CN108466692A - The manned aircraft of rear single ducted fan formula composite wing with the compound auxiliary wing and additional fin - Google Patents
The manned aircraft of rear single ducted fan formula composite wing with the compound auxiliary wing and additional fin Download PDFInfo
- Publication number
- CN108466692A CN108466692A CN201810544304.2A CN201810544304A CN108466692A CN 108466692 A CN108466692 A CN 108466692A CN 201810544304 A CN201810544304 A CN 201810544304A CN 108466692 A CN108466692 A CN 108466692A
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- Prior art keywords
- wing
- ducted fan
- additional fin
- compound
- manned
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- 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
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of compound auxiliary wing of band and the manned aircraft of rear single ducted fan formula composite wing of additional fin, including the compound rotor aircraft of rear single ducted fan formula, be assemblied in its wing both sides without the auxiliary wing of thrust self energizing, additional fin and manned storehouse；Wherein, additional fin is folding on the outside of the auxiliary wing of no thrust self energizing by wing hinge, and manned storehouse is mounted on the lower section of body.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, flight low energy consumption, the hang time is long the features such as, the hybrid lift wing of large area, it can play the role of aerodone under case of emergency, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.
Description
Technical field
The present invention relates to a kind of aircraft, rear single ducted fan formula of the compound auxiliary wing of specifically a kind of band and additional fin is multiple
The manned aircraft of the wing is closed, aircraft equipment technology field is belonged to.
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.Hair
Bright 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 structure is strong
Degree is high, wing can coordinate hydroplane with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area
The 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 the compound rotor aircraft of rear single ducted fan formula, is assemblied in its wing two
Side without the auxiliary wing of thrust self energizing, additional fin and manned storehouse；Wherein, rear single compound rotor aircraft of ducted fan formula includes
Body is fixedly mounted on body both sides hybrid lift wing, propeller；Wherein, the body is set as deck platform；It is described
Hybrid lift wing built in self-enclosed ducted fan, be designed with wing hinge on the outside of hybrid lift wing；Propeller is duct
Fan propeller；Self-enclosed ducted fan, the side or two of no auxiliary wing of thrust self energizing are provided in the no auxiliary wing of thrust self energizing
Side is provided with electro-hydraulic gas interface and wing hinge, and is flexibly connected with hybrid lift wing by wing hinge；No thrust confession
The auxiliary wing of energy can be divided into lift aileron and auxiliary two parts of empennage of balance, be separately positioned on before and after no auxiliary wing of thrust self energizing
Square, at least there are one self-enclosed ducted fans for installation inside lift aileron；Additional fin passes through the folding installation of wing hinge
On the outside of no auxiliary wing of thrust self energizing；Fuel built in additional fin or battery.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, 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 set as deck platform；The mounting hole of the regular arrangement in deck platform both sides；The first
It is designed with socket on plate platform；The socket is female or male.
Further, it is provided with video camera in front of body, video camera is monopod video camera.
Further, electro-hydraulic gas interface carries lid.
Further, it is provided with battery/fuel on the no auxiliary wing of thrust self energizing.
Further, additional wing surface is provided with solar panel.
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, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2. also adding additional fin on the outside of no auxiliary wing of thrust self energizing in the present invention, aircraft horizontal flight is improved
When lift, also increase the energy of energy device.
3, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device 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.
4. can lead between the modularization ducted fan drive-in hybrid lift aileron and hybrid lift aircraft of invention
Cross wing hinge and electro-hydraulic gas interface be attached, by hybrid lift aircraft main control unit control, and can by the battery of aerofoil/
The energy transmissions such as fuel give aircraft host, improve the flight time.Performance may be implemented by superimposion lift aileron
Multiplication.Modular design reduces the disposable input of client, reduces buying and operation cost.
5. the modularization ducted fan drive-in hybrid lift aileron of the present invention with other hybrid lifts ailerons phases simultaneously
Connection, 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 opens up again
Zhan Bingke gives the energy transmissions such as battery/fuel of aerofoil to aircraft host, improves the flight time.
6. thrust device modularization can very easily realize that repair is replaced.
7. in the present invention, additional fin side is provided with electro-hydraulic gas interface, additional fin and hybrid lift aircraft master are realized
Energy intercommunication between aerofoil, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
8. additional fin carries solar energy equipment, increase the energy of complete machine, energy conservation and environmental protection！
9. aerofoil type energy device, efficiently uses space.
10. 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；
1031, without the auxiliary wing of thrust self energizing；10311, lift aileron；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；
10361, lid；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 Figure 1, including the compound rotor aircraft of rear list ducted fan formula, being assemblied in being confessed without thrust for its wing both sides
It can the auxiliary wing, additional fin 114 and manned storehouse 112；
Wherein, described rear single compound rotor aircraft of ducted fan formula includes body 101, to be fixedly mounted on 101 both sides of body multiple
Close lifting wing 102, propeller 106；Wherein, the body 101 is set as deck platform；The hybrid lift wing
Self-enclosed ducted fan 104 built in 102,102 outside of hybrid lift wing are designed with wing hinge 1028；Propeller 106 is to contain
Road fan propeller；It is described without being provided with self-enclosed ducted fan 104, no auxiliary wing of thrust self energizing in the auxiliary wing of thrust self energizing
One or both sides be provided with electro-hydraulic gas interface 1036 and wing hinge (1028), and pass through wing hinge (1028) and compound liter
Power wing 102 is flexibly connected；The no auxiliary wing of thrust self energizing can be divided into lift aileron 10311 and auxiliary 10312 liang of the empennage of balance
A part, is separately positioned on the front and back of no auxiliary wing of thrust self energizing, inside lift aileron 10311 at least installation there are one from
Close ducted fan 104；The additional fin 114 is folding auxiliary mounted on no thrust self energizing by wing hinge (1028)
On the outside of the wing；Fuel or battery built in the additional fin 114.Manned storehouse 112 is mounted on the lower section of body 101.
As further improvement of the invention, no hybrid lift wing 102 can be divided into lift main wing 1021 and balance tail
1,023 two parts of the wing, are separately positioned on the front and back of hybrid lift wing 102；Lift main wing 1021 with balance empennage 1023 it
Between be reserved with space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, there are one at least being installed inside lift main wing 1021
Self-enclosed ducted fan 104.
As further improvement of the invention, without further including vertical tail 105, the setting of the vertical tail 105 is in body
Above or below in the of 101；The vertical tail 105 is arranged in wing both sides；The vertical tail 105 may be implemented to fold；It is described
Mobilizable vertical rudder wing 1051 is installed behind vertical tail 105.
As further improvement of the invention, inorganic body 101 is set as deck platform；There are rule in the deck platform both sides
The mounting hole 1003 then arranged；Socket 1001 is designed in the deck platform；The socket 1001 is female or male.
As further improvement of the invention, no electro-hydraulic gas interface 1036 carries lid 10361.
As further improvement of the invention, 101 front of inorganic body is provided with video camera 108, and video camera 108 is taken the photograph for holder
Camera.
As further improvement of the invention, no electro-hydraulic gas interface 1036 carries lid 10361.
It is improved as of the invention further, without being provided with battery/fuel 1006 on no auxiliary wing of thrust self energizing.
As further improvement of the invention, 114 surface of no additional fin is provided with solar panel 1141.
It is improved as of the invention further, without being provided with battery/fuel 1006 on the compound auxiliary wing of no thrust self energizing.
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and 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, additional fin is also added on the outside of no auxiliary wing of thrust self energizing in the present invention, improves aircraft level and flies
Lift when row also increases the energy of energy device.
3, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device 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.
4. can lead between the modularization ducted fan drive-in hybrid lift aileron and hybrid lift aircraft of invention
Cross wing hinge and electro-hydraulic gas interface be attached, by hybrid lift aircraft main control unit control, and can by the battery of aerofoil/
The energy transmissions such as fuel give aircraft host, improve the flight time.Performance may be implemented by superimposion lift aileron
Multiplication.Modular design reduces the disposable input of client, reduces buying and operation cost.
5. the modularization ducted fan drive-in hybrid lift aileron of the present invention with other hybrid lifts ailerons phases simultaneously
Connection, 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 opens up again
Zhan Bingke gives the energy transmissions such as battery/fuel of aerofoil to aircraft host, improves the flight time.
6. thrust device modularization can very easily realize that repair is replaced.
7. in the present invention, additional fin side is provided with electro-hydraulic gas interface, additional fin and hybrid lift aircraft master are realized
Energy intercommunication between aerofoil, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
8. additional fin carries solar energy equipment, increase the energy of complete machine, energy conservation and environmental protection！
9. aerofoil type energy device, efficiently uses space.
10. 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, are within the scope of protection of the invention.
Claims (10)
1. a kind of manned aircraft of rear single ducted fan formula composite wing of the band compound auxiliary wing and additional fin, which is characterized in that including rear
The compound rotor aircraft of single ducted fan formula, be assemblied in its wing both sides without the auxiliary wing of thrust self energizing, additional fin（114）With it is manned
Storehouse（112）；
Wherein, rear single compound rotor aircraft of ducted fan formula includes body（101）, be fixedly mounted on body（101）Two
Side hybrid lift wing（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；Described is compound
Lifting wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
(1028)；Propeller（106）For ducted fan propeller；
It is described without being provided with self-enclosed ducted fan in the auxiliary wing of thrust self energizing（104）, the side of no auxiliary wing of thrust self energizing
Or both sides are provided with electro-hydraulic gas interface（1036）With wing hinge (1028), and pass through wing hinge (1028) and hybrid lift machine
The wing（102）Flexible connection；The no auxiliary wing of thrust self energizing can be divided into lift aileron（10311）And the auxiliary empennage of balance（10312）
Two parts are separately positioned on the front and back of no auxiliary wing of thrust self energizing, lift aileron（10311）Inside is at least equipped with one
A self-enclosed ducted fan（104）；
The additional fin（114）It is folding on the outside of the auxiliary wing of no thrust self energizing by wing hinge (1028)；Institute
The additional fin stated（114）Built-in fuel or battery；
The manned storehouse（112）Mounted on body（101）Lower section.
2. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, 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. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, which is characterized in that further include vertical tail（105）, the vertical tail（105）It is arranged in body（101）Above or below；
The vertical tail（105）It is arranged in wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail
（105）Mobilizable vertical rudder wing is installed below（1051）.
4. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, which is characterized in that the body（101）It is set as deck platform；The regular arrangement in deck platform both sides is consolidated
Determine hole（1003）；It is designed with socket in the deck platform（1001）；The socket（1001）For female or male.
5. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, which is characterized in that the electro-hydraulic gas interface（1036）With lid（10361）.
6. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, which is characterized in that the body（101）Front is provided with video camera（108）, video camera（108）For monopod video camera.
7. a kind of band according to claim 1 is without the compound rotor aircraft of rear single ducted fan formula for pushing away the compound auxiliary wing, special
Sign is, the electro-hydraulic gas interface（1036）With lid（10361）.
8. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, which is characterized in that be provided with battery/fuel on the no auxiliary wing of thrust self energizing（1006）.
9. the compound auxiliary wing of a kind of band according to claim 1 and rear single ducted fan formula composite wing of additional fin is manned flies
Machine, which is characterized in that the additional fin（114）Surface is provided with solar panel（1141）.
10. a kind of band according to claim 1 is without the compound rotor aircraft of rear single ducted fan formula for pushing away the compound auxiliary wing, special
Sign is, battery/fuel is provided on the no compound auxiliary wing of thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544304.2A CN108466692A (en) | 2018-05-31 | 2018-05-31 | The manned aircraft of rear single ducted fan formula composite wing with the compound auxiliary wing and additional fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544304.2A CN108466692A (en) | 2018-05-31 | 2018-05-31 | The manned aircraft of rear single ducted fan formula composite wing with the compound auxiliary wing and additional fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108466692A true CN108466692A (en) | 2018-08-31 |
Family
ID=63260604
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810544304.2A Pending CN108466692A (en) | 2018-05-31 | 2018-05-31 | The manned aircraft of rear single ducted fan formula composite wing with the compound auxiliary wing and additional fin |
Country Status (1)
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113165551A (en) * | 2018-11-06 | 2021-07-23 | Wing航空有限责任公司 | Adjusting power communication for charging of unmanned aerial vehicle |
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| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113165551A (en) * | 2018-11-06 | 2021-07-23 | Wing航空有限责任公司 | Adjusting power communication for charging of unmanned aerial vehicle |
| CN113165551B (en) * | 2018-11-06 | 2024-04-16 | Wing航空有限责任公司 | Power communication to regulate charging of unmanned aerial vehicle |
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Application publication date: 20180831 |