CN108791869A - With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle - Google Patents

With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle Download PDF

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Publication number
CN108791869A
CN108791869A CN201810544323.5A CN201810544323A CN108791869A CN 108791869 A CN108791869 A CN 108791869A CN 201810544323 A CN201810544323 A CN 201810544323A CN 108791869 A CN108791869 A CN 108791869A
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CN
China
Prior art keywords
wing
turbofan
compound auxiliary
lift
auxiliary wing
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
CN201810544323.5A
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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 CN201810544323.5A priority Critical patent/CN108791869A/en
Publication of CN108791869A publication Critical patent/CN108791869A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like
    • 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
    • B64C3/00Wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C9/00Adjustable control surfaces or members, e.g. rudders

Abstract

The present invention be it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle, wherein no back pressure formula composite wing manned vehicle includes body, is fixedly mounted on body both sides hybrid lift wing;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;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 with hybrid lift wing by wing hinge.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, safe the features such as, the auxiliary wing uses hybrid lift, it is ensured that the applicability of power.

Description

With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle
Technical field
It is specifically a kind of to push away the manned without back pressure formula composite wing of the compound auxiliary wing with turbofan the present invention relates to a kind of aircraft Aircraft belongs to aircraft equipment technology field.
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 no back pressure formula composite wing manned vehicle and is assemblied in its wing both sides The compound auxiliary wing composition of turbofan thrust self energizing;Wherein, the no back pressure formula composite wing manned vehicle includes body, consolidates Dingan County is mounted in body both sides hybrid lift wing;Wherein, wherein the body is set as deck platform;The compound liter Self-enclosed ducted fan built in power wing, hybrid lift wing outside are designed with 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 carries lid, 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;A self-enclosed ducted fan is at least fitted with inside the auxiliary wing of lift;Manned 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 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, 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 plant, the power plant is turbofan propeller.
Further, it is provided with battery/fuel 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, 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. aerofoil type energy device, efficiently uses space.
11. 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 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;112, manned storehouse.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
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 manned vehicle, it is special Sign is, by no back pressure formula composite wing manned vehicle and the compound auxiliary wing of turbofan thrust self energizing for being assemblied in its wing both sides Composition;Wherein, the no back pressure formula composite wing manned vehicle includes body 101, to be fixedly mounted on 101 both 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 104,102 outside of hybrid lift wing are designed with wing hinge (1028);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 with hybrid lift wing 102 by wing hinge (1028), wherein the electro-hydraulic gas connects Mouth 1036 carries 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;Inside the auxiliary wing of lift at least all There are one self-enclosed ducted fans for installation;Manned 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, 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 turbofan thrust self energizing 111, power plant is provided in engine installation position 111, the power plant 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, 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. aerofoil type energy device, efficiently uses space.
11. 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. it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle, which is characterized in that by no back pressure Formula composite wing manned vehicle, the compound auxiliary wing of turbofan thrust self energizing for being assemblied in its wing both sides, manned storehouse(112)Composition;
Wherein, the no back pressure formula composite wing manned vehicle 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 is designed with wing hinge (1028);
It is provided with turbofan propeller 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)Flexible connection, 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, the auxiliary wing of lift(10311)Inside is at least fitted with a self-enclosed ducted fan(104);
The manned storehouse(112)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 manned vehicle, 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. according to right want described in 3 it is a kind of with turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle, 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 manned vehicle, 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. 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 manned vehicle, 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 manned vehicle, It is characterized in that, engine installation position is additionally provided on the compound auxiliary wing of turbofan thrust self energizing(111), engine installation position (111)It is inside provided with power plant, the power plant 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 manned vehicle, It is characterized in that, battery/fuel is provided on the compound auxiliary wing of turbofan thrust self energizing(1006).
CN201810544323.5A 2018-05-31 2018-05-31 With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle Pending CN108791869A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810544323.5A CN108791869A (en) 2018-05-31 2018-05-31 With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810544323.5A CN108791869A (en) 2018-05-31 2018-05-31 With turbofan push away the compound auxiliary wing without back pressure formula composite wing manned vehicle

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CN108791869A true CN108791869A (en) 2018-11-13

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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: 20181113