CN108945414A - Rear single ducted fan formula combined wing aircraft with the compound auxiliary wing and additional fin - Google Patents
Rear single ducted fan formula combined wing aircraft with the compound auxiliary wing and additional fin Download PDFInfo
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- CN108945414A CN108945414A CN201810544293.8A CN201810544293A CN108945414A CN 108945414 A CN108945414 A CN 108945414A CN 201810544293 A CN201810544293 A CN 201810544293A CN 108945414 A CN108945414 A CN 108945414A
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- wing
- ducted fan
- aircraft
- lift
- auxiliary wing
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- 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
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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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention is rear single ducted fan formula combined wing aircraft of a kind of the band compound auxiliary wing and additional fin, a kind of rear single ducted fan formula combined wing aircraft of the band compound auxiliary wing and additional fin, it is characterized in that, by the compound rotor aircraft of rear single ducted fan formula, being assemblied in the compound auxiliary wing of airscrew thrust self energizing of its wing two sides and additional fin forms.The 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, highly-safe the features such as, the auxiliary wing uses hybrid lift, it is ensured that the adaptation range of power.
Description
Technical field
The present invention relates to a kind of aircraft, rear single ducted fan formula of the compound auxiliary wing of specifically a kind of band and additional fin is compound
Wing aircraft belongs to aircraft equipment technology field.
Background technique
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 high, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the disadvantages of air crash；Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
The disadvantages 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.
Summary of the invention
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, rear single ducted fan formula combined wing aircraft of the compound auxiliary wing of band of the present invention and additional fin,
It is characterized in that, being answered by the compound rotor aircraft of rear single ducted fan formula, the airscrew thrust self energizing for being assemblied in its wing two sides
Close the auxiliary wing and additional fin composition；Wherein, rear single compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on machine
Body two sides hybrid lift wing, propeller；Wherein, body is set as deck platform；Self-enclosed duct built in hybrid lift wing
Fan, the outside design of hybrid lift wing have wing hinge；Propeller is ducted fan propeller；The airscrew thrust is certainly
The front end for energizing the compound auxiliary wing is provided with screw propeller, and being internally provided with for the compound auxiliary wing of airscrew thrust self energizing is self-styled
Ducted fan is closed, the one or both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and
It is flexibly connected by wing hinge with hybrid lift wing, wherein electro-hydraulic gas interface has lid, and airscrew thrust self energizing is multiple
The auxiliary wing of lift and auxiliary two parts of empennage of balance can be divided by closing the auxiliary wing, be separately positioned on the compound auxiliary wing of airscrew thrust self energizing
Front and back；It is reserved with space between the auxiliary wing of lift and the auxiliary empennage of balance, the horizontal lifting rudder wing is provided in space；Wherein, it rises
One self-enclosed ducted fan is at least installed inside the auxiliary wing of power；Additional fin is mounted on no thrust by the way that wing hinge is folding
On the outside of the auxiliary wing of self energizing；Fuel built in additional fin or battery.
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 and magnetic-type self interlocking interface female are taper connection,
Further, hybrid lift wing can be divided into lift main wing and balance two parts of empennage, be separately positioned on hybrid lift
The front and back of wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Wherein,
One self-enclosed ducted fan is at least installed 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 device, the power device is screw propeller.
Further, battery/fuel is provided on the compound auxiliary wing of airscrew thrust self energizing.
Further, additional wing surface is provided with solar panel.
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, obstacle 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 modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention uses hybrid lift, i.e., existed by design
Self-enclosed ducted fan in aerofoil generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to be formed compound
Lift.
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, cooperates 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 damage simultaneously, the forced landing of aerodone formula is also able to achieve, greatly improves
The safety of aircraft has ensured the safety of personnel and goods and materials.
3. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
4. the present invention using two 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.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, energy
Realize the flight of long range, the cluster flight of only aircraft does not provide 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 investment of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded 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 maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve 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 are used, and have saved cost.
13. additional fin has solar energy equipment, increase the energy of complete machine, energy conservation and environmental protection！
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is side view of the invention；
Fig. 3 is rearview of the invention；
Fig. 4 is plan view of the invention；
Fig. 5 is oblique view of the invention；
In figure: 101: body；102: hybrid lift wing；104: self-enclosed ducted fan；105: vertical tail；1051. vertical
The rudder wing；106: propeller；107: Energy Management System；1021: lift main wing；1022: the horizontal lifting rudder wing；1023: balance tail
The wing；1028: wing hinge；1001: socket；1002: cavity；1003: fixation hole；1006: battery/fuel；108: video camera；
1026: magnetic-type self interlocking interface male connector；1027: magnetic-type self interlocking interface female；1031, airscrew thrust self energizing
The compound auxiliary wing；10311, the auxiliary wing of lift；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；10361, lid；111, start
Machine installation position；1062, screw propeller；114, additional fin；1141, solar panel.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figure 1, a kind of rear single ducted fan formula combined wing aircraft of the band compound auxiliary wing and additional fin, feature exist
In, by the compound rotor aircraft of rear single ducted fan formula, be assemblied in its wing two sides the compound auxiliary wing of airscrew thrust self energizing and
Additional fin composition；Wherein, rear single compound rotor aircraft of ducted fan formula includes body 101, is fixedly mounted on body 101
Two sides hybrid lift wing 102, propeller 106；Wherein, wherein the body 101 is set as deck platform；Described answers
Self-enclosed ducted fan 104 built in lifting wing 102 is closed, design has wing hinge 1028 on the outside of hybrid lift wing 102；It promotes
Device 106 is ducted fan propeller；The front end of the compound auxiliary wing of airscrew thrust self energizing is provided with screw propeller 1062, spiral shell
The rotation compound auxiliary wing of paddle thrust self energizing is internally provided with self-enclosed ducted fan 104, the compound auxiliary wing of airscrew thrust self energizing
One or both sides be provided with electro-hydraulic gas interface 1036 and wing hinge 1028, and pass through wing hinge 1028 and hybrid lift machine
The wing 102 is flexibly connected, wherein the electro-hydraulic gas interface 1036 has lid 10361, and the airscrew thrust self energizing is multiple
The auxiliary wing 10311 of lift and auxiliary 10,312 two parts of empennage of balance can be divided by closing the auxiliary wing, be separately positioned on airscrew thrust confession
The front and back of the compound auxiliary wing of energy；It is reserved with space between the auxiliary wing 10311 of lift and the auxiliary empennage 10312 of balance, is provided in space
The horizontal lifting rudder wing 1022；Wherein, a self-enclosed ducted fan 104 is at least installed inside the auxiliary wing 10311 of lift；Additional fin
114 are mounted on the outside of the auxiliary wing of no thrust self energizing by the way that wing hinge 1028 is folding；Fuel built in the additional fin 114
Or battery.
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 and magnetic
Suction 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, be at least equipped with inside lift main wing 1,021 one it is self-enclosed
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 device is provided in engine installation position 111, the power device is screw propeller.
As further improvement of the invention, battery/fuel 1006 is provided on the compound auxiliary wing of airscrew thrust self energizing.
As further improvement of the invention, 114 surface of additional fin is provided with solar panel 1141.
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, obstacle 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 modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention uses hybrid lift, i.e., existed by design
Self-enclosed ducted fan in aerofoil generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to be formed compound
Lift.
3. 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, cooperates 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 damage simultaneously, the forced landing of aerodone formula is also able to achieve, greatly improves
The safety of aircraft has ensured the safety of personnel and goods and materials.
4. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
5. the present invention using two sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
6. 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.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, energy
Realize the flight of long range, the cluster flight of only aircraft does not provide 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.
7. 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 investment of client, reduces buying and operation cost.
8. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
9. thrust device modularization can very easily realize maintenance replacement.
10. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift flies
Energy intercommunication between device main plane, and the control by hybrid lift aircraft is acted, improve the flexibility of complete machine.
11. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
12. aerofoil type energy device efficiently uses space.
13. the present invention uses modularized design, compound different types of machines are used, and have saved cost.
14. additional fin has solar energy equipment, increase the energy of complete machine, energy conservation and environmental protection！
Schematically the present invention and embodiments thereof are described above, description is not limiting, shown in the drawings
It also is one of embodiments of the present invention, actual structure is not limited to this.So if the ordinary skill people of this field
Member is enlightened by it, without departing from the spirit of the invention, is not inventively designed similar to the technical solution
Frame mode and embodiment, should belong to the scope of the present invention.
Claims (8)
1. a kind of rear single ducted fan formula combined wing aircraft of the band compound auxiliary wing and additional fin, which is characterized in that by rear single duct
The compound auxiliary wing of the compound rotor aircraft of fan-type, the airscrew thrust self energizing for being assemblied in its wing two sides and additional fin (114) group
At；
Wherein, rear single compound rotor aircraft of ducted fan formula includes body (101), is fixedly mounted on body (101) two
Side hybrid lift wing (102), propeller (106)；Wherein, wherein the body (101) is set as deck platform；It is described
Hybrid lift wing (102) built in self-enclosed ducted fan (104), design has wing hinge on the outside of hybrid lift wing (102)
Chain (1028)；Propeller (106) is ducted fan propeller；
The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with screw propeller (1062), and airscrew thrust is certainly
Energize being internally provided with self-enclosed ducted fan (104) for the compound auxiliary wing, the side of the compound auxiliary wing of airscrew thrust self energizing or
Two sides are provided with electro-hydraulic gas interface (1036) and wing hinge (1028), and pass through wing hinge (1028) and hybrid lift wing
(102) it is flexibly connected, wherein the electro-hydraulic gas interface (1036) has lid (10361), the airscrew thrust confession
The compound auxiliary wing of energy can be divided into the auxiliary wing of lift (10311) and auxiliary (10312) two parts of empennage of balance, be separately positioned on propeller
The front and back of the compound auxiliary wing of thrust self energizing；It is reserved with space between the auxiliary wing of lift (10311) and the auxiliary empennage (10312) of balance,
The horizontal lifting rudder wing (1022) is provided in space；Wherein, a self-enclosed culvert is at least installed inside the auxiliary wing of lift (10311)
Road fan (104)；
The additional fin (114) is mounted on the outside of the auxiliary wing of no thrust self energizing by the way that wing hinge (1028) are folding；Institute
Fuel or battery built in the additional fin (114) stated.
2. rear single ducted fan formula combined wing aircraft of a kind of band compound auxiliary wing and additional fin according to claim 1,
It is characterized in that, described 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) and magnetic-type automatic
Mutual lock interface female (1027) size is identical.
3. rear single ducted fan formula combined wing aircraft of a kind of band compound auxiliary wing and additional fin according to claim 3, special
Sign is that the magnetic-type self interlocking interface male connector (1026) and magnetic-type self interlocking interface female (1027) are taper
Connection.
4. rear single ducted fan formula combined wing aircraft of a kind of band compound auxiliary wing and additional fin according to claim 1,
It is characterized in that, the hybrid lift wing (102) can be divided into lift main wing (1021) and balance (1023) two portions of empennage
Point, it is 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, one is at least equipped with inside lift main wing (1021) certainly
It closes ducted fan (104).
5. rear single ducted fan formula combined wing aircraft of a kind of band compound auxiliary wing and additional fin according to claim 1,
It is characterized in that, the body (101) is installed with cavity (1002), and the interior installation diagram of cavity (1002) passes, flies the moulds such as control, driving
Block.
6. rear single ducted fan formula combined wing aircraft of a kind of band compound auxiliary wing and additional fin according to claim 1,
It is characterized in that, is additionally provided with engine installation position (111) on the compound auxiliary wing of the airscrew thrust self energizing, engine installation
Power device is provided in position (111), the power device is screw propeller.
7. rear single ducted fan formula combined wing aircraft of a kind of band compound auxiliary wing and additional fin according to claim 1,
It is characterized in that, is provided with battery/fuel (1006) on the compound auxiliary wing of the airscrew thrust self energizing.
8. special according to a kind of rear single ducted fan formula combined wing aircraft of the band compound auxiliary wing and additional fin described in claim 1
Sign is that the additional fin (114) surface is provided with solar panel (1141).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544293.8A CN108945414A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula combined wing aircraft with the compound auxiliary wing and additional fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544293.8A CN108945414A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula combined wing aircraft with the compound auxiliary wing and additional fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108945414A true CN108945414A (en) | 2018-12-07 |
Family
ID=64492347
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810544293.8A Pending CN108945414A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula combined wing aircraft with the compound auxiliary wing and additional fin |
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| CN (1) | CN108945414A (en) |
Citations (9)
| 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 |
| US20040245374A1 (en) * | 2003-01-06 | 2004-12-09 | Morgan Brian H. | 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 |
| 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 |
-
2018
- 2018-05-31 CN CN201810544293.8A patent/CN108945414A/en active Pending
Patent Citations (9)
| 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 |
| US20040245374A1 (en) * | 2003-01-06 | 2004-12-09 | Morgan Brian H. | 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 |
| 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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Application publication date: 20181207 |