CN108454844A - The combined wing aircraft of the compound auxiliary wing of twin screw thrust with solar energy additional fin - Google Patents
The combined wing aircraft of the compound auxiliary wing of twin screw thrust with solar energy additional fin Download PDFInfo
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- CN108454844A CN108454844A CN201810552374.2A CN201810552374A CN108454844A CN 108454844 A CN108454844 A CN 108454844A CN 201810552374 A CN201810552374 A CN 201810552374A CN 108454844 A CN108454844 A CN 108454844A
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- Prior art keywords
- wing
- aircraft
- additional fin
- lift
- compound auxiliary
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin, wherein the no compound rotor aircraft of back pressure formula includes body, is fixedly mounted on body both sides hybrid lift wing, additional fin;Wherein, body is set as deck platform;Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge;Additional fin internal battery/fuel;The surface of additional fin, which is provided with the solar panel present invention, not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, low energy consumption for flight, the hang time is long, safe the features such as, the auxiliary wing uses hybrid lift, it is ensured that the accommodation of power.
Description
Technical field
The present invention relates to a kind of aircraft, the compound auxiliary wing of twin screw thrust of specifically a kind of solar energy additional fin is answered
Wing aircraft is closed, aircraft equipment technology field is belonged to.
Background technology
Existing aircraft is broadly divided into fixed-wing and vertically taking off and landing flyer(Such as helicopter and more rotors)Two major classes.When
So also there is this product of VTOL fixed-wing.Traditional fixed-wing have the advantages that flying speed is fast, low energy consumption, but have
It is not connected to before and after main wing and tailplane, wing structure intensity is not high, is easily damaged, and landing requires high, landing distance disadvantage;
Traditional vertically taking off and landing flyer has the advantages that landing is convenient, but has that energy consumption is big, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the shortcomings of air crash;Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
The shortcomings of controllability when flat flight is not satisfactory, and that there is flight resistances is big, and energy consumption is high, and safety coefficient is not still high.
Invention content
In view of the above-mentioned problems of the prior art, the present invention not only has landing apart from short, flying speed is fast, wing knot
Structure intensity height, wing can be with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area, feelings of meeting an urgent need
It can play the role of aerodone under condition, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.
To achieve the goals above, the present invention by the compound rotor aircraft of back pressure formula, be assemblied in the spiral of its wing both sides
The compound auxiliary wing of paddle thrust self energizing and additional fin composition;Wherein, the compound rotor aircraft of back pressure formula includes body, fixation
Mounted on body both sides hybrid lift wing;Wherein, wherein the body is set as deck platform;The hybrid lift
Self-enclosed ducted fan built in wing, hybrid lift wing outside are designed with wing hinge;The airscrew thrust self energizing
The front end of the compound auxiliary wing is provided with screw propeller, and the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed culvert
The one or both sides of road fan, the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and pass through
Wing hinge is flexibly connected with hybrid lift wing, wherein the electro-hydraulic gas interface carries lid, the airscrew thrust
The compound auxiliary wing of self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, be separately positioned on airscrew thrust self energizing
The front and back of the compound auxiliary wing;At least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.Additional fin towards body one
Side is provided with wing hinge, and is mounted on the outside of hybrid lift wing by the way that wing hinge is folding;Additional fin internal battery/
Fuel;The surface of additional fin is provided with solar panel.
Further, hybrid lift wing front and back are respectively set to magnetic-type self interlocking interface male connector and magnetic-type automatic
Mutual lock interface female;The magnetic-type self interlocking interface male connector is identical as magnetic-type self interlocking interface female size.
Further, magnetic-type self interlocking interface male connector(It is taper connection with magnetic-type self interlocking interface female.
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on compound
The front and back of lifting wing;It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space;Its
In, at least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity.
Further, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing, in engine installation position
It is provided with power plant, the power plant is screw propeller.
Further, it is provided with battery/fuel on the compound auxiliary wing of airscrew thrust self energizing.
The prior art is compared, the main feature having is invented:
1. the present invention has landing apart from short, flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, machine
The wing can be with energy storage, the features such as low energy consumption of flying.Self-enclosed vertical ducted fan is relied on, aircraft can be provided in horizontal flight
Additional maneuverability, realize moment change of flight posture and track super maneuver ability.
2. the Waverider wing that the present invention is very large, can play the role of certain paraglider, gravity acceleration is substantially reduced
Degree greatly improves safety coefficient, coordinates the control function of the hydroplane wing and the vertical rudder wing and the aerofoil envelope of self-enclosed ducted fan
Function is closed, even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously, is greatly improved
The safety of aircraft has ensured the safety of personnel and goods and materials.
3. the present invention can realize multiple functions using hardware and software platform, modularized design,
4. the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
5. the present invention also has successive magnetic-type self interlocking interface, the cluster of aircraft is facilitated to fly, into one
Step reduces power consumption when cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, energy
Realize the flight of long range, the not cluster flight of only aircraft provides the low-power consumption scheme of clustering, it might even be possible to realize
Air rescue between aircraft, i.e., preceding aircraft take off faulty aircraft dragging below, realize not seen before fly
Phenomenon is rescued mutually between row device.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable input of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize that repair is replaced.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft
Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
10. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility!
11. aerofoil type energy device, efficiently uses space.
12. additional fin carries solar energy equipment, increase the energy of complete machine, energy conservation and environmental protection!
13. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Description of the drawings
Fig. 1 is the structural schematic diagram of the present invention;
Fig. 2 is the side view of the present invention;
Fig. 3 is the rearview of the present invention;
Fig. 4 is the plan view of the present invention;
Fig. 5 is the oblique view of the present invention;
In figure:101:Body;102:Hybrid lift wing;104:Self-enclosed ducted fan;105:Vertical tail;1051. vertical
The rudder wing;107:Energy Management System;1021:Lift main wing;1022:The horizontal lifting rudder wing;1023:Balance empennage;1028:Wing
Hinge;1001:Socket;1002:Cavity;1003:Mounting hole;1006:Battery/fuel;108:Video camera;1026:It is magnetic-type from
Move mutual lock interface male connector;1027:Magnetic-type self interlocking interface female;1031, the compound auxiliary wing of airscrew thrust self energizing;
10311, the auxiliary wing of lift;10312, auxiliary empennage is balanced;1036, electro-hydraulic gas interface;10361, lid;111, engine installation position;
1062, screw propeller;114, additional fin;1141, solar panel.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
Such as Fig. 1 to Fig. 5, the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin, by no pusher
The compound auxiliary wing of the compound rotor aircraft of power formula, the airscrew thrust self energizing for being assemblied in its wing both sides and additional fin 114 form;
Wherein, the no compound rotor aircraft of back pressure formula includes body 101, is fixedly mounted on 101 both sides hybrid lift machine of body
The wing 102;Wherein, wherein the body 101 is set as deck platform;Self-enclosed culvert built in the hybrid lift wing 102
Road fan 104,102 outside of hybrid lift wing are designed with wing hinge 1028;The airscrew thrust self energizing is compound auxiliary
The front end of the wing is provided with screw propeller 1062, and the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed duct
The one or both sides of fan 104, the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge
1028, and be flexibly connected with hybrid lift wing 102 by wing hinge (1028), wherein the electro-hydraulic gas interface 1036
With lid 10361, the compound auxiliary wing of the airscrew thrust self energizing can be divided into the auxiliary wing 10311 of lift and the auxiliary empennage of balance
10312 two parts are separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing;Auxiliary 10311 inside of the wing of lift is extremely
There are one self-enclosed ducted fans 104 for few installation.The side of additional fin 114 towards body 101 is provided with wing hinge (1028),
And it is mounted on 102 outside of hybrid lift wing by the way that wing hinge (1028) is folding;114 internal batteries of additional fin/fuel
1006;The surface of additional fin 114 is provided with solar panel 1141
As further improvement of the invention, 102 front and back of hybrid lift wing are respectively set to magnetic-type self interlocking interface
Male connector 1026 and magnetic-type self interlocking interface female 1027;The magnetic-type self interlocking interface male connector 1026 with it is magnetic-type
Self interlocking interface 1027 sizes of female are identical.
As further improvement of the invention, magnetic-type self interlocking interface male connector 1026 and magnetic-type self interlocking interface
Female 1027 is taper connection,
As further improvement of the invention, hybrid lift wing 102 can be divided into lift main wing 1021 and balance empennage 1023
Two parts, are separately positioned on the front and back of hybrid lift wing 102;It is reserved between lift main wing 1021 and balance empennage 1023
There is space, the horizontal lifting rudder wing 1022 is provided in space;Wherein, at least there are one self-enclosed for installation inside lift main wing 1021
Ducted fan 104.
Improved as of the invention further, body 101 is installed with cavity 1002, in cavity 1002 installation diagram pass, fly control,
The modules such as driving.
As further improvement of the invention, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing
111, power plant is provided in engine installation position 111, the power plant is screw propeller.
As further improvement of the invention, battery/fuel 1006 is provided on the compound auxiliary wing of airscrew thrust self energizing.
The prior art is compared, the main feature having is invented:
1. the present invention has landing apart from short, flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, machine
The wing can be with energy storage, the features such as low energy consumption of flying.Self-enclosed vertical ducted fan is relied on, aircraft can be provided in horizontal flight
Additional maneuverability, realize moment change of flight posture and track super maneuver ability.
2. the Waverider wing that the present invention is very large, can play the role of certain paraglider, gravity acceleration is substantially reduced
Degree greatly improves safety coefficient, coordinates the control function of the hydroplane wing and the vertical rudder wing and the aerofoil envelope of self-enclosed ducted fan
Function is closed, even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously, is greatly improved
The safety of aircraft has ensured the safety of personnel and goods and materials.
3. the present invention can realize multiple functions using hardware and software platform, modularized design,
4. the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
5. the present invention also has successive magnetic-type self interlocking interface, the cluster of aircraft is facilitated to fly, into one
Step reduces power consumption when cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, energy
Realize the flight of long range, the not cluster flight of only aircraft provides the low-power consumption scheme of clustering, it might even be possible to realize
Air rescue between aircraft, i.e., preceding aircraft take off faulty aircraft dragging below, realize not seen before fly
Phenomenon is rescued mutually between row device.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable input of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize that repair is replaced.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft
Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
10. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility!
11. aerofoil type energy device, efficiently uses space.
12. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment should all belong to the scope of the present invention.
Claims (7)
1. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin, which is characterized in that by back pressure formula
The compound auxiliary wing of compound rotor aircraft, the airscrew thrust self energizing for being assemblied in its wing both sides, additional fin(114)Composition;
Wherein, the no compound rotor aircraft of back pressure formula includes body(101), be fixedly mounted on body(101)Both sides are multiple
Close lifting wing(102);Wherein, the body(101)It is set as deck platform;The hybrid lift wing(102)It is interior
Set self-enclosed ducted fan(104), hybrid lift wing(102)Outside is designed with wing hinge (1028);
The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with screw propeller(1062), airscrew thrust is certainly
Energize the compound auxiliary wing is internally provided with self-enclosed ducted fan(104), the side of the compound auxiliary wing of airscrew thrust self energizing or
Both sides are provided with electro-hydraulic gas interface(1036)With wing hinge (1028), and pass through wing hinge (1028) and hybrid lift wing
(102)Flexible connection, wherein the electro-hydraulic gas interface(1036)With lid(10361), the described airscrew thrust confession
The compound auxiliary wing of energy can be divided into the auxiliary wing of lift(10311)And the auxiliary empennage of balance(10312)Two parts, are separately positioned on propeller
The front and back of the compound auxiliary wing of thrust self energizing;The auxiliary wing of lift(10311)There are one self-enclosed ducted fans for internal at least installation
(104);
The additional fin(114)Towards body(101)Side be provided with wing hinge (1028), and pass through wing hinge
(1028) folding to be mounted on hybrid lift wing(102)Outside;Additional fin(114)Internal battery/fuel(1006);It is additional
The wing(114)Surface be provided with solar panel(1141).
2. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin according to claim 1,
It is characterized in that, the hybrid lift wing(102)Front and back are respectively set to magnetic-type self interlocking interface male connector(1026)
With magnetic-type self interlocking interface female(1027);The magnetic-type self interlocking interface male connector(1026)With it is magnetic-type automatic
Mutual lock interface female(1027)Size is identical.
3. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin according to claim 3,
It is characterized in that, the magnetic-type self interlocking interface male connector(1026)With magnetic-type self interlocking interface female(1027)For cone
Shape connects.
4. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin according to claim 1,
It is characterized in that, the hybrid lift wing(102)Lift main wing can be divided into(1021)And balance empennage(1023)Two portions
Point, it is separately positioned on hybrid lift wing(102)Front and back;Lift main wing(1021)With balance empennage(1023)Between reserve
There is space, the horizontal lifting rudder wing is provided in space(1022);Wherein, lift main wing(1021)There are one certainly for internal at least installation
Close ducted fan(104).
5. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin according to claim 1,
It is characterized in that, the body(101)It is installed with cavity(1002), cavity(1002)Interior installation diagram passes, flies the moulds such as control, driving
Block.
6. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin according to claim 1,
It is characterized in that, engine installation position is additionally provided on the compound auxiliary wing of the airscrew thrust self energizing(111), engine installation
Position(111)It is inside provided with power plant, the power plant is screw propeller.
7. the combined wing aircraft of the compound auxiliary wing of the twin screw thrust with solar energy additional fin according to claim 1,
It is characterized in that, battery/fuel is provided on the compound auxiliary wing of the airscrew thrust self energizing(1006).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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CN201810552374.2A CN108454844A (en) | 2018-05-31 | 2018-05-31 | The combined wing aircraft of the compound auxiliary wing of twin screw thrust with solar energy additional fin |
Applications Claiming Priority (1)
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CN201810552374.2A CN108454844A (en) | 2018-05-31 | 2018-05-31 | The combined wing aircraft of the compound auxiliary wing of twin screw thrust with solar energy additional fin |
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CN108454844A true CN108454844A (en) | 2018-08-28 |
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CN201810552374.2A Pending CN108454844A (en) | 2018-05-31 | 2018-05-31 | The combined wing aircraft of the compound auxiliary wing of twin screw thrust with solar energy additional fin |
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Citations (10)
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US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
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2018
- 2018-05-31 CN CN201810552374.2A patent/CN108454844A/en active Pending
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
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