CN108773482A - With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle - Google Patents
With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle Download PDFInfo
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- CN108773482A CN108773482A CN201810544373.3A CN201810544373A CN108773482A CN 108773482 A CN108773482 A CN 108773482A CN 201810544373 A CN201810544373 A CN 201810544373A CN 108773482 A CN108773482 A CN 108773482A
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- Prior art keywords
- wing
- turbofan
- compound auxiliary
- lift
- compound
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention be one with the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle, 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；It is provided with turbofan propeller below the compound auxiliary wing of turbofan thrust self energizing, 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 it is flexibly connected with hybrid lift wing by wing hinge, the side of additional fin towards body is provided with wing hinge, and is mounted on the outside of hybrid lift wing by the way that wing hinge is folding；The lower section present invention that manned storehouse is mounted on body 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
Technical field
It is specifically a kind of compound without back pressure formula with the compound auxiliary wing of turbofan and additional fin the present invention relates to a kind of aircraft
Wing manned vehicle 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 the compound rotor aircraft of back pressure formula, be assemblied in the turbofan of its wing both sides
The compound auxiliary wing of thrust self energizing and additional fin composition；Wherein, the compound rotor aircraft of back pressure formula includes body, fixed peace
Mounted in body both sides hybrid lift wing, additional fin and manned storehouse；Wherein, wherein the body is set as deck platform, institute
Self-enclosed ducted fan built in the hybrid lift wing stated, hybrid lift wing outside are designed with wing hinge；The turbofan
Turbofan propeller, the inside setting of the compound auxiliary wing of turbofan thrust self energizing are provided with below the compound auxiliary wing of thrust self energizing
There are self-enclosed ducted fan, the one or both sides of the compound auxiliary wing of turbofan thrust self energizing to be provided with electro-hydraulic gas interface and wing hinge
Chain, and be flexibly connected with hybrid lift wing by wing hinge, wherein the electro-hydraulic gas interface carries lid, described
The compound auxiliary wing of turbofan thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, be separately positioned on turbofan thrust
The front and back of the compound auxiliary wing of self energizing；At least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.Additional fin is towards machine
The side of body is provided with wing hinge, and is mounted on the outside of hybrid lift wing by the way that wing hinge is folding；In additional fin
Set battery/fuel；The surface of additional fin is provided with solar panel.Manned storehouse is mounted on the lower section of body.
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. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
11. aerofoil type energy device, efficiently uses space.
12. additional fin carries solar energy equipment, increase the energy of complete machine, energy conservation and environmental protection!
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；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；1026：Magnetic-type self interlocking interface is public
Head；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, turbofan pushes away
Into device；114, additional fin；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, band with the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle,
It is characterized in that, by the compound rotor aircraft of no back pressure formula, the compound auxiliary wing of turbofan thrust self energizing that is assemblied in its wing both sides,
Additional fin 114 and manned storehouse 112 form；Wherein, the no compound rotor aircraft of back pressure formula includes body 101, fixed peace
Mounted in 101 both sides hybrid lift wing 102 of body；Wherein, wherein the body 101 is set as deck platform, and described answers
Self-enclosed ducted fan 104 built in lifting wing 102 is closed, 102 outside of hybrid lift wing is designed with wing hinge (1028)；Institute
It is provided with turbofan propeller 1064 below the compound auxiliary wing of turbofan thrust self energizing stated, turbofan thrust self energizing is compound auxiliary
The wing is internally provided with self-enclosed ducted fan 104, and 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),
In, the electro-hydraulic gas interface 1036 carries lid 10361, and it is auxiliary that the compound auxiliary wing of turbofan thrust self energizing can be divided into lift
The wing 10311 and auxiliary 10,312 two parts of empennage of balance, are separately positioned on the front and back of the compound auxiliary wing of turbofan thrust self energizing；
At least there are one self-enclosed ducted fans 104 for installation inside the auxiliary wing of lift 10311.The side of additional fin 114 towards body 101 is set
It is equipped with wing hinge (1028), and 102 outside of hybrid lift wing is mounted on by the way that wing hinge (1028) is folding；It is additional
114 internal batteries of the wing/fuel 1006；The surface of additional fin 114 is provided with solar panel 1141, and manned storehouse 112 is mounted on
The lower section of body 101.
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. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
11. aerofoil type energy device, efficiently uses space.
12. 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 (5)
1. it is a kind of with the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle, which is characterized in that by rear
The compound rotor aircraft of thrust type, the compound auxiliary wing of turbofan thrust self energizing for being assemblied in its wing both sides, additional fin（114）With it is manned
Storehouse（112）Composition；
Wherein, the no compound rotor aircraft of back pressure formula includes body（101）, be fixedly mounted on body（101）Both sides are multiple
Close lifting wing（102）；Wherein, wherein the body（101）It is set as deck platform；The hybrid lift 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 turbofan thrust self energizing
The compound auxiliary wing can be divided into the auxiliary wing of lift（10311）And the auxiliary empennage of balance（10312）Two parts, are separately positioned on turbofan thrust
The front and back of the compound auxiliary wing of self energizing；The auxiliary wing of lift（10311）There are one self-enclosed ducted fans for internal at least installation（104）；
The additional fin（114）Towards body（101）Side be provided with wing hinge (1028), and pass through wing hinge
(1028) folding to be mounted on hybrid lift wing（102）Outside；Additional fin（114）Internal battery/fuel（1006）；
The manned storehouse（112）Mounted on body（101）Lower section.
2. according to claim 1 a kind of manned without back pressure formula composite wing with the compound auxiliary wing of turbofan and additional fin
Device, which is characterized in that the hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two
A part is separately positioned on hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between
It is reserved with space, the horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）Inside is at least equipped with one
A self-enclosed ducted fan（104）.
3. according to claim 1 a kind of manned without back pressure formula composite wing with the compound auxiliary wing of turbofan and additional fin
Device, which is characterized in that the body（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies control, driving
Etc. modules.
4. according to claim 1 a kind of manned without back pressure formula composite wing with the compound auxiliary wing of turbofan and additional fin
Device, which is characterized in that be additionally provided with engine installation position on the compound auxiliary wing of turbofan thrust self energizing（111）, engine
Installation position（111）It is inside provided with power plant, the power plant is turbofan propeller.
5. according to claim 1 a kind of manned without back pressure formula composite wing with the compound auxiliary wing of turbofan and additional fin
Device, which is characterized in that be provided with battery/fuel on the compound auxiliary wing of turbofan thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544373.3A CN108773482A (en) | 2018-05-31 | 2018-05-31 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544373.3A CN108773482A (en) | 2018-05-31 | 2018-05-31 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108773482A true CN108773482A (en) | 2018-11-09 |
Family
ID=64028180
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810544373.3A Pending CN108773482A (en) | 2018-05-31 | 2018-05-31 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108773482A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205131649U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Multi -axis aircraft |
| CN206012959U (en) * | 2016-09-08 | 2017-03-15 | 朗星无人机系统有限公司 | A kind of how culvert vertical take-off and landing unmanned machine |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| CN107856838A (en) * | 2017-11-10 | 2018-03-30 | 肇庆市高新区晓靖科技有限公司 | A kind of unmanned plane wingfold mechanism |
-
2018
- 2018-05-31 CN CN201810544373.3A patent/CN108773482A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205131649U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Multi -axis aircraft |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| CN206012959U (en) * | 2016-09-08 | 2017-03-15 | 朗星无人机系统有限公司 | A kind of how culvert vertical take-off and landing unmanned machine |
| CN107856838A (en) * | 2017-11-10 | 2018-03-30 | 肇庆市高新区晓靖科技有限公司 | A kind of unmanned plane wingfold mechanism |
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Application publication date: 20181109 |