CN110683041A - Disc-shaped aircraft - Google Patents
Disc-shaped aircraft Download PDFInfo
- Publication number
- CN110683041A CN110683041A CN201911016374.1A CN201911016374A CN110683041A CN 110683041 A CN110683041 A CN 110683041A CN 201911016374 A CN201911016374 A CN 201911016374A CN 110683041 A CN110683041 A CN 110683041A
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- Prior art keywords
- wing
- group
- hollow
- wings
- pair
- 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
Links
- 238000004804 winding Methods 0.000 claims description 8
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
Classifications
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- 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
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
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- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to a disc-shaped aircraft, which comprises a hollow fuselage (1), a pair of inner stators (2), a pair of outer rotors (3) and wings, wherein the top of the hollow fuselage (1) is provided with a fairing (5), the bottom of the hollow fuselage (1) is provided with a base (7), the bottom of the base (7) is provided with a bin gate (8) communicated with the inside of the hollow fuselage (1), and the pair of outer rotors (3) are respectively provided with a helical blade (9) for generating downward airflow thrust, and the invention has the advantages that: the hollow aircraft body, the inner stator and the outer rotor form the outer rotor motor, the whole aircraft is a power mechanism, the structure is simple, the failure rate is low, energy consumption can be saved to the maximum extent, and the cruising ability is greatly improved.
Description
Technical Field
The invention relates to the technical field of glass production, in particular to a disc-shaped aircraft.
Background
At present, the vertical aircraft is more and more widely used, most of the vertical aircraft appearing on the market are multi-rotor aircraft, and the Chinese patent network application number 201620129102.8 discloses a disk aircraft capable of adjusting flight attitude, wherein a power mechanism of the disk aircraft comprises a group of engines, a group of upper gear boxes, a group of lower gear boxes, an upper propeller driving gear ring and a lower propeller driving gear ring, the disk aircraft is complex in structure, high in failure rate, large in energy loss in the working process and seriously influenced in cruising ability.
Disclosure of Invention
The present invention is directed to a dish-shaped aircraft.
The invention comprises a hollow machine body, a pair of inner stators, a pair of outer rotors and wings, wherein a fairing is arranged at the top of the hollow machine body, a base is arranged at the bottom of the hollow machine body, a bin gate communicated with the interior of the hollow machine body is arranged at the bottom of the base, a hollow machine body avoidance hole is formed in the middle of the inner stators, the pair of inner stators are respectively sleeved on the hollow machine body and are fastened through a screw, a group of stator windings are arranged on the inner stators, a group of permanent magnet yokes matched with the stator windings for use are arranged in the outer rotors, the pair of outer rotors are vertically and symmetrically arranged on the hollow machine body, the rotating directions of the upper outer rotor and the lower outer rotor are opposite, the outer rotors and the hollow machine body are movably connected through bearings, a;
the wings comprise a group of upper wings, a group of upper wing control hydraulic cylinders, a group of lower wings, a group of lower wing control hydraulic cylinders and wing connecting rings, the group of upper wings and the group of lower wings are respectively arranged on the hollow fuselage in an annular array mode, the wing connecting rings are arranged on the hollow fuselage through a group of supporting rods and are located between the upper wings and the lower wings, one ends of the upper wings and the lower wings are hinged with the hollow fuselage, the other ends of the upper wings and the lower wings are hinged with the wing connecting rings, and the group of upper wing control hydraulic cylinders and the group of lower wing control hydraulic cylinders are respectively arranged on the hollow fuselage in an annular array mode and drive the corresponding upper wings and the corresponding.
The propeller blade is provided with a connecting outer ring which is movably connected with the wing connecting ring through a bearing.
A group of hydraulic supporting legs is arranged on the base.
A cockpit is arranged in the fairing.
The upper wing, the lower wing and the wing connecting ring are connected through spherical joint bearings.
The invention has the advantages that: the hollow aircraft body, the inner stator and the outer rotor form the outer rotor motor, the whole aircraft is a power mechanism, the structure is simple, the failure rate is low, energy consumption can be saved to the maximum extent, and the cruising ability is greatly improved.
Drawings
FIG. 1 is a schematic diagram of the present invention.
Fig. 2 is a schematic view of the internal structure of the present invention.
Detailed Description
As shown in the attached drawing, the invention comprises a hollow fuselage 1, a pair of inner stators 2, a pair of outer rotors 3 and wings, wherein the top of the hollow fuselage 1 is provided with a fairing 5, the bottom of the hollow fuselage 1 is provided with a base 7, the bottom of the base 7 is provided with a bin gate 8 communicated with the inside of the hollow fuselage 1, the middle part of the inner stator 2 is provided with a hollow fuselage 1 avoidance hole, the pair of inner stators 2 are respectively sleeved on the hollow fuselage 1, the inner stator 2 is provided with a group of stator windings, the outer rotor 3 is internally provided with a group of permanent magnet yokes matched with the stator windings, the pair of outer rotors 3 are symmetrically arranged on the hollow machine body 1 from top to bottom, the rotating directions of the upper outer rotor 3 and the lower outer rotor 3 are opposite, the outer rotor 3 and the hollow machine body 1 are movably connected through a bearing, the pair of outer rotors 3 are respectively provided with a propeller blade 9 for generating downward airflow thrust, and the base 7 is internally provided with a battery assembly 10 for supplying power to the stator windings;
the wings comprise a group of upper wings 11, a group of upper wing control hydraulic cylinders 12, a group of lower wings 13, a group of lower wing control hydraulic cylinders 14 and wing connecting rings 15, the group of upper wings 11 and the group of lower wings 13 are respectively arranged on the hollow fuselage 1 in an annular array mode, the wing connecting rings 15 are installed on the hollow fuselage 1 through a group of supporting rods and are located between the upper wings 11 and the lower wings 13, one ends of the upper wings 11 and the lower wings 13 are hinged with the hollow fuselage 1, the other ends of the upper wings 11 and the lower wings 13 are hinged with the wing connecting rings 15, and the group of upper wing control hydraulic cylinders 12 and the group of lower wing control hydraulic cylinders 14 are respectively arranged on the hollow fuselage 1 in an annular array mode and drive the corresponding upper wings 11 and the corresponding lower.
The propeller blade 9 is provided with a connecting outer ring 17, and the connecting outer ring 17 is movably connected with the wing connecting ring 15 through a bearing.
A group of hydraulic support legs 16 are arranged on the base 7.
A cockpit is arranged in the fairing 5.
The upper wing 11, the lower wing 13 and the wing connecting ring 15 are connected through ball joint bearings.
The working mode and principle are as follows: the hollow aircraft body 1 is used as an engine room for storing articles, the pair of inner stators 2 and the pair of outer rotors 3 form two outer rotor motors, the two outer rotor motors rotate by taking the hollow aircraft body 1 as an axis, the rotation directions of the two outer rotor motors are opposite, the inclination directions of the upper and lower propeller blades 9 are opposite, downward airflow thrust is generated in the rotating process, the stability of the aircraft body can be effectively kept while the thrust is improved, the lifting of the aircraft is controlled by controlling the rotating speed of the two outer rotor motors, and the wings are used for adjusting the flying posture of the aircraft.
A group of upper wings 11 and a group of lower wings 13 are symmetrically distributed up and down and are connected through wing connecting rings 15 to form a cover body in a surrounding mode, an upper propeller blade 9 and a lower propeller blade 9 rotate in the cover body respectively, the number of the upper wings 11, the number of the lower wings 13, the number of the upper wing control hydraulic cylinders 12 and the number of the lower wing control hydraulic cylinders 14 are the same, one upper wing control hydraulic cylinder 12 is matched with one corresponding lower wing control hydraulic cylinder 14 for use, synchronous action is achieved, one upper wing 11 and one lower wing 13 which correspond up and down are controlled to swing synchronously, and the flying posture is adjusted by changing the inclination angles of the upper wings 11 and the lower wings.
The propeller blade 9 is provided with a connecting outer ring 17, the connecting outer ring 17 is movably connected with the wing connecting ring 15 through a bearing, the propeller blade 9 cannot deform in the vertical direction when rotating to generate thrust, and the whole propeller blade 9 rotates on a fixed track.
A group of hydraulic support legs 16 are used in taking off and landing, the hydraulic support legs 16 are folded in the flight process, the bin gate 8 is a hydraulic lifting gate, and steps are arranged on the inner side of the bin gate 8 and are convenient to lift up and down.
Claims (5)
1. A disc-shaped aircraft is characterized by comprising a hollow aircraft body (1), a pair of inner stators (2), a pair of outer rotors (3) and wings, wherein a fairing (5) is arranged at the top of the hollow aircraft body (1), a base (7) is arranged at the bottom of the hollow aircraft body (1), a bin gate (8) communicated with the interior of the hollow aircraft body (1) is arranged at the bottom of the base (7), a hollow aircraft body (1) avoidance hole is formed in the middle of the inner stator (2), the pair of inner stators (2) are respectively sleeved on the hollow aircraft body (1) and fastened through a screw rod, a group of stator windings are arranged on the inner stator (2), a group of permanent magnet yokes matched with the stator windings are arranged in the outer rotors (3), the pair of outer rotors (3) are vertically and symmetrically arranged on the hollow aircraft body (1), the rotating directions of the upper and lower outer rotors (3) are opposite, and the outer rotors (3), the pair of outer rotors (3) are respectively provided with a propeller blade (9) for generating downward airflow thrust, and a battery assembly (10) for supplying power to the stator winding is arranged in the base (7);
the wings comprise a group of upper wings (11), a group of upper wing control hydraulic cylinders (12), a group of lower wings (13), a group of lower wing control hydraulic cylinders (14) and wing connecting rings (15), the group of upper wings (11) and the group of lower wings (13) are respectively arranged on the hollow fuselage (1) in an annular array manner, the wing connecting rings (15) are arranged on the hollow fuselage (1) through a group of supporting rods, and the hydraulic control system is positioned between an upper wing (11) and a lower wing (13), one end of the upper wing (11) and one end of the lower wing (13) are hinged with the hollow fuselage (1), the other end of the upper wing (11) and the other end of the lower wing (13) are hinged with a wing connecting ring (15), and a group of upper wing control hydraulic cylinders (12) and a group of lower wing control hydraulic cylinders (14) are respectively arranged on the hollow fuselage (1) in an annular array mode and drive the corresponding upper wing (11) and the corresponding lower wing (13) to swing.
2. A saucer-shaped aircraft according to claim 1, characterized in that the propeller blades (9) are provided with a connection outer ring (17), and the connection outer ring (17) is movably connected to the wing connection ring (15) via a bearing.
3. A dish aircraft according to claim 1, characterized in that the base (7) is provided with a set of hydraulic legs (16).
4. A dish aircraft according to claim 1, characterized in that a cockpit is provided in the fairing (5).
5. The disc-shaped aircraft according to claim 1, characterized in that the upper wing (11), the lower wing (13) and the wing connection ring (15) are connected by ball joint bearings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911016374.1A CN110683041A (en) | 2019-10-24 | 2019-10-24 | Disc-shaped aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911016374.1A CN110683041A (en) | 2019-10-24 | 2019-10-24 | Disc-shaped aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110683041A true CN110683041A (en) | 2020-01-14 |
Family
ID=69114144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911016374.1A Pending CN110683041A (en) | 2019-10-24 | 2019-10-24 | Disc-shaped aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110683041A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928550A (en) * | 2021-11-26 | 2022-01-14 | 歌尔科技有限公司 | Aircraft with a flight control device |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6270038B1 (en) * | 1999-04-22 | 2001-08-07 | Sikorsky Aircraft Corporation | Unmanned aerial vehicle with counter-rotating ducted rotors and shrouded pusher-prop |
| CN101857087A (en) * | 2009-04-09 | 2010-10-13 | 史智勇 | Dual-rotor dish-shaped aircraft |
| CN202264885U (en) * | 2011-08-12 | 2012-06-06 | 柴贵景 | Dish-shaped aircraft |
| CN102602539A (en) * | 2012-04-06 | 2012-07-25 | 柴贵景 | Double spiral disc butterfly aircraft |
| CN103803078A (en) * | 2012-11-12 | 2014-05-21 | 余彦武 | Flying saucer type helicopter utilizing active airflow to generate lifting power |
| CN205366066U (en) * | 2016-03-01 | 2016-07-06 | 张红艳 | Jet dish form aircraft of adjustable flight gesture |
| CN105752330A (en) * | 2016-02-19 | 2016-07-13 | 张红艳 | Disk-like aircraft capable of adjusting flying attitude |
| WO2019059428A1 (en) * | 2017-09-20 | 2019-03-28 | 최현환 | Unmanned aerial device |
| CN211001822U (en) * | 2019-10-24 | 2020-07-14 | 张红艳 | Butterfly-shaped aircraft |
-
2019
- 2019-10-24 CN CN201911016374.1A patent/CN110683041A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6270038B1 (en) * | 1999-04-22 | 2001-08-07 | Sikorsky Aircraft Corporation | Unmanned aerial vehicle with counter-rotating ducted rotors and shrouded pusher-prop |
| CN101857087A (en) * | 2009-04-09 | 2010-10-13 | 史智勇 | Dual-rotor dish-shaped aircraft |
| CN202264885U (en) * | 2011-08-12 | 2012-06-06 | 柴贵景 | Dish-shaped aircraft |
| CN102602539A (en) * | 2012-04-06 | 2012-07-25 | 柴贵景 | Double spiral disc butterfly aircraft |
| CN103803078A (en) * | 2012-11-12 | 2014-05-21 | 余彦武 | Flying saucer type helicopter utilizing active airflow to generate lifting power |
| CN105752330A (en) * | 2016-02-19 | 2016-07-13 | 张红艳 | Disk-like aircraft capable of adjusting flying attitude |
| CN205366066U (en) * | 2016-03-01 | 2016-07-06 | 张红艳 | Jet dish form aircraft of adjustable flight gesture |
| WO2019059428A1 (en) * | 2017-09-20 | 2019-03-28 | 최현환 | Unmanned aerial device |
| CN211001822U (en) * | 2019-10-24 | 2020-07-14 | 张红艳 | Butterfly-shaped aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928550A (en) * | 2021-11-26 | 2022-01-14 | 歌尔科技有限公司 | Aircraft with a flight control device |
| CN113928550B (en) * | 2021-11-26 | 2023-11-14 | 歌尔科技有限公司 | Aircraft with a plurality of aircraft body |
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