned aerial vehicle; and/or a VTOL (vertical take-off and landing) aircraft.
Drawings Aspects of the invention will now be described, by way of example only, with reference to the accompanying figures in which: Figure 1 shows a perspective view of a first embodiment aircraft.
Figure 2 shows a perspective view of a second embodiment aircraft.
While the invention is susceptible to various modifications and alternative forms, specific embodiments are shown by way of example in the drawings and are herein described in detail. It should be understood however that drawings and detailed description attached hereto are not intended to limit the invention to the particular form disclosed but rather the invention is to cover all modifications, equivalents and alternatives falling within the spirit and scope of the claimed invention It will be recognised that the features of the aspects of the invention(s) described herein can conveniently and interchangeably be used in any suitable combination. It will also be recognised that the invention covers not only individual embodiments but also combinations of the embodiments that have been discussed herein.
Detailed Description
Aspects and features of certain examples and embodiments are discussed / described herein. Some aspects and features of certain examples and embodiments may be implemented conventionally and these are not discussed / described in detail in the interests of brevity. It will thus be appreciated that aspects and features of apparatus and methods discussed herein which are not described in detail may be implemented in accordance with any conventional techniques for implementing such aspects and features.
With reference to the Figures, there is shown an aircraft 1 comprising a main body 10 and a pair of wing sections 12. In the aircraft shown in the Figures, the aircraft 1 extends about a length direction L, a width direction W, and a height direction H, which are all directions that are perpendicular to each other.
The main body 10 is located between the pair of wing sections 12, such that the pair of wing sections comprises a first, left, wing section 12A located on a first, left, side 10A of the main body; and a second, right, wing section 12B located on a second, right, side 10B of the main body 10.
Each wing section 12 comprises a front wing 14 and a rear wing 16. The front wing 14 comprises a first end 17 that is connected to the main body 10, and a second end 18 which is opposite the first end of the front wing. Similarly, the rear wing 16 comprises a first end 20 that is connected to the main body 10, and a second end 22 which is opposite the first end 20 of the rear wing 16.
The second end 18 of the front wing 14 of each wing section 12 is connected to the second end 22 of the rear wing 16 of the wing section. As such, each wing section forms a loop that is connected to the main body 10 in at least two locations, namely at the first end 17 of the front wing 14, and at the first end 20 of the rear wing 16. This arrangement generates a wing section 12 that has both good mechanical strength, and which also demonstrates reduced induced drag properties.
In the embodiments shown in the Figures, the rear wing 16 of each wing section 12 may be located above (for the avoidance of any doubt, not necessarily directly above), the front wing 14 in a height direction H of the aircraft 10.
The rear wing of each wing section comprises a rear/trailing edge 24. In accordance with some embodiments, starting from the second end 22 of the rear wing 16 in a direction towards the first end 20 of the rear wing 16, the rear edge 24 may extend in a direction D1 away from the front wing 14. Put differently, each direction D1 may extend in a rearward direction towards a rear of the main body 10.
Each wing section 12 comprises a propulsion unit 30, located between the front wing 14 and the rear wing 16 of the wing section, for generating thrust to propel the aircraft in use. In the aircraft 10 shown in the Figures, each propulsion unit 30 comprises a first rotor 32 and a second rotor 34. In such embodiments, the propulsion unit 30 of each wing section 12 may be located between a front/leading edge 36 of the front wing 14 and the rear edge 24 of the rear wing 16. Providing such a wing section 12 where the propulsion unit 30 is located between the front wing 14 and the rear wing 16 not only provides for a wing section 12 with good mechanical strength, but also allows the front and rear wings 14;16 to act as a physical barrier for better preventing inadvertent access by ground crew to the propulsion unit 30when the aircraft 1 is on the ground and when the propulsion unit 30 is operational.
In accordance with some embodiments, the first rotor 32 may be connected to the front wing 14, and/or the main body 10. In some embodiments, such as those shown in the embodiment of aircraft from Figures 1 and 2, the front wing 14 of each wing section 12 may comprise a recess 38 in which the first rotor 32 is at least partially accommodated. In accordance with some embodiments, the first rotor 32 may be pivotable with respect to the front wing 14 and/or the recess 32 as required to allow better control of thrust generated from the rotor with respect to the aircraft 1.
With respect to the second rotor 34 of each wing section 12, in some embodiments the second rotor 34 may be connected to the rear wing 16 and/or the main body 10. In some embodiments, the rear wing 16 may comprise a recess 40 in which the second rotor 34 is at least partially accommodated. Again, in some embodiments, the second rotor 34 may be pivotable with respect to the rear wing 14 and/or the recess 40 for better controlling the thrust generated from the rotor with respect to the aircraft 1.
By allowing each propulsion unit 30, and/or the first and second rotors 32;34, to pivot with respect to the rest of the aircraft 1, this serves to better allow the aircraft 1 to be used as a VTOL (vertical take-off and landing) aircraft.
In some embodiments, such as those shown in Figures 1 and 2, to help control and direct the thrust generated from the first and second rotors 32;34 of each wing section, the first rotor 32 may be located nearer the first end 17 of the front wing 14 than it is to the second end 18 of the front wing 14, and/or with the second rotor 34 located nearer the first end 20 of the rear wing than it is to the second end 22 of the rear wing 16.
In additional embodiments to help control and direct the thrust generated from the first and second rotors 32;34, in such embodiments the second rotor 34 may be located above the first rotor 32 in the height direction H of the aircraft 1. In the particular embodiments of aircraft 1 shown in Figure 1 and 2, the second rotor 34 is located above the first rotor 32 in the height direction H of the aircraft 1, yet behind the first rotor 32 in a length direction L of the aircraft 1.
Particularly in embodiments where the aircraft is a manned aircraft, the main body 10 of the aircraft 1 may comprise a canopy 42 enclosing a cockpit 44 of the aircraft 1. The cockpit 44 in some embodiments may be configured such that the aircraft may be provided as a single-seat aircraft, as is shown in the embodiment aircraft 1 from Figures 1 and 2.
In embodiments where the canopy 42 is present, to reduce the chance of injury to an occupant of the aircraft from each propulsion unit 30, the propulsion unit 30; first rotor 32; and/or second rotor 34 of each wing section 12 may in some embodiments be located beneath the canopy 42 in a height direction H of the aircraft 1. In some embodiments, the second rotor 34 may be at least partially located behind the canopy 42 in a length direction L of the aircraft 1.
In terms of the powering and control of the aircraft 1, it will be appreciated that the necessary electronics, power source, mechanical and electrical controls and connections may be distributed throughout the aircraft 1 as required. In cases where the aircraft is an unmanned aerial vehicle, the aircraft 1 would also then as required comprises the necessary communication means for it to be operated by a user from a location remote from the aircraft.
Thus, from one perspective, there has now been an aircraft comprising: a main body; a pair of wing sections, each wing section comprising a front wing and a rear wing, wherein the front wing and the rear wing each comprise a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing; wherein the main body is located between the pair of wing sections, and each wing section comprises a propulsion unit located between the front wing and the rear wing of the wing section. The provision of the pair of wing sections whose front and rear wings each have a second end that are connected to each other, where the propulsion unit is located between these front and rear wings provides an aerodynamic arrangement that, although not exclusively, is particularly suited for use in smaller aircraft and also VTOL (vertical take-off and landing) aircraft.
In order to address various issues and advance the art, this disclosure shows by way of illustration various embodiments in which the claimed invention(s) may be practiced. The advantages and features of the disclosure are of a representative sample of embodiments only, and are not exhaustive and/or exclusive. They are presented only to assist in understanding and to teach the claimed invention(s). It is to be understood that advantages, embodiments, examples, functions, features, structures, and/or other aspects of the disclosure are not to be considered limitations on the disclosure as defined by the claims or limitations on equivalents to the claims, and that other embodiments may be utilised and modifications may be made without departing from the scope of the claims. Various embodiments may suitably comprise, consist of, or consist essentially of, various combinations of the disclosed elements, components, features, parts, steps, means, etc. other than those specifically described herein, and it will thus be appreciated that features of the dependent claims may be combined with features of the independent claims in combinations other than those explicitly set out in the claims. The disclosure may include other inventions not presently claimed, but which may be claimed in future.
It will be appreciated that while the above description has focused on some specific aircraft configurations comprising a number of different features, aircraft in accordance with other embodiments of the disclosure may not include all these features. For example, the aircraft shown in the Figures are shown as comprising a cockpit for a pilot that is enclosed by a canopy. However, in some embodiments the aircraft may be operated without such a canopy/cockpit and instead take the form of an unmanned aerial vehicle, which may for instance then have communication means for being operated by a user from a location remote from the aircraft.
Consistorv Set of Clauses 1. An aircraft comprising: a main body; a pair of wing sections, each wing section comprising a front wing and a rear wing, wherein the front wing and the rear wing each comprise a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing; wherein the main body is located between the pair of wing sections, and each wing section comprises a propulsion unit located between the front wing and the rear wing of the wing section.
2. An aircraft according to clause 1, wherein each propulsion unit comprises a first rotor and a second rotor.
3. An aircraft according to clause 2, wherein the first rotor is connected to the front wing.
4. An aircraft according to clause 2 or 3, wherein the front wing comprises a recess in which the first rotor is at least partially accommodated.
5. An aircraft according to any of clauses 2-4, wherein the first rotor is located nearer the first end of the front wing than it is to the second end of the front wing.
6. An aircraft according to any of clauses 2-5, wherein the first rotor is connected to the main body.
7. An aircraft according to any of clauses 2-6, wherein the second rotor is connected to the rear wing.
8. An aircraft according to any of clauses 2-7, wherein the rear wing comprises a recess in which the second rotor is at least partially accommodated.
9. An aircraft according to any of clauses 2-8, wherein the second rotor is located nearer the first end of the rear wing than it is to the second end of the rear wing.
10. An aircraft according to any preceding clause, wherein the rear wing is located above the front wing in a height direction of the aircraft.
11. An aircraft according to any of clauses 2-10, wherein the second rotor is located above the first rotor.
12. An aircraft according to any preceding clause, wherein the rear wing comprises a rear edge, wherein starting from the second end of the rear wing in a direction towards the first end of the rear wing, the rear edge of the rear wing extends in a direction away from the front 10 wing.
13. An aircraft according to any of clauses 2-12, wherein the main body comprises a canopy enclosing a cockpit of the aircraft, wherein at least one of the rotors is located beneath the canopy in a height direction of the aircraft.
14. An aircraft according to clause 13, wherein each first rotor is located beneath the canopy in a height direction of the aircraft.
15. An aircraft according to clause 13 or 14, wherein each second rotor is located beneath the canopy in a height direction of the aircraft.
16. An aircraft according to any preceding clause, wherein the aircraft is a single-seat aircraft.
17. An aircraft according to any of clauses 1-15, wherein the aircraft is an unmanned aerial vehicle.
18. An aircraft according to any preceding clause, wherein the aircraft is a VTOL (vertical take-off and landing) aircraft.

Claims (20)

  1. Claims 1. A VTOL (vertical take-off and landing) aircraft comprising: a main body; a pair of wing sections, each wing section comprising a front wing and a rear wing, wherein the front wing and the rear wing each comprise a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing; wherein the main body is located between the pair of wing sections, and each wing section comprises a pivotable propulsion unit located between the front wing and the rear wing of the wing section; wherein each wing section forms a loop that is connected to the main body in at least two locations; and wherein the rear wing comprises a rear edge, wherein starting from the second end of the rear wing in a direction towards the first end of the rear wing, the rear edge of the rear wing extends in a direction away from the front wing.
  2. 2. An aircraft according to claim 1, wherein each loop is connected to the main body at the first end of the front wing and at the first end of the rear wing.
  3. 3. An aircraft according to any preceding claim, wherein the aircraft does not comprise a tail fin
  4. 4. An aircraft according to any preceding claim, wherein the aircraft does not comprise a tail rotor.
  5. 5. An aircraft according to any preceding claim, wherein each propulsion unit comprises a first rotor and a second rotor.
  6. An aircraft according to claim 5, wherein the first rotor is connected to the front wing.
  7. 7. An aircraft according to claim 5 or 6, wherein the front wing comprises a recess in which the first rotor is at least partially accommodated.
  8. 8. An aircraft according to any of claims 5-7, wherein the first rotor is located nearer the first end of the front wing than it is to the second end of the front wing.
  9. 9. An aircraft according to any of claims 5-8, wherein the first rotor is connected to the main body.
  10. 10. An aircraft according to any of claims 5-9, wherein the second rotor is connected to the rear wing.
  11. 11. An aircraft according to any of claims 5-10, wherein the rear wing comprises a recess in which the second rotor is at least partially accommodated.
  12. 12. An aircraft according to any of claims 5-11, wherein the second rotor is located nearer the first end of the rear wing than it is to the second end of the rear wing.
  13. 13. An aircraft according to any of claims 5-12, wherein the second rotor is located above the first rotor.
  14. 14. An aircraft according to any preceding claim, wherein the rear wing is located above the front wing in a height direction of the aircraft.
  15. 15. An aircraft according to any preceding claim, wherein the main body comprises a canopy enclosing a cockpit of the aircraft.
  16. 16. An aircraft according to claim 15, when further dependent on claim 5 at least, wherein at least one of the rotors is located beneath the canopy in a height direction of the aircraft.
  17. 17. An aircraft according to claim 16, wherein each first rotor is located beneath the canopy in a height direction of the aircraft.
  18. 18. An aircraft according to claim 16 or 17, wherein each second rotor is located beneath the canopy in a height direction of the aircraft.
  19. 19. An aircraft according to any preceding claim, wherein the aircraft is a single-seat aircraft.
  20. 20. An aircraft according to any of claims 1-18, wherein the aircraft is an unmanned aerial vehicle.
GB2203125.6A 2019-07-18 2019-07-18 An aircraft Active GB2601453B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2203125.6A GB2601453B (en) 2019-07-18 2019-07-18 An aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1910278.9A GB2585864B (en) 2019-07-18 2019-07-18 An aircraft
GB2203125.6A GB2601453B (en) 2019-07-18 2019-07-18 An aircraft

Publications (3)

Publication Number Publication Date
GB202203125D0 GB202203125D0 (en) 2022-04-20
GB2601453A true GB2601453A (en) 2022-06-01
GB2601453B GB2601453B (en) 2023-05-03

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ID=81456303

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2203125.6A Active GB2601453B (en) 2019-07-18 2019-07-18 An aircraft

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GB (1) GB2601453B (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015019255A1 (en) * 2013-08-08 2015-02-12 Bottoni Claudio Boxwing aircraft
CN108408043A (en) * 2018-03-02 2018-08-17 北京航空航天大学 A kind of boxlike verts rotor aircraft
NL2018278B1 (en) * 2017-02-01 2018-08-22 Avy Tech B V Vertical Take-Off and Landing Unmanned Aerial Vehicle (VTOL UAV)
WO2019056052A1 (en) * 2017-09-22 2019-03-28 AMSL Innovations Pty Ltd Wing tilt actuation system for electric vertical take-off and landing (vtol) aircraft
CN109733603A (en) * 2019-02-27 2019-05-10 西北工业大学 A kind of boxlike solar energy unmanned plane
EP3483064A1 (en) * 2017-11-13 2019-05-15 Bell Helicopter Textron Inc. Segmented duct for tilting proprotors
WO2019202325A1 (en) * 2018-04-17 2019-10-24 Flugauto Holding Limited Vertical take-off and landing vehicle

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015019255A1 (en) * 2013-08-08 2015-02-12 Bottoni Claudio Boxwing aircraft
NL2018278B1 (en) * 2017-02-01 2018-08-22 Avy Tech B V Vertical Take-Off and Landing Unmanned Aerial Vehicle (VTOL UAV)
WO2019056052A1 (en) * 2017-09-22 2019-03-28 AMSL Innovations Pty Ltd Wing tilt actuation system for electric vertical take-off and landing (vtol) aircraft
EP3483064A1 (en) * 2017-11-13 2019-05-15 Bell Helicopter Textron Inc. Segmented duct for tilting proprotors
CN108408043A (en) * 2018-03-02 2018-08-17 北京航空航天大学 A kind of boxlike verts rotor aircraft
WO2019202325A1 (en) * 2018-04-17 2019-10-24 Flugauto Holding Limited Vertical take-off and landing vehicle
CN109733603A (en) * 2019-02-27 2019-05-10 西北工业大学 A kind of boxlike solar energy unmanned plane

Also Published As

Publication number Publication date
GB202203125D0 (en) 2022-04-20
GB2601453B (en) 2023-05-03

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