CN108820202A - It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula - Google Patents

It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula Download PDF

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Publication number
CN108820202A
CN108820202A CN201810553099.6A CN201810553099A CN108820202A CN 108820202 A CN108820202 A CN 108820202A CN 201810553099 A CN201810553099 A CN 201810553099A CN 108820202 A CN108820202 A CN 108820202A
Authority
CN
China
Prior art keywords
wing
ducted fan
compound
auxiliary wing
lift
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201810553099.6A
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Chinese (zh)
Inventor
任曲波
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangsu Chang Exploration Robot Co Ltd
Original Assignee
Jiangsu Chang Exploration Robot Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Jiangsu Chang Exploration Robot Co Ltd filed Critical Jiangsu Chang Exploration Robot Co Ltd
Priority to CN201810553099.6A priority Critical patent/CN108820202A/en
Publication of CN108820202A publication Critical patent/CN108820202A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/20Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C37/00Convertible aircraft
    • B64C37/02Flying units formed by separate aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/16Unmanned aerial vehicles; Equipment therefor characterised by type of propulsion unit
    • B64C2201/162Unmanned aerial vehicles; Equipment therefor characterised by type of propulsion unit using ducted fans or propellers

Abstract

The present invention be it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, wherein the no compound rotor aircraft of back pressure formula 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 ducted fan thrust self energizing is provided with ducted fan propeller, the compound auxiliary wing of ducted fan thrust self energizing is internally provided with self-enclosed ducted fan, the one or both sides of the compound auxiliary wing of ducted fan 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 power it is suitable.

Description

It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula
Technical field
It is specifically a kind of to fly with the compound auxiliary wing of ducted fan without back pressure formula composite wing the present invention relates to a kind of aircraft Row device 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 is by no compound rotor aircraft of back pressure formula and the culvert for being assemblied in its wing two sides The compound auxiliary wing composition of road fan thrust self energizing;Wherein, the no compound rotor aircraft of back pressure formula includes body, fixed peace Mounted in body two sides hybrid lift wing;Wherein, wherein the body is set as deck platform;The hybrid lift machine Self-enclosed ducted fan built in the wing, the outside design of hybrid lift wing have wing hinge;The ducted fan thrust self energizing The front end of the compound auxiliary wing is provided with ducted fan propeller, and being internally provided with for the compound auxiliary wing of ducted fan thrust self energizing is self-styled Ducted fan is closed, the one or both sides of the compound auxiliary wing of ducted fan 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 the electro-hydraulic gas interface has lid, the duct The compound auxiliary wing of fan thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, be separately positioned on ducted fan The front and back of the compound auxiliary wing of thrust self energizing;One self-enclosed ducted fan is at least installed inside the auxiliary wing of lift.
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, engine installation position, engine installation position are additionally provided on the compound auxiliary wing of ducted fan thrust self energizing It is inside provided with power device, the power device is ducted fan propeller.
Further, battery/fuel is provided on the compound auxiliary wing of ducted fan 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 ducted fan 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; 1063, ducted fan propeller.
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 the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, by without after The compound rotor aircraft of thrust type and the compound auxiliary wing composition of the ducted fan thrust self energizing for being assemblied in its wing two sides;Wherein, institute That states includes body 101 without the compound rotor aircraft of back pressure formula, is fixedly mounted on 101 two sides hybrid lift wing 102 of body;Its In, wherein the body 101 is set as deck platform;Self-enclosed ducted fan built in the hybrid lift wing 102 104, design has wing hinge (1028) on the outside of hybrid lift wing 102;The compound auxiliary wing of ducted fan thrust self energizing Front end be provided with ducted fan propeller 1063, the compound auxiliary wing of ducted fan thrust self energizing is internally provided with self-enclosed culvert Road fan 104, the one or both sides of the compound auxiliary wing of ducted fan thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge Chain (1028), and be flexibly connected by wing hinge (1028) with hybrid lift wing 102, wherein the electro-hydraulic gas interface 1036 have lid 10361, and the compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing 10311 of lift and balance 10,312 two parts of auxiliary empennage, are separately positioned on the front and back of the compound auxiliary wing of ducted fan thrust self energizing;The auxiliary wing of lift One self-enclosed ducted fan 104 is at least installed inside 10311.
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 is additionally provided on the compound auxiliary wing of ducted fan thrust self energizing Position 111, power device is provided in engine installation position 111, and the power device is ducted fan propeller.
As further improvement of the invention, battery/fuel is provided on the compound auxiliary wing of ducted fan thrust self energizing 1006。
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 the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, which is characterized in that by no back pressure formula Compound rotor aircraft and the compound auxiliary wing composition of the ducted fan thrust self energizing for being assemblied in its wing two sides;
Wherein, the no compound rotor aircraft of back pressure formula includes body(101), be fixedly mounted on body(101)Two 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 design has wing hinge (1028);
The front end of the compound auxiliary wing of ducted fan thrust self energizing is provided with ducted fan propeller(1063), ducted fan The compound auxiliary wing of thrust self energizing is internally provided with self-enclosed ducted fan(104), the compound auxiliary wing of ducted fan thrust self energizing One or both sides be provided with electro-hydraulic gas interface(1036)With wing hinge (1028), and by wing hinge (1028) with it is compound Lifting wing(102)It is flexibly connected, wherein the electro-hydraulic gas interface(1036)With lid(10361), the duct wind The fan compound auxiliary wing of thrust self energizing can be divided into the auxiliary wing of lift(10311)And the auxiliary empennage of balance(10312)Two parts, set respectively It sets in the front and back of the compound auxiliary wing of ducted fan thrust self energizing;The auxiliary wing of lift(10311)Inside be at least equipped with one it is self-styled Close ducted fan(104).
2. it is according to claim 1 it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, it is special Sign is, 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 magnetic-type automatic mutual Lock interface female(1027)Size is identical.
3. it is according to claim 3 it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, feature It is, the magnetic-type self interlocking interface male connector(1026)With magnetic-type self interlocking interface female(1027)For taper company It connects.
4. it is according to claim 1 it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, it is special Sign is, the hybrid lift wing(102)Lift main wing can be divided into(1021)And balance empennage(1023)Two parts, It is separately positioned on hybrid lift wing(102)Front and back;Lift main wing(1021)With balance empennage(1023)Between be reserved with Space is provided with the horizontal lifting rudder wing in space(1022);Wherein, lift main wing(1021)Inside be at least equipped with one it is self-styled Close ducted fan(104).
5. it is according to claim 1 it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, it is special Sign is, the body(101)It is installed with cavity(1002), cavity(1002)Interior installation diagram passes, flies the modules such as control, driving.
6. it is according to claim 1 it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, it is special Sign is, is additionally provided with engine installation position on the compound auxiliary wing of ducted fan thrust self energizing(111), engine installation Position(111)It is inside provided with power device, the power device is ducted fan propeller.
7. it is according to claim 1 it is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula, it is special Sign is, is provided with battery/fuel on the compound auxiliary wing of ducted fan thrust self energizing(1006).
CN201810553099.6A 2018-05-31 2018-05-31 It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula Pending CN108820202A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810553099.6A CN108820202A (en) 2018-05-31 2018-05-31 It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810553099.6A CN108820202A (en) 2018-05-31 2018-05-31 It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula

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CN108820202A true CN108820202A (en) 2018-11-16

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103935512A (en) * 2014-05-12 2014-07-23 马轶 High endurable multi-rotor craft
CN205131644U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Four -axis glide vehicle
CN206107569U (en) * 2016-09-26 2017-04-19 中国航空工业集团公司沈阳飞机设计研究所 Unmanned aerial vehicle
CN107813929A (en) * 2016-09-11 2018-03-20 郎风 Combined type dalta wing duct aircraft

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103935512A (en) * 2014-05-12 2014-07-23 马轶 High endurable multi-rotor craft
CN205131644U (en) * 2015-10-30 2016-04-06 佛山市神风航空科技有限公司 Four -axis glide vehicle
CN107813929A (en) * 2016-09-11 2018-03-20 郎风 Combined type dalta wing duct aircraft
CN206107569U (en) * 2016-09-26 2017-04-19 中国航空工业集团公司沈阳飞机设计研究所 Unmanned aerial vehicle

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Application publication date: 20181116

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