CN108639327A - A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts - Google Patents

A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts Download PDF

Info

Publication number
CN108639327A
CN108639327A CN201810551432.XA CN201810551432A CN108639327A CN 108639327 A CN108639327 A CN 108639327A CN 201810551432 A CN201810551432 A CN 201810551432A CN 108639327 A CN108639327 A CN 108639327A
Authority
CN
China
Prior art keywords
wing
aircraft
ducted fan
compound auxiliary
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
CN201810551432.XA
Other languages
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 CN201810551432.XA priority Critical patent/CN108639327A/en
Publication of CN108639327A publication Critical patent/CN108639327A/en
Pending legal-status Critical Current

Links

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

Abstract

The present invention is a kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts, is made of rear single-screw paddle composite wing aircraft and the compound auxiliary wing of ducted fan thrust self energizing for being assemblied in its wing both sides;Single-screw paddle composite wing aircraft includes body, is fixedly mounted on body both sides hybrid lift wing, propeller afterwards;Wherein, 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;Propeller is screw propeller.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 accommodation of power.

Description

A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts
Technical field
The present invention relates to a kind of aircraft, the rear single-blade formula combined wing aircraft of specifically a kind of double compound auxiliary wings of duct thrust , belong 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 rear single-screw paddle composite wing aircraft and is movably arranged on hybrid lift The compound auxiliary wing composition of ducted fan thrust self energizing of aircraft both sides;Wherein, rear single-screw paddle composite wing aircraft includes Body is fixedly mounted on body both sides hybrid lift wing, propeller;Wherein, body is set as deck platform;Hybrid lift machine Self-enclosed ducted fan built in the wing, hybrid lift wing outside are designed with wing hinge;Ducted fan thrust self energizing is compound auxiliary The front end of the wing is provided with ducted fan propeller, and the compound auxiliary wing of ducted fan thrust self energizing is internally provided with self-enclosed duct The one or both sides of fan, the compound auxiliary wing of ducted fan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and pass through Wing hinge is flexibly connected with hybrid lift wing.
Further, propeller is a variety of dynamic structures such as electric propeller, the dynamic propeller of oil.
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;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 two parts of lift main wing and balance 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, At least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, further include vertical tail, the vertical tail is arranged above or below body;The vertical tail is set It sets in wing both sides;The vertical tail may be implemented to fold;Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity..
Further, the compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two portions of empennage of balance Point, it is separately positioned on the front and back of the compound auxiliary wing of ducted fan thrust self energizing;Wherein, at least it is equipped with one inside the auxiliary wing of lift A self-enclosed ducted fan.
Further, engine installation position, engine installation position are additionally provided on the compound auxiliary wing of ducted fan thrust self energizing Inside it is provided with power plant.
Further, the compound auxiliary wing engine installation position installation of ducted fan thrust self energizing is electric propeller or oil Dynamic propeller.
Further, it is provided with battery/fuel 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, 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 auxiliary wing of modularization ducted fan drive-in hybrid lift of the present 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, compound to be formed 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, 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.
4. the present invention can realize multiple functions using hardware and software platform, modularized design,
5. 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.
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.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.
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 input of client, reduces buying and operation cost.
8. 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.
9. thrust device modularization can very easily realize that repair is replaced.
10. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and fly with hybrid lift Energy intercommunication between device main plane, and action is controlled by hybrid lift aircraft, improves 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 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;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:Mounting hole;1006:Battery/fuel;108:Video camera; 1026:Magnetic-type self interlocking interface male connector;1027:Magnetic-type self interlocking interface female;10311, the auxiliary wing of lift;10312、 Balance auxiliary empennage;1036, electro-hydraulic gas interface;10361, lid;111, engine installation position;1063, ducted fan propeller.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figures 1 to 5, a kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts, by rear single-screw The compound rotor aircraft of paddle and the compound auxiliary wing composition of the ducted fan thrust self energizing for being assemblied in its wing both sides;
Wherein, the rear single-screw paddle composite wing aircraft includes body 101, to be fixedly mounted on 101 both sides of body compound Lifting wing 102, propeller 106;Wherein, wherein the body 101 is set as deck platform;The hybrid lift machine Self-enclosed ducted fan 104 built in the wing 102,102 outside of hybrid lift wing are designed with wing hinge (1028);
The front end of the compound auxiliary wing of ducted fan thrust self energizing is provided with ducted fan propeller 1063, the confession of ducted fan thrust Can the compound auxiliary wing be internally provided with self-enclosed ducted fan 104, the side of the compound auxiliary wing of ducted fan thrust self energizing or Both sides are provided with electro-hydraulic gas interface 1036 and wing hinge (1028), and pass through wing hinge (1028) and hybrid lift wing 102 flexible connections, wherein the electro-hydraulic gas interface 1036 carries lid 10361.
As further improvement of the invention, propeller 106 is a variety of power knots such as electric propeller, the dynamic propeller of oil Structure.
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.
Further include vertical tail 105 as further improvement of the invention, the vertical tail 105 is arranged in body 101 Above or below;The vertical tail 105 is arranged in wing both sides;The vertical tail 105 may be implemented to fold;It is described vertical Mobilizable vertical rudder wing 1051 is installed behind empennage 105.
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.
It is improved as of the invention further, the compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift 10311 And auxiliary 10,312 two parts of empennage of balance, it is separately positioned on the front and back of the compound auxiliary wing of ducted fan thrust self energizing;Its In, at least there are one self-enclosed ducted fans 104 for installation inside the auxiliary wing of lift 10311.
As further improvement of the invention, engine installation is additionally provided on the compound auxiliary wing of ducted fan thrust self energizing Position 111 is provided with power plant in engine installation position 111.
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, 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 auxiliary wing of modularization ducted fan drive-in hybrid lift of the present 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, compound to be formed 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, 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.
4. the present invention can realize multiple functions using hardware and software platform, modularized design,
5. 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.
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.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.
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 input of client, reduces buying and operation cost.
8. 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.
9. thrust device modularization can very easily realize that repair is replaced.
10. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and fly with hybrid lift Energy intercommunication between device main plane, and action is controlled by hybrid lift aircraft, improves 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 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 (9)

1. a kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts, which is characterized in that answered by rear single-screw paddle The compound auxiliary wing composition of ducted fan thrust self energizing for closing rotor aircraft and being assemblied in its wing both sides;
Wherein, the rear single-screw paddle composite wing aircraft includes body(101), be fixedly mounted on body(101)Both sides Hybrid lift wing(102), propeller(106);Wherein, wherein the body(101)It is set as deck platform;Described Hybrid lift wing(102)Built-in self-enclosed ducted fan(104), hybrid lift wing(102)Outside is designed with wing hinge (1028);Propeller(106)For screw propeller;
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)Flexible connection, wherein the electro-hydraulic gas interface(1036)With lid(10361);
The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift(10311)And the auxiliary empennage of balance (10312)Two parts are separately positioned on the front and back of the compound auxiliary wing of ducted fan thrust self energizing;Wherein, the auxiliary wing of lift (10311)There are one self-enclosed ducted fans for internal at least installation(104).
2. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In the propeller(106)For a variety of dynamic structures such as electric propeller, the dynamic propellers of oil.
3. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In the hybrid lift wing(102)Front and back are respectively set to magnetic-type self interlocking interface male connector(1026)And magnetic Formula self interlocking interface female(1027);The magnetic-type self interlocking interface male connector(1026)With magnetic-type automatic mutual interlocking Mouth female(1027)Size is identical.
4. wanting a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust described in 3 according to right, which is characterized in that The magnetic-type self interlocking interface male connector(1026)With magnetic-type self interlocking interface female(1027)For taper connection.
5. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In the hybrid lift wing(102)Lift main wing can be divided into(1021)And balance empennage(1023)Two parts, respectively It is arranged in hybrid lift wing(102)Front and back;Lift main wing(1021)With balance empennage(1023)Between be reserved with space, The horizontal lifting rudder wing is provided in space(1022);Wherein, lift main wing(1021)There are one self-enclosed culverts for internal at least installation Road fan(104).
6. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In further including vertical tail(105), the vertical tail(105)It is arranged in body(101)Above or below;The vertical end The wing(105)It is arranged in wing both sides;The vertical tail(105)It may be implemented to fold;The vertical tail(105)It installs below There is mobilizable vertical rudder wing(1051).
7. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In the body(101)It is installed with cavity(1002), cavity(1002)Interior installation diagram passes, flies the modules such as control, driving.
8. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In being additionally provided with engine installation position on the compound auxiliary wing of ducted fan thrust self energizing(111), engine installation position (111)Inside it is provided with power plant.
9. a kind of rear single-blade formula combined wing aircraft of double compound auxiliary wings of duct thrust according to claim 1, feature exist In being provided with battery/fuel on the compound auxiliary wing of ducted fan thrust self energizing(1006).
CN201810551432.XA 2018-05-31 2018-05-31 A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts Pending CN108639327A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810551432.XA CN108639327A (en) 2018-05-31 2018-05-31 A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810551432.XA CN108639327A (en) 2018-05-31 2018-05-31 A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts

Publications (1)

Publication Number Publication Date
CN108639327A true CN108639327A (en) 2018-10-12

Family

ID=63758952

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201810551432.XA Pending CN108639327A (en) 2018-05-31 2018-05-31 A kind of rear single-blade formula combined wing aircraft of the compound auxiliary wing of double duct thrusts

Country Status (1)

Country Link
CN (1) CN108639327A (en)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030062443A1 (en) * 2001-10-02 2003-04-03 Joseph Wagner VTOL personal aircraft
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 (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030062443A1 (en) * 2001-10-02 2003-04-03 Joseph Wagner VTOL personal aircraft
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

Similar Documents

Publication Publication Date Title
EP3254962B1 (en) Electric distributed propulsion anti-torque redundant power and control system
EP2991897B1 (en) Vertical takeoff and landing (vtol) air vehicle
EP3401215A1 (en) Multi-copter lift body aircraft with tail pusher
CN206012959U (en) A kind of how culvert vertical take-off and landing unmanned machine
US10131426B2 (en) Aircraft capable of vertical take-off
US9783291B2 (en) Hybrid axial/cross-flow fan multi-rotor aerial vehicle
US20170240274A1 (en) Propulsion system
JP6567054B2 (en) Multi-rotor with inclined wings
CN204452934U (en) The double mode aircraft of rotor, fixed-wing
US9669924B2 (en) Unmanned aerial vehicle
CN101875399B (en) Tilt rotor aircraft adopting parallel coaxial dual rotors
RU141669U1 (en) Vertical takeoff and landing flight
CN107042884A (en) A kind of tilting rotor wing unmanned aerial vehicle
WO2016066131A1 (en) Combined vertical take-off and landing aircraft
CN104918853A (en) Convertible aircraft provided with two ducted rotors at the wing tips and with a horizontal fan in the fuselage
EP2690012A1 (en) Semi-convertible rotorcraft
JP6509835B2 (en) Vertical take-off and landing aircraft
CN103043212A (en) Combined aircraft composed of fixed wing and electric multi-rotor wing
CN103625640A (en) Multi-rotor unmanned aerial vehicle
US20170158325A1 (en) Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor
CN202728576U (en) Transformable composite aircraft formed by fixed wing and electric multi-propeller
CN101643116A (en) Tiltrotor controlled by double-propeller vertical duct
US8857755B2 (en) Vertical/short take-off and landing passenger aircraft
CN104276284B (en) A kind of series type fan rotor aircraft layout
CN106585976B (en) A kind of long endurance aircraft layout of tilting rotor/lift fan high speed

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication
RJ01 Rejection of invention patent application after publication

Application publication date: 20181012