CN108482663A - The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin - Google Patents

The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin Download PDF

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Publication number
CN108482663A
CN108482663A CN201810551036.7A CN201810551036A CN108482663A CN 108482663 A CN108482663 A CN 108482663A CN 201810551036 A CN201810551036 A CN 201810551036A CN 108482663 A CN108482663 A CN 108482663A
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CN
China
Prior art keywords
wing
compound auxiliary
auxiliary wing
aircraft
compound
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Pending
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CN201810551036.7A
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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 CN201810551036.7A priority Critical patent/CN108482663A/en
Publication of CN108482663A publication Critical patent/CN108482663A/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
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/54Varying in area
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C5/00Stabilising surfaces
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C5/00Stabilising surfaces
    • B64C5/06Fins
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02Aircraft characterised by the type or position of power plant
    • B64D27/24Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/10Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means
    • B64C2201/102Deployable wings, e.g. foldable or morphing wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/10Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means
    • B64C2201/108Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means using rotors, or propellers
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Abstract

The present invention is a kind of rear single-blade formula combined wing aircraft of double duct thrusts of band compound auxiliary wing and additional fin, wherein rear single-screw paddle composite wing aircraft includes body, is fixedly mounted on body both sides hybrid lift wing, ducted fan propeller;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 airscrew thrust self energizing is provided with ducted fan propeller, the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed ducted fan, the both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected with hybrid lift wing by the wing hinge of side;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

The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin
Technical field
The present invention relates to a kind of aircraft, the rear single-blade formula of the double duct thrusts of specifically a kind of band compound auxiliary wing and additional fin Combined wing 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, hydrous waters The flat rudder wing can play the role of aerodone under case of emergency, greatly improve the safety of aircraft, the safety of support personnel.
To achieve the goals above, the present invention includes rear single-screw paddle composite wing aircraft, is movably arranged on compound liter The compound auxiliary wing of airscrew thrust self energizing of power aircraft both sides and shipping storehouse;Wherein, rear single-screw paddle composite wing flight Device includes body, is fixedly mounted on body both sides hybrid lift wing, ducted fan propeller;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;Airscrew thrust The front end of the compound auxiliary wing of self energizing is provided with ducted fan propeller, and the compound auxiliary wing of airscrew thrust self energizing is internally provided with The both sides of self-enclosed ducted fan, the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and lead to The wing hinge for crossing side is flexibly connected with hybrid lift wing;The side of additional fin towards body is provided with wing hinge and electricity Liquid gas interface, and be mounted on the outside of the compound auxiliary wing of airscrew thrust self energizing by the way that wing hinge is folding;Electro-hydraulic gas interface With lid, additional fin internal battery/fuel.
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;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 airscrew thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, It is separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing;It is reserved between the auxiliary wing of lift and the auxiliary empennage of balance free Between, the horizontal lifting rudder wing is provided in space;Wherein, at least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.
Further, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing, in engine installation position It is provided with power plant.
Further, the compound auxiliary wing engine installation position installation of airscrew thrust self energizing is that electric propeller or oil are dynamic Propeller.
Further, it is provided with battery/fuel on the compound auxiliary wing of airscrew 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 compound auxiliary wing of airscrew thrust self energizing of the present invention uses hybrid lift, i.e., by designing in aerofoil Self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
3. also adding additional fin on the outside of the compound auxiliary wing of airscrew thrust self energizing in the present invention, flight is improved Lift when device horizontal flight also increases the energy of energy device.
4. 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.
5. the present invention can realize multiple functions using hardware and software platform, modularized design,
6. 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.
7. 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.
8. wing hinge can be passed through between the compound auxiliary wing of the airscrew thrust self energizing of invention and hybrid lift aircraft It is attached, is controlled by hybrid lift aircraft main control unit, and can be by energy such as battery/fuel of aerofoil with electro-hydraulic gas interface Aircraft host is passed to, the flight time is improved.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.It is modular Design, reduces the disposable input of client, reduces buying and operation cost.
9. the compound auxiliary wing of airscrew thrust self energizing of the present invention is in parallel with the auxiliary wing of other hybrid lifts, and passes through machine Wing hinge and electro-hydraulic gas interface are attached, synchronous to be controlled by hybrid lift aircraft main control unit, are expanded again and can be by the wing The energy transmissions such as the battery/fuel in face give aircraft host, improve the flight time.
10. thrust device modularization can very easily realize that repair is replaced.
11. 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.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility!
13. aerofoil type energy device, efficiently uses space.
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;1031, airscrew thrust self energizing The compound auxiliary wing;10311, lift additional fin;10312, auxiliary empennage is balanced;1026, electro-hydraulic gas interface;10261, lid;111, it sends out Motivation installation position;114, additional fin;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, the rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin, including Afterwards single-screw paddle composite wing aircraft, be assemblied in the compound auxiliary wing of airscrew thrust self energizing and additional fin of its wing both sides 114;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, the body 101 is set as deck platform;The hybrid lift wing 102 Built-in self-enclosed ducted fan 104,102 outside of hybrid lift wing are designed with wing hinge 1028;The airscrew thrust The front end of the compound auxiliary wing of self energizing is provided with ducted fan propeller 1063, and the inside of the compound auxiliary wing of airscrew thrust self energizing is set It is equipped with self-enclosed ducted fan 104, the both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface 1036 and machine Wing hinge 1028, and be flexibly connected with hybrid lift wing 102 by the wing hinge of side 1028;The additional fin 114 The side of body 101 is provided with wing hinge 1028 and electro-hydraulic gas interface 1036, and foldable by wing hinge 1028 Be mounted on the outside of the compound auxiliary wing of airscrew thrust self energizing;The electro-hydraulic gas interface 1036 carries lid 10361, additional fin 114 internal batteries/fuel 1006.
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.
Improved as of the invention further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing of lift 10311 with 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 airscrew thrust self energizing;Wherein, it rises At least there are one self-enclosed ducted fans 104 for installation inside the auxiliary wing of power 10311.
As further improvement of the invention, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing 111, power plant is provided in engine installation position 111.
As further improvement of the invention, battery/fuel 1006 is provided on the compound auxiliary wing of airscrew 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 compound auxiliary wing of airscrew thrust self energizing of the present invention uses hybrid lift, i.e., by designing in aerofoil Self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
3. also adding additional fin on the outside of the compound auxiliary wing of airscrew thrust self energizing in the present invention, flight is improved Lift when device horizontal flight also increases the energy of energy device.
4. 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.
5. the present invention can realize multiple functions using hardware and software platform, modularized design,
6. 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.
7. 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.
8. wing hinge can be passed through between the compound auxiliary wing of the airscrew thrust self energizing of invention and hybrid lift aircraft It is attached, is controlled by hybrid lift aircraft main control unit, and can be by energy such as battery/fuel of aerofoil with electro-hydraulic gas interface Aircraft host is passed to, the flight time is improved.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.It is modular Design, reduces the disposable input of client, reduces buying and operation cost.
9. the compound auxiliary wing of airscrew thrust self energizing of the present invention is in parallel with the auxiliary wing of other hybrid lifts, and passes through machine Wing hinge and electro-hydraulic gas interface are attached, synchronous to be controlled by hybrid lift aircraft main control unit, are expanded again and can be by the wing The energy transmissions such as the battery/fuel in face give aircraft host, improve the flight time.
10. thrust device modularization can very easily realize that repair is replaced.
11. 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.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility!
13. aerofoil type energy device, efficiently uses space.
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. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin, which is characterized in that including rear single spiral shell The compound auxiliary wing of the compound rotor aircraft of rotary propeller type, the airscrew thrust self energizing for being assemblied in its wing both sides and additional fin(114);
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, the body(101)It is set as deck platform;The compound liter Power 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 the airscrew thrust self energizing is provided with ducted fan propeller(1063), airscrew thrust The compound auxiliary wing of self energizing is internally provided with self-enclosed ducted fan(104), the both sides of the compound auxiliary wing of airscrew thrust self energizing It is provided with electro-hydraulic gas interface(1036)With wing hinge (1028), and pass through the wing hinge of side (1028) and hybrid lift machine The wing(102)Flexible connection;
The additional fin(114)Towards body(101)Side be provided with wing hinge (1028) and electro-hydraulic gas interface (1036), and be mounted on the outside of the compound auxiliary wing of airscrew thrust self energizing by the way that wing hinge (1028) is folding;Described Electro-hydraulic gas interface(1036)With lid(10361), additional fin(114)Internal battery/fuel(1006);
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. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, It is characterized in that, the propeller(106)For a variety of dynamic structures such as electric propeller, the dynamic propellers of oil.
3. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, 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.
4. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band described in the 3 compound auxiliary wing and additional fin is wanted according to right, 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.
5. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, It is characterized in that, further includes vertical tail(105), the vertical tail(105)It is arranged in body(101)Above or below;It is described Vertical tail(105)It is arranged in wing both sides;The vertical tail(105)It may be implemented to fold;The vertical tail(105)Afterwards Face is equipped with mobilizable vertical rudder wing(1051).
6. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, 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.
7. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, It is characterized in that, the compound auxiliary wing of the airscrew 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 airscrew thrust self energizing;The auxiliary wing of lift(10311)With Balance auxiliary empennage(10312)Between be reserved with space, the horizontal lifting rudder wing is provided in space(1022);Wherein, the auxiliary wing of lift (10311)There are one self-enclosed ducted fans for internal at least installation(104).
8. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, It is characterized in that, engine installation position is additionally provided on the compound auxiliary wing of the airscrew thrust self energizing(111), engine installation Position(111)Installation is electric propeller or the dynamic propeller of oil.
9. the rear single-blade formula combined wing aircraft of the double duct thrusts of the band according to claim 1 compound auxiliary wing and additional fin, It is characterized in that, battery/fuel is provided on the compound auxiliary wing of the airscrew thrust self energizing(1006).
CN201810551036.7A 2018-05-31 2018-05-31 The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin Pending CN108482663A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810551036.7A CN108482663A (en) 2018-05-31 2018-05-31 The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin

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Application Number Priority Date Filing Date Title
CN201810551036.7A CN108482663A (en) 2018-05-31 2018-05-31 The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin

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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

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