CN108945415A - With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft - Google Patents
With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft Download PDFInfo
- Publication number
- CN108945415A CN108945415A CN201810544332.4A CN201810544332A CN108945415A CN 108945415 A CN108945415 A CN 108945415A CN 201810544332 A CN201810544332 A CN 201810544332A CN 108945415 A CN108945415 A CN 108945415A
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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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention be it is a kind of with the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft, wherein body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, the outside design of hybrid lift wing have wing hinge；Turbofan propeller is provided with 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 by wing hinge with hybrid lift wing, 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 shipping 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, highly-safe the features such as, the auxiliary wing uses hybrid lift, it is ensured that the adaptation range 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 cargo aircraft belongs to aircraft equipment technology field.
Background technique
Existing aircraft is broadly divided into fixed-wing and vertically taking off and landing flyer (such as helicopter and more rotors) two major classes.When
So also there is this product of VTOL fixed-wing.Traditional fixed-wing have the advantages that flying speed is fast, low energy consumption, but have
It is not connected to before and after main wing and tailplane, wing structure intensity is not high, is easily damaged, and landing requires high, landing distance disadvantage；
Traditional vertically taking off and landing flyer has the advantages that landing is convenient, but has that energy consumption is high, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the disadvantages of air crash；Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
The disadvantages of controllability when flat flight is not satisfactory, and that there is flight resistances is big, and energy consumption is high, and safety coefficient is not still high.
Summary of the invention
In view of the above-mentioned problems of the prior art, the present invention not only has landing apart from short, flying speed is fast, wing knot
Structure intensity height, wing can be with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area, feelings of meeting an urgent need
It can play the role of aerodone under condition, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.
To achieve the goals above, the present invention by the compound rotor aircraft of back pressure formula, be assemblied in the turbofan of its wing two 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 two sides hybrid lift wing, additional fin and shipping storehouse；Wherein, wherein the body is set as deck platform；Machine
Video camera, self-enclosed ducted fan built in the hybrid lift wing are provided in front of body, hybrid lift wing outside is set
In respect of wing hinge；Turbofan propeller, turbofan thrust are provided with below the compound auxiliary wing of turbofan thrust self energizing
The compound auxiliary wing of self energizing is internally provided with self-enclosed ducted fan, and the one or both sides of the compound auxiliary wing of turbofan thrust self energizing are set
It is equipped with electro-hydraulic gas interface and wing hinge, and is flexibly connected by wing hinge with hybrid lift wing, wherein described is electro-hydraulic
Gas interface has lid, and the compound auxiliary wing of turbofan 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 turbofan thrust self energizing；At least be equipped with inside the auxiliary wing of lift one it is self-enclosed
Ducted fan.The side of additional fin towards body is provided with wing hinge, and by wing hinge it is folding be mounted on it is compound
On the outside of lifting wing；Additional fin internal battery/fuel；The surface of additional fin is provided with solar panel.Shipping storehouse is mounted on
The lower section of body.
Further, hybrid lift wing can be divided into lift main wing and balance two parts of empennage, be separately positioned on compound
The front and back of lifting wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Its
In, a self-enclosed ducted fan is at least installed inside lift main wing.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity.
Further, 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 device, the power device is turbofan propeller.
Further, battery/fuel 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, obstacle avoidance ability are strong, wing structure intensity is high, machine
The wing can be with energy storage, the features such as low energy consumption of flying.Self-enclosed vertical ducted fan is relied on, aircraft can be provided in horizontal flight
Additional maneuverability, realize moment change of flight posture and track super maneuver ability.
2. the Waverider wing that the present invention is very large, can play the role of certain paraglider, gravity acceleration is substantially reduced
Degree greatly improves safety coefficient, cooperates the control function of the hydroplane wing and the vertical rudder wing and the aerofoil envelope of self-enclosed ducted fan
Function is closed, even if lift ducted fan and horizontal propeller damage simultaneously, the forced landing of aerodone formula is also able to achieve, greatly improves
The safety of aircraft has ensured the safety of personnel and goods and materials.
3. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
4. the present invention using two sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
5. the present invention also has successive magnetic-type self interlocking interface, the cluster of aircraft is facilitated to fly, into one
Step reduces power consumption when cluster flight.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, energy
Realize the flight of long range, the cluster flight of only aircraft does not provide the low-power consumption scheme of clustering, it might even be possible to realize
Air rescue between aircraft, i.e., preceding aircraft take off faulty aircraft dragging below, realize not seen before fly
Phenomenon is rescued mutually between row device.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable investment of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve the flexibility of complete machine.
10. 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 has 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 are used, and have saved cost.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is side view of the invention；
Fig. 3 is rearview of the invention；
Fig. 4 is plan view of the invention；
Fig. 5 is oblique view of the invention；
In figure: 101: body；102: hybrid lift wing；104: self-enclosed ducted fan；105: vertical tail；1051. vertical
The rudder wing；107: Energy Management System；1021: lift main wing；1022: the horizontal lifting rudder wing；1023: balance empennage；1028: wing
Hinge；1001: socket；1002: cavity；1003: fixation hole；1006: battery/fuel；108: video camera；1026: it is magnetic-type from
Move mutual lock interface male connector；1027: magnetic-type self interlocking interface female；1031, the compound auxiliary wing of 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；114, additional fin；113, shipping storehouse..
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figures 1 to 5, band with the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft, it is special
Sign is, 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 two sides, additional
The wing 114 and shipping storehouse 113 form；Wherein, the no compound rotor aircraft of back pressure formula includes body 101, is fixedly mounted on
101 two sides hybrid lift wing 102 of body；Wherein, wherein the body 101 is set as deck platform；Before body 101
Side is provided with video camera 108, self-enclosed ducted fan 104 built in the hybrid lift wing 102, hybrid lift wing 102
Outside design has wing hinge (1028)；Turbofan propulsion is provided with below the compound auxiliary wing of turbofan thrust self energizing
Device 1064, the compound auxiliary wing of turbofan thrust self energizing are internally provided with self-enclosed ducted fan 104, and turbofan thrust self energizing is compound
The one or both sides of the auxiliary wing are provided with electro-hydraulic gas interface 1036 and wing hinge (1028), and by wing hinge (1028) and multiple
It closes lifting wing 102 to be flexibly connected, wherein the electro-hydraulic gas interface 1036 has lid 10361, and the turbofan thrust is certainly
The auxiliary wing 10311 of lift and auxiliary 10,312 two parts of empennage of balance can be divided by energizing the compound auxiliary wing, be separately positioned on turbofan thrust
The front and back of the compound auxiliary wing of self energizing；One self-enclosed ducted fan 104 is at least installed inside the auxiliary wing 10311 of lift.It is additional
The side of the wing 114 towards body 101 is provided with wing hinge (1028), and is mounted on by the way that wing hinge (1028) are folding
102 outside of hybrid lift wing；114 internal batteries of additional fin/fuel 1006；The surface of additional fin 114 is provided with solar-electricity
Pond plate 1141, shipping storehouse 113 are 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, be at least equipped with inside lift main wing 1,021 one it is self-enclosed
Ducted fan 104.
Improved as of the invention further, body 101 is installed with cavity 1002, in cavity 1002 installation diagram pass, fly control,
The modules such as driving.
As further improvement of the invention, engine installation position is additionally provided on the compound auxiliary wing of turbofan thrust self energizing
111, power device is provided in engine installation position 111, the power device 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, obstacle avoidance ability are strong, wing structure intensity is high, machine
The wing can be with energy storage, the features such as low energy consumption of flying.Self-enclosed vertical ducted fan is relied on, aircraft can be provided in horizontal flight
Additional maneuverability, realize moment change of flight posture and track super maneuver ability.
2. the Waverider wing that the present invention is very large, can play the role of certain paraglider, gravity acceleration is substantially reduced
Degree greatly improves safety coefficient, cooperates the control function of the hydroplane wing and the vertical rudder wing and the aerofoil envelope of self-enclosed ducted fan
Function is closed, even if lift ducted fan and horizontal propeller damage simultaneously, the forced landing of aerodone formula is also able to achieve, greatly improves
The safety of aircraft has ensured the safety of personnel and goods and materials.
3. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
4. the present invention using two sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
5. the present invention also has successive magnetic-type self interlocking interface, the cluster of aircraft is facilitated to fly, into one
Step reduces power consumption when cluster flight.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, energy
Realize the flight of long range, the cluster flight of only aircraft does not provide the low-power consumption scheme of clustering, it might even be possible to realize
Air rescue between aircraft, i.e., preceding aircraft take off faulty aircraft dragging below, realize not seen before fly
Phenomenon is rescued mutually between row device.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable investment of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve the flexibility of complete machine.
10. 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 are used, and have saved cost.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment, should belong to the scope of the present invention.
Claims (5)
1. with the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft, which is characterized in that by pusher
The compound rotor aircraft of power formula, the compound auxiliary wing of turbofan thrust self energizing, additional fin (114) and the shipping storehouse for being assemblied in its wing two sides
(113) it forms；
Wherein, the no compound rotor aircraft of back pressure formula includes body (101), to be fixedly mounted on body (101) two sides multiple
It closes lifting wing (102)；Wherein, wherein the body (101) is set as deck platform；Body is provided in front of (101)
Video camera (108), self-enclosed ducted fan (104) built in the hybrid lift wing (102), hybrid lift wing (102)
Outside design has wing hinge (1028)；
It is provided with turbofan propeller (1064) below the compound auxiliary wing of turbofan thrust self energizing, 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) and wing hinge (1028), and passes through wing hinge (1028) and hybrid lift wing
(102) it is flexibly connected, wherein the electro-hydraulic gas interface (1036) has lid (10361), the turbofan thrust self energizing
The compound auxiliary wing can be divided into the auxiliary wing of lift (10311) and auxiliary (10312) two parts of empennage of balance, be separately positioned on turbofan thrust
The front and back of the compound auxiliary wing of self energizing；A self-enclosed ducted fan (104) is at least installed inside the auxiliary wing of lift (10311)；
The side of additional fin (114) towards the body (101) is provided with wing hinge (1028), and passes through wing hinge
(1028) folding to be mounted on the outside of hybrid lift wing (102)；Additional fin (114) internal battery/fuel (1006)；
The shipping storehouse (113) is mounted on the lower section of body (101).
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) can be divided into lift main wing (1021) and balance empennage (1023) two
A part is separately positioned on the front and back of hybrid lift wing (102)；Between lift main wing (1021) and balance empennage (1023)
It is reserved with space, the horizontal lifting rudder wing (1022) is provided in space；Wherein, one is at least equipped with inside lift main wing (1021)
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) is installed with cavity (1002), and the interior installation diagram of cavity (1002) 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 (111), engine on the compound auxiliary wing of turbofan thrust self energizing
Power device is provided in installation position (111), the power device 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 (1006) on the compound auxiliary wing of turbofan thrust self energizing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544332.4A CN108945415A (en) | 2018-05-31 | 2018-05-31 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544332.4A CN108945415A (en) | 2018-05-31 | 2018-05-31 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108945415A true CN108945415A (en) | 2018-12-07 |
Family
ID=64492658
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810544332.4A Pending CN108945415A (en) | 2018-05-31 | 2018-05-31 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing cargo aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN108945415A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
-
2018
- 2018-05-31 CN CN201810544332.4A patent/CN108945415A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
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| PB01 | Publication | ||
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Application publication date: 20181207 |