CN106494608A - Many shrouded propeller variable geometry Electric aircrafts - Google Patents
Many shrouded propeller variable geometry Electric aircrafts Download PDFInfo
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- CN106494608A CN106494608A CN201510555617.4A CN201510555617A CN106494608A CN 106494608 A CN106494608 A CN 106494608A CN 201510555617 A CN201510555617 A CN 201510555617A CN 106494608 A CN106494608 A CN 106494608A
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- tilting type
- shrouded propeller
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 4
- 229910052744 lithium Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
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Abstract
A kind of many shrouded propeller variable geometry Electric aircrafts, category air material field.Lifting and when parking, wing and tailplane foldable with body on, after lift-off, wing and tailplane are opened, less than on wing, the horizontal plane of tailplane before and after multiple shrouded propellers for verting are symmetrically distributed in wing and in the body left and right sides.Using above-mentioned layout, the machine can VTOL, again can quick flat fly, VTOL and reduce floor space when parking, when flat winged, increased speed and airborne period.Landing process safety reliability, flight attitude are steady.Piloted vehicle can be made, may be made as unmanned plane.
Description
Technical field
The present invention relates to a kind of band wing, tailplane, the electricity that vertical tail and multiple shrouded propellers are constituted
Dynamic aircraft, category air material field.
Background technology
At present, known helicopter or multi-rotor unmanned aerial vehicle are all to complete to take off vertically by rotary wings, hovering
With horizontal flight, due to the presence of rotor, in small space landing, no matter to the pedestrian of surrounding or
Itself all has certain danger.Chinese patent literature application number：200420063679.0, title：Vertical
The double four spout individual lift devices of duct of row and application number：200920053565.0, title：Double ducts can be vertical
Landing hovercar etc. also provides the scheme of some duct aircraft, but the former is fixed-wing, takes off vertically
Big with floor space when parking；, without wing, power consumption is big, and airborne period is short for the latter, and during horizontal flight
Speed is slow, furthermore produces vertical lift using two shrouded propellers, and safety is also poor, especially inorganic
Wing person, in the air, once there is a shrouded propeller to break down, consequence is hardly imaginable.
Content of the invention
In order to overcome prior art floor space big, power consumption, and the deficiency of poor stability, the invention provides
A kind of Electric aircraft scheme constituted with multiple tilting type shrouded propellers and variable geometry so that flight
During device VTOL, floor space is little, and energy-conservation during horizontal flight, airborne period are long, and during high-speed flight, resistance is little,
Flight attitude is stable, and landing is safe and reliable.
The technical solution adopted for the present invention to solve the technical problems is：Design one kind is by fuselage (8), wing
(3) what, tailplane (4), vertical tail (5), tilting type shrouded propeller (1), (2) were constituted is more
Shrouded propeller variable geometry Electric aircraft, its wing (3), tailplane (4) root are respectively provided with one
The rotating mechanism being connected with fuselage (8), rotating mechanism can be detected the reducing motor of rotary position information by band
(14) steering wheel (19) for or by wing rotating shaft (17), connecting rod (12), rocking arm (13), control wing rotating
Mechanism's composition of composition, the wing tip that can control wing (3) are rotated to the rear portion of fuselage (8), while control
Front portion rotation of the wing tip of tailplane (4) to fuselage (8), mounted on top is on fuselage (8)；Multiple
Before tilting type shrouded propeller (1) is symmetrically distributed in wing (3) or after tailplane (4), another
A bit multiple tilting type shrouded propeller (2) be symmetrically distributed in fuselage (8) left and right sides less than wing (3) and
On the horizontal plane of tailplane (4)；Tilting type shrouded propeller (1), the tiliting axis (7) of (2) are through shaking
Arm (13), connecting rod (12) are connected with steering wheel (11), can control tilting type shrouded propeller (1), (2)
Rotate to 90 degree around tiliting axis (7), the control signal of steering wheel (11), the position of reducing motor (14)
The control signal of the input or steering wheel (19) of signal and control signal is connected respectively to flight controller (20)
Corresponding input, output port.
The invention has the beneficial effects as follows：After the folding of wing and tailplane, aircraft can be risen narrow space is vertical
Drop and park, after lift-off, wing and tailplane are opened, and can be glided using wing during horizontal flight, are saved
Electric energy, extends airborne period, and during high-speed flight, wing, tailplane sweepback reduce air drag. by
Be made up of motor and battery in dynamical system, pollution-free, noise is also little, be easy to automatically control with wireless electric-controlled
System and regular maintenance, safe and reliable during landing, flight attitude is stable, even if there is indivedual shrouded propellers to occur
Failure, also can safe vertical landing or dead-stick landing by remaining shrouded propeller and wing aircraft.
The present invention can be made into manned vehicle, used as civilian traffic instrument；May be made as unmanned plane. with reality
Now take photo by plane, investigate and all kinds of civilian and militaries in terms of purposes.
Description of the drawings
The present invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 be the present invention using 6 tilting type shrouded propellers type, two of which of verting tilting type
Shrouded propeller carries out the shaft side figure of horizontal flight.
The 1. tilting type shrouded propeller before wing or after tailplane in figure, is 2. located at fuselage both sides
Tilting type shrouded propeller, 3. wing, 4. tailplane, 5. vertical tail, 7. tilting type contain
Road propeller tiliting axis, 8. body, 10. underpart.
Fig. 2 is axle of the present invention using the type VTOL of 6 tilting type shrouded propellers or when parking
Side figure.
The 1. tilting type shrouded propeller before wing or after tailplane in figure, is 2. located at fuselage both sides
Tilting type shrouded propeller, 3. wing, 4. tailplane, 8. body.
Fig. 3 be the present invention using 6 tilting type shrouded propellers type, 6 tilting type shrouded propellers
All verting carries out the shaft side figure of horizontal flight.
In figure, 2. are located at the tilting type shrouded propeller of fuselage both sides.
Fig. 4 be the present invention using 4 tilting type shrouded propellers type, two of which of verting tilting type
Shrouded propeller carries out the shaft side figure of horizontal flight.
In figure, 1. are located at the tilting type shrouded propeller before wing, are 2. located at the tilting type duct of fuselage both sides
Propeller, 3. wing, 4. tailplane, 5. vertical tail, 6. dynamic lithium battery group, 7. inclines
Rotatable shrouded propeller tiliting axis, 8. body.
Fig. 5 is axle of the present invention using the type VTOL of 4 tilting type shrouded propellers or when parking
Side figure.
In figure, 2. are located at the tilting type shrouded propeller of fuselage both sides.
Fig. 6 be the present invention using 4 tilting type shrouded propellers type, 4 tilting type shrouded propellers
All verting carries out the shaft side figure of horizontal flight.
In figure, 1. are located at the tilting type shrouded propeller before wing, are 2. located at the tilting type duct of fuselage both sides
Propeller, 3. wing, 4. tailplane, 5. vertical tail, 6. dynamic lithium battery group, 7. inclines
Rotatable shrouded propeller tiliting axis,
Fig. 7 is the structure chart of wing of the present invention or tailplane and reducing motor connection.
3. wings or tailplane in figure, 14. reducing motors, 18. connection wings or tailplane and wing
The fixedly connected part of rotating shaft.
Fig. 8 is the schematic diagram of reducing motor of the present invention and position detecting device.
14. reducing motor in figure, 15. slot optical couplings, 16. brake sacks, 17. wing rotating shafts.
Fig. 9 is the structure chart of wing of the present invention or tailplane and control steering wheel.
3. wing in figure, 12. connecting rods, 13. rocking arms, 17. wing rotating shafts, 19. control wing rotations
Steering wheel.
Figure 10 is the structure chart of tilting type shrouded propeller of the present invention and control steering wheel.
1. tilting type shrouded propeller in figure, 7. tilting type shrouded propeller tiliting axis, 11. control flaps
Machine, 12. connecting rods, 13. rocking arms.
Figure 11 is the circuit connection block diagram of flight controller of the present invention and associated control element.
6. dynamic lithium battery group in figure, 11. tilting duct propeller steering wheels, 14. reducing motors, 19. can
Become wing steering wheel, 20. flight controllers, 21. wireless remotecontrol command receivers, 22. pilot steerings are grasped
Vertical mechanism, 23. lifting steering wheels, 24. direction steering wheels, 25. aileron steering wheels, 26. electricity adjust, 27. duct spirals
Oar motor.
Specific embodiment
As shown in Figure 1, Figure 2, Fig. 4, Fig. 6, wing (3) and tailplane (4) root are respectively connected with one
Rotating mechanism, the mechanism can be made up of the reducing motor with test position information (14), see Fig. 7 and Fig. 8；
Can also be made up of wing rotating shaft (17), rocking arm (13), connecting rod (12), steering wheel (19), referring to Fig. 9；
Rotating mechanism one end is fixedly connected with wing (3) or tailplane (4), and the other end is fixed on fuselage or machine
On body skeleton (8).Drive reducing motor (14) or the steering wheel (19) of control wing rotation make expansion
The wing tip of wing (3) is to fuselage afterbody rotary folding；Or the wing (3) of folding is rotated round about
Launch, or stop certain angle between.Connect the reducing motor (14) of tailplane (4) in the same manner
Or the steering wheel (19) of control wing rotation can be such that the wing tip of the tailplane (3) of expansion revolves to fore-body
Turnover is folded, or the tailplane (4) for making to have folded rotary expansion round about, or stops between
Certain angle.After folding wing (3) and tailplane (4) can mounted on top on fuselage (8), ginseng
See Fig. 2, Fig. 6.Every airfoil root connects the rudder of a reducing motor (14) or a control wing rotation
Machine (19), referring to Fig. 7, Fig. 8, Fig. 9.Fig. 8 is constituted using two optocouplers (15) and brake sack (16)
Rotary position information detection means, two optocouplers (15) output termination flight controller (20).Fig. 1,
Fig. 2 is the type constituted using 6 tilting type shrouded propellers, two of which tilting type shrouded propeller (1)
It is symmetrically distributed in wing (3) before and tailplane (4) is higher than machine on the horizontal plane of body center of gravity afterwards
After the span is opened, during horizontal flight, two tilting type shrouded propellers (1) are rotated by 90 °, and produce forward
Pulling force or thrust；To further increase pulling force forward or thrust, can by two of fuselage (8) both sides or
Four tilting type shrouded propellers (2) are also rotated by 90 °, referring to Fig. 3.Four of fuselage (8) both sides incline
Rotatable shrouded propeller is symmetrically distributed in the left and right sides of fuselage (8) less than wing (3) and tailplane (4)
Horizontal plane on, when taking off vertically, provide the pulling force for taking off vertically with tilting type shrouded propeller (1) together,
Referring to Fig. 2；Tilting type shrouded propeller (1), the tiliting axis (7) of (2) pass through rocking arm (13), connecting rod (12)
It is connected with steering wheel (11), can pivot 90 degree of pulling force or thrust to provide aircraft horizontal flight.
Fig. 4, Fig. 5 and Fig. 6 are the types that the present invention is constituted using 4 tilting type shrouded propellers, and two of which is inclined
Before rotatable shrouded propeller (1) is symmetrically distributed in wing (3), two other is distributed in tailplane (4)
Before higher than on the horizontal plane of body center of gravity, 4 tilting type shrouded propellers are placed in less than wing and level
In tail plane.After wing launches, during horizontal flight, two tilting type shrouded propeller (1) rotations 90
Degree, produces pulling force forward, referring to Fig. 4；To further increase pulling force forward or thrust, can be by fuselage
(8) two tilting type shrouded propellers (2) of both sides are also rotated by 90 °, and see Fig. 5.Whether 6 are adopted
The type that individual or 4 tilting type shrouded propellers are constituted, each tilting type shrouded propeller (1), (2)
All connect a steering wheel (11)；The control signal circuit of steering wheel (11) is connected to flight controller (20)
I/O ports, can control each tilting type shrouded propeller (1), (2) respectively and vert；Each tilting type duct
Propeller (1), (2) all individually connect a motor (27), and they are individually connected to respective electricity and adjust
(26) on；Electricity adjusts the outfan and the I/O of flight controller (20) of (26) and dynamic lithium battery group (6)
Control end is connected, and can independently control the rotating speed of each motor (27), referring to Figure 11；Flight control
The commercially available finished product of device (20) processed using Open Source Code, its interface connect multiple electricity respectively and adjust (26).Manually drive
Bench board (22) is sailed for manned (unmanned type is not needed), driver's cabin is placed in.Pilot steering is grasped
Vertical platform (22) directly can be reequiped with radio remote controller, and its antenna is connected to after resistance decrement radio
The antenna end of receiver (21), and the signal ground of two machines is joined directly together.Flight controller (20)
I/O ports are also connected with the output circuit of wireless remotecontrol command receiver (21), and wireless remotecontrol instruction connects
Receipts machine (21) wireless remotecontrol command receiver transmitter can adopt the above model airplane remote control transmitting-receiving of commercially available 9 passage
Equipment, respectively control tilting type shrouded propeller (1), the verting of (2), wing (3), tailplane (4)
Rotation, tilting type shrouded propeller (1), (2) vert and rotating speed and lifting steering wheel (23), rudder
Machine (24), the swing of aileron steering wheel (25).During VTOL, flight controller (20) adjust 4 or
6 tilting type shrouded propellers (1), the rotating speeds of (2), keep stablizing for aircraft flight attitude；Level flies
During row, flight controller (20) adjusts lifting steering wheel (23), direction steering wheel (24), aileron steering wheel (25)
Angle, keep aircraft horizontal flight, climb, decline and course.
Claims (1)
1. one kind is by fuselage (8), wing (3), tailplane (4), vertical tail (5), tilting type duct spiral shell
Many shrouded propeller variable geometry Electric aircrafts that rotation oar (1), (2) are constituted, it is characterised in that：Wing
(3), tailplane (4) root is respectively provided with a rotating mechanism being connected with fuselage (8), rotating mechanism
Can by band detect rotary position information reducing motor (14) or by wing rotating shaft (17), connecting rod (12),
Mechanism's composition that rocking arm (13), the steering wheel (19) of control wing rotation are constituted, can control wing (3)
Wing tip is rotated to the rear portion of fuselage (8), while the wing tip of control tailplane (4) is to before fuselage (8)
Portion rotates, and mounted on top is on fuselage (8)；Multiple tilting type shrouded propeller (1) is symmetrically distributed in machine
Before the wing (3) or after tailplane (4), other multiple tilting type shrouded propeller (2) are symmetrically divided
On horizontal plane of the cloth in fuselage (8) left and right sides less than wing (3) and tailplane (4)；Tilting type is contained
Road propeller (1), the tiliting axis (7) of (2) are through rocking arm (13), connecting rod (12) and steering wheel (11) phase
Even, controllable tilting type shrouded propeller (1), (2) are rotated to 90 degree around tiliting axis (7), steering wheel (11)
Control signal, the position signalling of reducing motor (14) and control signal input or steering wheel (19)
Control signal is connected respectively to the corresponding input of flight controller (20), output port.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510555617.4A CN106494608A (en) | 2015-09-06 | 2015-09-06 | Many shrouded propeller variable geometry Electric aircrafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510555617.4A CN106494608A (en) | 2015-09-06 | 2015-09-06 | Many shrouded propeller variable geometry Electric aircrafts |
Publications (1)
| Publication Number | Publication Date |
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| CN106494608A true CN106494608A (en) | 2017-03-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510555617.4A Pending CN106494608A (en) | 2015-09-06 | 2015-09-06 | Many shrouded propeller variable geometry Electric aircrafts |
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| CN106828904A (en) * | 2017-04-07 | 2017-06-13 | 东莞市锦明运动器材有限公司 | Machine is maked an inspection tour in a kind of new-type unmanned delivery with gliding function |
| CN107458579A (en) * | 2017-08-01 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane device |
| CN107458601A (en) * | 2017-09-03 | 2017-12-12 | 佛山市龙远科技有限公司 | A kind of amphibious unmanned plane of the VTOL with auxiliary power |
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| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| US20110168834A1 (en) * | 2003-10-27 | 2011-07-14 | Urban Aeronautics Ltd. | Ducted fan vtol vehicles |
| CN102574575A (en) * | 2009-09-09 | 2012-07-11 | 威罗门飞行公司 | Elevon control system |
| CN102897317A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN103231805A (en) * | 2013-05-21 | 2013-08-07 | 吉林大学 | Duct type folding wing machine |
| CN103832585A (en) * | 2012-11-22 | 2014-06-04 | 上海市浦东新区知识产权保护协会 | Cruise aircraft |
| CN104071336A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Portable folding wing unmanned aerial vehicle |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
| US9085355B2 (en) * | 2012-12-07 | 2015-07-21 | Delorean Aerospace, Llc | Vertical takeoff and landing aircraft |
-
2015
- 2015-09-06 CN CN201510555617.4A patent/CN106494608A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110168834A1 (en) * | 2003-10-27 | 2011-07-14 | Urban Aeronautics Ltd. | Ducted fan vtol vehicles |
| CN200995782Y (en) * | 2007-01-17 | 2007-12-26 | 赵文志 | Airplane |
| CN102574575A (en) * | 2009-09-09 | 2012-07-11 | 威罗门飞行公司 | Elevon control system |
| CN102897317A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| CN103832585A (en) * | 2012-11-22 | 2014-06-04 | 上海市浦东新区知识产权保护协会 | Cruise aircraft |
| US9085355B2 (en) * | 2012-12-07 | 2015-07-21 | Delorean Aerospace, Llc | Vertical takeoff and landing aircraft |
| CN103043214A (en) * | 2012-12-19 | 2013-04-17 | 天津全华时代航天科技发展有限公司 | Folding type unmanned plane |
| CN103231805A (en) * | 2013-05-21 | 2013-08-07 | 吉林大学 | Duct type folding wing machine |
| CN104071336A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Portable folding wing unmanned aerial vehicle |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
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| CN108791876B (en) * | 2017-04-28 | 2022-01-07 | 北京领恩科技有限公司 | Aircraft capable of vertically taking off and landing |
| CN108791876A (en) * | 2017-04-28 | 2018-11-13 | 北京领恩科技有限公司 | It is a kind of can be with the aircraft of vertical and landing takeoff |
| US11634222B2 (en) | 2017-05-16 | 2023-04-25 | South China University Of Technology | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
| WO2018209911A1 (en) * | 2017-05-16 | 2018-11-22 | 华南理工大学 | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
| CN108995802A (en) * | 2017-06-07 | 2018-12-14 | 北京领恩科技有限公司 | A kind of modular propulsion system and can be with the aircraft of vertical and landing takeoff |
| CN108995802B (en) * | 2017-06-07 | 2022-01-07 | 北京领恩科技有限公司 | Modular propulsion system and aircraft capable of vertical takeoff and landing |
| US10745125B2 (en) | 2017-07-27 | 2020-08-18 | Tatsumi Ryoki Co., Ltd | Hovering vehicle |
| CN110891859A (en) * | 2017-07-27 | 2020-03-17 | 株式会社辰巳菱机 | Suspension type mobile device |
| CN110891859B (en) * | 2017-07-27 | 2023-03-10 | 株式会社辰巳菱机 | Suspension type mobile device |
| CN107458579A (en) * | 2017-08-01 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of unmanned plane device |
| US11584524B2 (en) | 2017-08-02 | 2023-02-21 | Gadfin Ltd. | Unmanned aerial vehicle |
| WO2019026079A1 (en) * | 2017-08-02 | 2019-02-07 | Gadfin Ltd. | An unmanned aerial vehicle |
| EP4043345A1 (en) * | 2017-08-02 | 2022-08-17 | Eyal Regev | An unmanned aerial vehicle |
| CN111295330A (en) * | 2017-08-02 | 2020-06-16 | 嘉德芬有限公司 | Unmanned aerial vehicle |
| EP3661846A4 (en) * | 2017-08-02 | 2021-08-11 | Eyal Regev | An unmanned aerial vehicle |
| CN107696811A (en) * | 2017-09-03 | 2018-02-16 | 佛山市龙远科技有限公司 | A kind of VTOL amphibious unmanned plane of more power |
| CN107458601A (en) * | 2017-09-03 | 2017-12-12 | 佛山市龙远科技有限公司 | A kind of amphibious unmanned plane of the VTOL with auxiliary power |
| CN107554778A (en) * | 2017-09-03 | 2018-01-09 | 佛山市海茂聚航科技有限公司 | A kind of land and water unmanned plane of VTOL |
| CN107554783A (en) * | 2017-09-03 | 2018-01-09 | 佛山市龙远科技有限公司 | A kind of amphibious unmanned plane of VTOL |
| CN107539470A (en) * | 2017-09-03 | 2018-01-05 | 佛山市龙远科技有限公司 | A kind of four oars amphibious unmanned plane of VTOL |
| WO2019052142A1 (en) * | 2017-09-12 | 2019-03-21 | 深圳光启合众科技有限公司 | Flying car |
| CN107972860A (en) * | 2017-12-03 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of stabilized flight device |
| CN108791874A (en) * | 2018-06-21 | 2018-11-13 | 南京航空航天大学 | A kind of tilting duct power unmanned vehicle |
| CN109159633A (en) * | 2018-08-31 | 2019-01-08 | 长春工程学院 | A kind of amphibious unmanned plane |
| CN109592007A (en) * | 2018-11-17 | 2019-04-09 | 成都奥克特科技有限公司 | Double mode unmanned plane working method and double mode unmanned plane |
| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
| CN112124569B (en) * | 2020-09-17 | 2022-04-01 | 西安电子科技大学 | Vertical take-off and landing and unmanned aerial vehicle stabilizing system based on launching canister |
| CN112124569A (en) * | 2020-09-17 | 2020-12-25 | 西安电子科技大学 | Vertical take-off and landing and unmanned aerial vehicle stabilizing system based on launching canister |
| CN112498679B (en) * | 2020-12-14 | 2022-10-28 | 江西洪都航空工业股份有限公司 | Tilting composite power aircraft |
| CN112498679A (en) * | 2020-12-14 | 2021-03-16 | 江西洪都航空工业股份有限公司 | Tilting composite power aircraft |
| CN112549885A (en) * | 2020-12-21 | 2021-03-26 | 中国科学院沈阳自动化研究所 | Folding wing submerged cross-domain marine robot capable of vertically taking off and landing |
| CN113002770A (en) * | 2021-03-29 | 2021-06-22 | 曾成刚 | Rotor craft capable of attaching wings to fuselage |
| CN113104195B (en) * | 2021-05-19 | 2022-03-11 | 涵涡智航科技(玉溪)有限公司 | Double-duct composite wing aircraft |
| CN113104195A (en) * | 2021-05-19 | 2021-07-13 | 涵涡智航科技(玉溪)有限公司 | Double-duct composite wing aircraft |
| CN113830300A (en) * | 2021-11-09 | 2021-12-24 | 北京航空航天大学 | General structure of duct type aircraft |
| CN114148506A (en) * | 2021-12-06 | 2022-03-08 | 浙江大学 | Foldable variant unmanned aerial vehicle and control method thereof |
| CN114148506B (en) * | 2021-12-06 | 2023-10-13 | 浙江大学 | Foldable variant unmanned aerial vehicle and control method thereof |
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