CN108860591A - With turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft - Google Patents
With turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft Download PDFInfo
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- CN108860591A CN108860591A CN201810544371.4A CN201810544371A CN108860591A CN 108860591 A CN108860591 A CN 108860591A CN 201810544371 A CN201810544371 A CN 201810544371A CN 108860591 A CN108860591 A CN 108860591A
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- Prior art keywords
- wing
- turbofan
- compound auxiliary
- 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
-
- 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)
- Mechanical Engineering (AREA)
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Abstract
The present invention be it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft, wherein no back pressure formula composite wing cargo aircraft includes body, is fixedly mounted on body two sides hybrid lift wing；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, the outside design of hybrid lift wing have wing hinge；The front end of the compound auxiliary wing of turbofan thrust self energizing is provided with turbofan propeller, the compound auxiliary wing of turbofan thrust self energizing is internally provided with self-enclosed ducted fan, the one or both sides of the compound auxiliary wing of turbofan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected by wing hinge with hybrid lift wing.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 applicability of power.
Description
Technical field
The present invention relates to a kind of aircraft, it is specifically a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing shipping
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, the present invention by no back pressure formula composite wing cargo aircraft and is assemblied in its wing two sides
The compound auxiliary wing composition of turbofan thrust self energizing；Wherein, the no back pressure formula composite wing cargo aircraft includes body, consolidates
Dingan County is mounted in body two sides hybrid lift wing；Wherein, wherein the body is set as deck platform；The compound liter
Self-enclosed ducted fan built in power wing, the outside design of hybrid lift wing have wing hinge；The turbofan thrust self energizing
The front end of the compound auxiliary wing is provided with turbofan propeller, and the compound auxiliary wing of turbofan thrust self energizing is internally provided with self-enclosed culvert
The one or both sides of road fan, the compound auxiliary wing of turbofan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and pass through machine
Wing hinge is flexibly connected with hybrid lift wing, wherein the electro-hydraulic gas interface has lid, the turbofan thrust confession
The compound auxiliary wing of energy can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, and it is compound auxiliary to be separately positioned on turbofan thrust self energizing
The front and back of the wing；Wherein, it in the compound auxiliary wing of turbofan thrust self energizing of side, is reserved between the auxiliary wing of lift and the auxiliary empennage of balance
Space is provided with the horizontal lifting rudder wing in space；In the compound auxiliary wing of turbofan thrust self energizing of two sides, inside the auxiliary wing of lift at least
It is fitted with a self-enclosed ducted fan；Shipping storehouse is mounted on the lower section of body.
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 lift main wing and balance two parts of 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, a 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, it is additionally provided with engine installation position on the compound auxiliary wing of turbofan thrust self energizing, engine is set in installation position
It is equipped with power device, the power device is turbofan propeller.
Further, battery/fuel is provided on the compound auxiliary wing of turbofan 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, 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 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. aerofoil type energy device efficiently uses space.
11. the present invention uses modularized design, compound different types of machines are used, and have saved cost.
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；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：Fixation 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 turbofan 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；1064, whirlpool
Take turns fan propeller；113, shipping storehouse.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figures 1 to 5, it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft, it is special
Sign is, by no back pressure formula composite wing cargo aircraft and the compound auxiliary wing of turbofan thrust self energizing for being assemblied in its wing two sides
Composition；Wherein, the no back pressure formula composite wing cargo aircraft includes body 101, to be fixedly mounted on 101 two sides of body multiple
Close lifting wing 102；Wherein, wherein the body 101 is set as deck platform；Built in the hybrid lift wing 102
Self-enclosed ducted fan 104, design has wing hinge (1028) on the outside of hybrid lift wing 102；The turbofan thrust confession
The front end of the compound auxiliary wing of energy is provided with turbofan propeller 1064, and the compound auxiliary wing of turbofan thrust self energizing is internally provided with certainly
Ducted fan 104 is closed, the one or both sides of the compound auxiliary wing of turbofan thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing
Hinge (1028), and be flexibly connected by wing hinge (1028) with hybrid lift wing 102, wherein the electro-hydraulic gas connects
Mouth 1036 has lid 10361, and the compound auxiliary wing of turbofan thrust self energizing can be divided into the auxiliary wing 10311 of lift and balance is auxiliary
10,312 two parts of empennage, are separately positioned on the front and back of the compound auxiliary wing of turbofan thrust self energizing；Wherein, the turbofan of side pushes away
In the compound auxiliary wing of power self energizing, it is reserved with space between the auxiliary wing of lift and the auxiliary empennage of balance, horizontal lifting rudder is provided in space
The wing；In the compound auxiliary wing of turbofan thrust self energizing of two sides, a self-enclosed ducted fan is at least fitted with inside the auxiliary wing of lift；
Shipping storehouse is mounted on the lower section of body.
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 turbofan thrust self energizing
111, power device is provided in engine installation position 111, the power device is turbofan propeller.
As further improvement of the invention, battery/fuel 1006 is provided on the compound auxiliary wing of turbofan 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, 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 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. aerofoil type energy device efficiently uses space.
11. the present invention uses modularized design, compound different types of machines are used, and have saved cost.
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 belong to the scope of the present invention.
Claims (7)
1. it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft, which is characterized in that by no back pressure
Formula composite wing cargo aircraft, the compound auxiliary wing of turbofan thrust self energizing for being assemblied in its wing two sides, shipping storehouse（113）Composition；
Wherein, the no back pressure formula composite wing cargo aircraft includes body（101）, be fixedly mounted on body（101）Two
Side hybrid lift wing（102）；Wherein, wherein the body（101）It is set as deck platform；The hybrid lift machine
The wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside design has wing hinge (1028)；
Turbofan propeller is provided with below the compound auxiliary wing of turbofan thrust self energizing（1064）, the confession of turbofan thrust
The compound auxiliary wing of energy is internally provided with self-enclosed ducted fan（104）, the one or both sides of the compound auxiliary wing of turbofan thrust self energizing
It is provided with electro-hydraulic gas interface（1036）With 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）With lid（10361）,
The compound auxiliary wing of turbofan thrust self energizing can be divided into the auxiliary wing of lift（10311）And the auxiliary empennage of balance（10312）Two
A part is separately positioned on the front and back of the compound auxiliary wing of turbofan thrust self energizing；Wherein, the turbofan thrust self energizing of side is compound
In the auxiliary wing, wherein in the compound auxiliary wing of turbofan thrust self energizing of side, the auxiliary wing of lift（10311）With the auxiliary empennage of balance（10312）
Between be reserved with space, the horizontal lifting rudder wing is provided in space（1022）；In the compound auxiliary wing of turbofan thrust self energizing of two sides,
The auxiliary wing of lift（10311）Inside is at least fitted with a self-enclosed ducted fan（104）；
The shipping storehouse（113）It is mounted on body（101）Lower section.
2. it is according to claim 1 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft,
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. it is according to claim 3 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft, it is special
Sign is, the magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female（1027）For taper
Connection.
4. it is according to claim 1 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft,
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）Inside is at least equipped with one certainly
Close ducted fan（104）.
5. it is according to claim 1 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft,
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. it is according to claim 1 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft,
It is characterized in that, is additionally provided with engine installation position on the compound auxiliary wing of turbofan thrust self energizing（111）, engine installation position
（111）It is inside provided with power device, the power device is turbofan propeller.
7. it is according to claim 1 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft,
It is characterized in that, is provided with battery/fuel on the compound auxiliary wing of turbofan thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544371.4A CN108860591A (en) | 2018-05-31 | 2018-05-31 | With turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544371.4A CN108860591A (en) | 2018-05-31 | 2018-05-31 | With turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108860591A true CN108860591A (en) | 2018-11-23 |
Family
ID=64335634
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810544371.4A Pending CN108860591A (en) | 2018-05-31 | 2018-05-31 | With turbofan push away the compound auxiliary wing without back pressure formula composite wing cargo aircraft |
Country Status (1)
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| CN (1) | CN108860591A (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 |
| 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 |
| 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 |
-
2018
- 2018-05-31 CN CN201810544371.4A patent/CN108860591A/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 |
| 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 |
| 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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Application publication date: 20181123 |