CA2958445A1 - Multipoint dual-axis tiltrotor aircraft - Google Patents
Multipoint dual-axis tiltrotor aircraft Download PDFInfo
- Publication number
- CA2958445A1 CA2958445A1 CA2958445A CA2958445A CA2958445A1 CA 2958445 A1 CA2958445 A1 CA 2958445A1 CA 2958445 A CA2958445 A CA 2958445A CA 2958445 A CA2958445 A CA 2958445A CA 2958445 A1 CA2958445 A1 CA 2958445A1
- Authority
- CA
- Canada
- Prior art keywords
- aircraft
- frame
- multipoint
- dual
- axis
- 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.)
- Abandoned
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
An aircraft includes a frame, an energy source carried by to the frame, a controller, and a plurality of gimballing motor mount propulsion devices attached to the frame and controlled by the controller to maintain a substantially horizontal attitude of the aircraft during flight.
Description
Multipoint Dual-Axis Tiltrotor Aircraft Field :
[0001] This invention relates to aircraft.
:
:
Background
[0001] This invention relates to aircraft.
:
:
Background
[0002] Conventional multi-rotor helicopters or similar aircraft require.extensive rd,T
training to operate. The pilot or operator needs to be aware of basic aircraft position and movement, as well as other critical factors such as pitch, yaw, and roll.
[00031 The concepts of pitch, yaw, and roll contribute greatly to the complexity of flying an aircraft. This complexity is amplified when the pilot is onboard the aircraft and subject to the unintuitive character and dynamic forces of pitch, yaw, and roll.
This problem is one of the main reasons, if not the single most important reason, why personal aircraft have not yet become mainstream.
[0004] These and other problems exist in known aircraft.
Summary -[0005] According to one aspect of the invention, an aircraft includes a frame, an , energy source carried by to the frame, a controller, and a plurality of gimballing motor mount propulsion devices attached to the frame and controlled by the e ' controller to maintain a substantially horizontal attitude of the aircraft during flight.
Brief Description of the Drawings [0006] The drawings illustrate, by way of example only, embodiments of the ,16 , present invention.
[0007] FIG. 1 is a perspective view of an aircraft according to the present invention.
[0008] FIG. 2 is a top view of the aircraft.
[0009] FIG. 3 is a front view of the aircraft.
,f [0010] FIG. 4 is a side view of the aircraft.
[0011] FIG, 5 is a top view of a rotor of the aircraft.
A
:
Detailed Description [0012] The present invention aims to solve or mitigate at least one of the problems described above. A multipoint, dual axistiltrotor aircraft according to the present invention has the unique aeronautical utility of having the entire vehicle and payload remain substantially horizontal while maneuvering in the three-dimensional A
airspace. Known airplanes and helicopters cannot do this. In conventional aircraft, vehicle and payload must pitch and roll to maneuver. Such aircraft achieve this with the use of Mechanical control surfaces, namely, aileron, elevator, rudders cyclic and collective input devices. As a result, conventional aircraft do not remain horizontal white maneuvering.
r [0013] The multipoint, dual axis tiltrotor aircraft 1 according to the present invention enables the vehicle and payload 8 to remain substantially horizontal and :
move linearly along all three axes (x, y, z). The aircraft includes a frame 2 and an array, in this example four, internally actuated gimballing motor mount propulsion devices 3.
[0014] Each propulsion device 3 is oriented vertically to provide direct upward thrust and controllably gimballed to tilt laterally to provide a lateral thrust , component. In some embodiments, each propulsion device 3 is gimbatled about two perpendicular axes so that the lateral thrust component can be provided in any direction.
[0015] The propulsion devices 3 are set to the four corners of the vehicle 1 within the confines of the frame 2. The rotor discs 4 are controlled to move (e.g., tilt) in desired combinations (forward, back, starboard, port, up, down), while having the ' overall computer thrust governing equipment 5 (e.g., an onboard controller) request the vehicle 1 remain horizontal, or as near to horizontal as possible, at all times. This is achieved by means of a software device 6a that performs variable throttle , 41!
=-=
:
management as informed by a sensor feedback loop algorithm. An energy storage or conversion system 7, which can include a rechargeable battery, is provided to power the aircraft 1. As a result, changes in horizontal attitude are not induced.
This is a novel capability and design.
[00161 White the foregoing provides certain non-limiting examples, it should be "
. g understood that combinations, subsets, and variations of the foregoing are.
contemplated.
. q contemplated. The monopoly sought is defined by the claims.
=
. , 2.: 1 , ¨A
... ' -'. 1 . .., 7 ',.
4 ' ;., ..:,.;.1 ....,:i , .
. i . .s.;.0 't4 ! 3 , ..... , , ' 1:-....=:.!
training to operate. The pilot or operator needs to be aware of basic aircraft position and movement, as well as other critical factors such as pitch, yaw, and roll.
[00031 The concepts of pitch, yaw, and roll contribute greatly to the complexity of flying an aircraft. This complexity is amplified when the pilot is onboard the aircraft and subject to the unintuitive character and dynamic forces of pitch, yaw, and roll.
This problem is one of the main reasons, if not the single most important reason, why personal aircraft have not yet become mainstream.
[0004] These and other problems exist in known aircraft.
Summary -[0005] According to one aspect of the invention, an aircraft includes a frame, an , energy source carried by to the frame, a controller, and a plurality of gimballing motor mount propulsion devices attached to the frame and controlled by the e ' controller to maintain a substantially horizontal attitude of the aircraft during flight.
Brief Description of the Drawings [0006] The drawings illustrate, by way of example only, embodiments of the ,16 , present invention.
[0007] FIG. 1 is a perspective view of an aircraft according to the present invention.
[0008] FIG. 2 is a top view of the aircraft.
[0009] FIG. 3 is a front view of the aircraft.
,f [0010] FIG. 4 is a side view of the aircraft.
[0011] FIG, 5 is a top view of a rotor of the aircraft.
A
:
Detailed Description [0012] The present invention aims to solve or mitigate at least one of the problems described above. A multipoint, dual axistiltrotor aircraft according to the present invention has the unique aeronautical utility of having the entire vehicle and payload remain substantially horizontal while maneuvering in the three-dimensional A
airspace. Known airplanes and helicopters cannot do this. In conventional aircraft, vehicle and payload must pitch and roll to maneuver. Such aircraft achieve this with the use of Mechanical control surfaces, namely, aileron, elevator, rudders cyclic and collective input devices. As a result, conventional aircraft do not remain horizontal white maneuvering.
r [0013] The multipoint, dual axis tiltrotor aircraft 1 according to the present invention enables the vehicle and payload 8 to remain substantially horizontal and :
move linearly along all three axes (x, y, z). The aircraft includes a frame 2 and an array, in this example four, internally actuated gimballing motor mount propulsion devices 3.
[0014] Each propulsion device 3 is oriented vertically to provide direct upward thrust and controllably gimballed to tilt laterally to provide a lateral thrust , component. In some embodiments, each propulsion device 3 is gimbatled about two perpendicular axes so that the lateral thrust component can be provided in any direction.
[0015] The propulsion devices 3 are set to the four corners of the vehicle 1 within the confines of the frame 2. The rotor discs 4 are controlled to move (e.g., tilt) in desired combinations (forward, back, starboard, port, up, down), while having the ' overall computer thrust governing equipment 5 (e.g., an onboard controller) request the vehicle 1 remain horizontal, or as near to horizontal as possible, at all times. This is achieved by means of a software device 6a that performs variable throttle , 41!
=-=
:
management as informed by a sensor feedback loop algorithm. An energy storage or conversion system 7, which can include a rechargeable battery, is provided to power the aircraft 1. As a result, changes in horizontal attitude are not induced.
This is a novel capability and design.
[00161 White the foregoing provides certain non-limiting examples, it should be "
. g understood that combinations, subsets, and variations of the foregoing are.
contemplated.
. q contemplated. The monopoly sought is defined by the claims.
=
. , 2.: 1 , ¨A
... ' -'. 1 . .., 7 ',.
4 ' ;., ..:,.;.1 ....,:i , .
. i . .s.;.0 't4 ! 3 , ..... , , ' 1:-....=:.!
Claims
1. An aircraft comprising a frame, an energy source carried by to the frame, a controller, and a plurality of gimballing motor mount propulsion devices attached to the frame and controlled by the controller to maintain a substantially horizontal attitude of the aircraft during flight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA2958445A CA2958445A1 (en) | 2017-02-17 | 2017-02-17 | Multipoint dual-axis tiltrotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA2958445A CA2958445A1 (en) | 2017-02-17 | 2017-02-17 | Multipoint dual-axis tiltrotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2958445A1 true CA2958445A1 (en) | 2018-08-17 |
Family
ID=63166000
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2958445A Abandoned CA2958445A1 (en) | 2017-02-17 | 2017-02-17 | Multipoint dual-axis tiltrotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2958445A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112744354A (en) * | 2021-02-07 | 2021-05-04 | 之江实验室 | Flight mode control method of distributed tilting multi-rotor aircraft |
-
2017
- 2017-02-17 CA CA2958445A patent/CA2958445A1/en not_active Abandoned
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112744354A (en) * | 2021-02-07 | 2021-05-04 | 之江实验室 | Flight mode control method of distributed tilting multi-rotor aircraft |
| CN112744354B (en) * | 2021-02-07 | 2022-11-18 | 之江实验室 | Flight mode control method of distributed tilting multi-rotor aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Dead |
Effective date: 20200218 |