CN108657424A - Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust - Google Patents
Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust Download PDFInfo
- Publication number
- CN108657424A CN108657424A CN201810546573.2A CN201810546573A CN108657424A CN 108657424 A CN108657424 A CN 108657424A CN 201810546573 A CN201810546573 A CN 201810546573A CN 108657424 A CN108657424 A CN 108657424A
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- CN
- China
- Prior art keywords
- wing
- ducted fan
- airscrew thrust
- lift
- compound auxiliary
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
Abstract
The present invention is a kind of rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust, wherein the rear list compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on body both sides hybrid lift wing and shipping storehouse composition；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；The front end of the compound auxiliary wing of airscrew thrust self energizing is provided with screw propeller, the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed ducted fan, the one or both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and be flexibly connected with hybrid lift wing by wing hinge, shipping 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, 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
The present invention relates to a kind of aircraft, specifically a kind of rear single ducted fan formula with the compound auxiliary wing of airscrew thrust is multiple
Wing cargo aircraft 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.
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 rear single ducted fan formula, be assemblied in the spiral shell of its wing both sides
Revolve the compound auxiliary wing of paddle thrust self energizing and shipping storehouse composition；Wherein, rear single compound rotor aircraft of ducted fan formula includes
Body is fixedly mounted on body）Both sides hybrid lift wing, propeller；Wherein, wherein it is flat that the body is set as deck
Platform；Self-enclosed ducted fan built in the hybrid lift wing, hybrid lift wing outside are designed with wing hinge；Propeller
For ducted fan propeller；The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with screw propeller, spiral
The compound auxiliary wing of paddle thrust self energizing is internally provided with self-enclosed ducted fan, the side of the compound auxiliary wing of airscrew thrust self energizing
Or both sides are provided with electro-hydraulic gas interface and wing hinge, and be flexibly connected with hybrid lift wing by wing hinge, wherein institute
The electro-hydraulic gas interface stated carries lid, and the compound auxiliary wing of the airscrew thrust self energizing can be divided into the auxiliary wing of lift and balance is auxiliary
Two parts of empennage, are separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing；The auxiliary wing of lift and the auxiliary empennage of balance
Between be reserved with space, the horizontal lifting rudder wing is provided in space；Wherein, at least there are one self-enclosed for installation inside the auxiliary wing of lift
Ducted fan, shipping storehouse are mounted on the lower section of body.
Further, hybrid lift wing front and back are respectively set to magnetic-type self interlocking interface male connector and magnetic-type self interlocking
Interface female；The 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（It is taper connection with magnetic-type self interlocking interface female.
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on hybrid lift
The front and back of wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Wherein,
At least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, 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 airscrew thrust self energizing, is arranged in engine installation position
Dynamic device, the power plant are screw 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 auxiliary wing of modularization ducted fan drive-in hybrid lift of the present invention uses hybrid lift, i.e., by designing in aerofoil
Interior self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
2. the Waverider wing that the present invention is very large, can play the role of certain paraglider, substantially reduce acceleration of gravity, greatly
Width improves safety coefficient, and the aerofoil of the control function and self-enclosed ducted fan that coordinate the hydroplane wing and the vertical rudder wing closes work(
Can, even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously, greatly improve flight
The safety of device 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, further dropped
Power consumption when low cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with
The flight of long range, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize flight
Air rescue between device, i.e., preceding aircraft take off faulty aircraft dragging below, realize aircraft not seen before
Between rescue phenomenon mutually.
6. wing can be passed through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/fuel etc. of aerofoil
Energy transmission gives aircraft host, improves the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.Module
The design of change 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 leads to
It crosses wing hinge and electro-hydraulic gas interface is attached, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again and can
The energy transmissions such as battery/fuel by aerofoil give 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, the auxiliary wing and hybrid lift aircraft main wing are realized
Energy intercommunication between face, 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.
The present invention uses modularized design, compound different types of machines to use, and has saved cost.
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, the auxiliary wing of lift；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；10361, lid；111, start
Machine installation position；1062, screw propeller；113, shipping storehouse.
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, a kind of rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust, feature
It is, by the compound rotor aircraft of rear single ducted fan formula, is assemblied in the compound auxiliary wing of airscrew thrust self energizing of its wing both sides
And shipping storehouse 113 forms；Wherein, rear single compound rotor aircraft of ducted fan formula includes body 101, is fixedly mounted on
101 both sides hybrid lift wing 102 of body, propeller 106；Wherein, wherein the body 101 is set as deck platform；Institute
Self-enclosed ducted fan 104 built in the hybrid lift wing 102 stated, 102 outside of hybrid lift wing are designed with wing hinge
1028；Propeller 106 is ducted fan propeller；The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with spiral
Paddle propeller 1062, the compound auxiliary wing of airscrew thrust self energizing are internally provided with self-enclosed ducted fan 104, airscrew thrust
The one or both sides of the compound auxiliary wing of self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge 1028, and pass through wing hinge
1028 are flexibly connected with hybrid lift wing 102, wherein the electro-hydraulic gas interface 1036 carries lid 10361, the spiral shell
The rotation compound auxiliary wing of paddle thrust self energizing can be divided into the auxiliary wing 10311 of lift and auxiliary 10,312 two parts of empennage of balance, be respectively set
In the front and back of the compound auxiliary wing of airscrew thrust self energizing；It is reserved free between the auxiliary wing 10311 of lift and the auxiliary empennage 10312 of balance
Between, the horizontal lifting rudder wing 1022 is provided in space；Wherein, at least there are one self-enclosed culverts for installation inside the auxiliary wing of lift 10311
Road fan 104, 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 with it is magnetic-type
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 be 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.
As further improvement of the invention, body 101 is installed with cavity 1002, and installation diagram passes, flies control, driving in cavity 1002
Etc. modules.
As further improvement of the invention, it is additionally provided with engine installation position 111 on the compound auxiliary wing of airscrew thrust self energizing,
Power plant is provided in engine installation position 111, the power plant is screw propeller.
As further improvement of the invention, battery/fuel 1006 is provided on the compound auxiliary wing of airscrew thrust self energizing.
Schematically the present invention and embodiments thereof are described above, description is not limiting, shown in attached drawing
Also it is one of embodiments of the present invention, actual structure is not limited to this.So if the ordinary skill people of this field
Member is enlightened by it, without departing from the spirit of the invention, is not inventively designed similar to the technical solution
Frame mode and embodiment, the scope of the present invention should all be belonged to.
Claims (7)
1. a kind of rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust, which is characterized in that by
Afterwards the compound rotor aircraft of single ducted fan formula, be assemblied in its wing both sides the compound auxiliary wing of airscrew thrust self energizing and shipping storehouse
（113）Composition；
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, wherein the body（101）It is set as deck platform；It is described
Hybrid lift wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
Chain (1028)；Propeller（106）For ducted fan propeller；
The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with screw propeller（1062）, airscrew thrust is certainly
Energize the compound auxiliary wing is internally provided with self-enclosed ducted fan（104）, the side of the compound auxiliary wing of airscrew 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 wing
（102）Flexible connection, wherein the electro-hydraulic gas interface（1036）With lid（10361）, the described airscrew thrust confession
The compound auxiliary wing of energy can be divided into the auxiliary wing of lift（10311）And the auxiliary empennage of balance（10312）Two parts, are separately positioned on propeller
The front and back of the compound auxiliary wing of thrust self energizing；The auxiliary wing of lift（10311）With the auxiliary empennage of balance（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 culverts for internal at least installation
Road fan（104）；
The shipping storehouse（113）Mounted on body（101）Lower section.
2. a kind of rear single ducted fan formula composite wing shipping with the compound auxiliary wing of airscrew thrust according to claim 1 flies
Row device, which is characterized in that the hybrid lift wing（102）It is public that front and back are respectively set to magnetic-type self interlocking interface
Head（1026）With magnetic-type self interlocking interface female（1027）；The magnetic-type self interlocking interface male connector（1026）With magnetic
Suction self interlocking interface female（1027）Size is identical.
3. wanting a kind of rear single ducted fan formula composite wing cargo flight with the compound auxiliary wing of airscrew thrust described in 3 according to right
Device, which is characterized in that the magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female
（1027）For taper connection.
4. a kind of rear single ducted fan formula composite wing shipping with the compound auxiliary wing of airscrew thrust according to claim 1 flies
Row device, which is characterized in that the hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage
（1023）Two parts, are separately positioned on hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage
（1023）Between be reserved with space, the horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）Inside is extremely
There are one self-enclosed ducted fans for few installation（104）.
5. a kind of rear single ducted fan formula composite wing shipping with the compound auxiliary wing of airscrew thrust according to claim 1 flies
Row device, which is characterized in that the body（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies control, drives
The modules such as dynamic.
6. a kind of rear single ducted fan formula composite wing shipping with the compound auxiliary wing of airscrew thrust according to claim 1 flies
Row device, which is characterized in that be additionally provided with engine installation position on the compound auxiliary wing of the airscrew thrust self energizing（111）, hair
Motivation installation position（111）It is inside provided with power plant, the power plant is screw propeller.
7. a kind of rear single ducted fan formula composite wing shipping with the compound auxiliary wing of airscrew thrust according to claim 1 flies
Row device, which is characterized in that be provided with battery/fuel on the compound auxiliary wing of the airscrew thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810546573.2A CN108657424A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810546573.2A CN108657424A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108657424A true CN108657424A (en) | 2018-10-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810546573.2A Pending CN108657424A (en) | 2018-05-31 | 2018-05-31 | Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust |
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| Country | Link |
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| CN (1) | CN108657424A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109733598A (en) * | 2018-11-26 | 2019-05-10 | 顺丰科技有限公司 | Aircraft duct and culvert type aircraft |
-
2018
- 2018-05-31 CN CN201810546573.2A patent/CN108657424A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109733598A (en) * | 2018-11-26 | 2019-05-10 | 顺丰科技有限公司 | Aircraft duct and culvert type aircraft |
| CN109733598B (en) * | 2018-11-26 | 2024-04-09 | 丰翼科技(深圳)有限公司 | Air vehicle duct and duct type air vehicle |
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Legal Events
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| PB01 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20181016 |