CN206446792U - Aircraft - Google Patents
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- CN206446792U CN206446792U CN201621488340.4U CN201621488340U CN206446792U CN 206446792 U CN206446792 U CN 206446792U CN 201621488340 U CN201621488340 U CN 201621488340U CN 206446792 U CN206446792 U CN 206446792U
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- Prior art keywords
- ducted fan
- duct
- aircraft
- ducted
- aircraft according
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Abstract
A kind of aircraft is disclosed, the aircraft includes：First ducted fan；And multiple second ducted fans, the multiple second ducted fan is spacedly distributed around first ducted fan, first ducted fan and the multiple second ducted fan include duct and propeller, the propeller rotates to provide power in the duct, wherein, one end of the duct longitudinal cross-section is round and smooth, and the other end is pointed at shape.According to aircraft of the present utility model, the layout type being spacedly distributed using multiple second ducted fans around the first ducted fan so that the flight or hovering of aircraft are more stable.The one end for the duct longitudinal cross-section that first ducted fan and the second ducted fan include is round and smooth, and the other end is pointed at shape, reduces aircraft because introducing the form drag that ducted fan occurs, optimizes its aeroperformance.
Description
Technical field
The utility model is related to field of aircraft, more particularly, to a kind of aircraft.
Background technology
Multi-rotor aerocraft has the advantages that maneuverability, reaction speed are fast, unmanned, accurately controlled, and one in crowd
Many neighborhood extensive uses, such as performing filming image task, detection mission.
Many rotor flyings of prior art more use open type spiral oar, the blade of propeller in high speed circular motion,
Speed highest at blade tip, than larger, and to external world, air-flow produces impact and causes noise big induced drag, causes pneumatic efficiency low.
A kind of improve of the prior art is to replace open type spiral oar using ducted fan formula propeller.Ducted fan refers to
By setting the propeller system of duct, under the protection of duct, ducted fan aircraft in the periphery of open type spiral oar
Security is higher, and aerodynamic noise is smaller.However, the duct profile that the ducted fan that prior art aircraft is used includes is approximately simple
Single cylindrical shape, only provides protection to propeller, without carrying out the Aerodynamic optimization design on application on board the aircraft.
Expect further to optimize the aeroperformance of aircraft.
Utility model content
In view of the above problems, the purpose of this utility model is to provide a kind of aircraft, and the aircraft includes multiple ducts
Fan, and the cross sectional shape of the duct of ducted fan is designed according to aircraft wing aerofoil profile, optimizes aeroperformance, flies
Device general stability is stronger.
A kind of aircraft is provided according to the utility model, including：First ducted fan；And multiple second ducted fans,
The multiple second ducted fan is spacedly distributed around first ducted fan, first ducted fan and described
Multiple second ducted fans include duct and propeller, and the propeller is rotated to provide power in the duct, wherein, institute
The one end for stating duct longitudinal cross-section is circular arc, and the other end is pointed at shape.
Preferably, the biconvex profile that the shape of the duct longitudinal cross-section corresponds in aircraft wing.
Preferably, first ducted fan and/or the multiple second ducted fan also include propeller bracket, described
The propeller is fixed in the duct by propeller bracket, the central shaft of the pivot of the propeller in the duct
On.
Preferably, the type face of the propeller bracket is quiet airfoil surface.
Preferably, the propeller bracket includes from the duct central shaft radiation profiles and extends to many of the duct
Individual rod member.
Preferably, the central shaft of the duct of the multiple second ducted fan and first ducted fan is described
The central shaft of duct is parallel.
Preferably, the aircraft also includes：Fuselage, first ducted fan is located in the fuselage and through institute
Two relative surfaces of fuselage are stated, the multiple second ducted fan is distributed in the fuselage edge.
Preferably, the aircraft also includes：Electric supply installation, guider and electric control gear, the electric supply installation, institute
State guider and the electric control gear is located in the fuselage.
Preferably, the fuselage shape is the assembly of a pair of terrace with edges, wherein the pair of terrace with edge includes the first positive terrace with edge
With the second positive terrace with edge, the first positive terrace with edge includes the first bottom and size is more than second bottom at first bottom, and described second just
Terrace with edge include shape identical with second bottom and the 3rd bottom that overlaps and size less than the 3rd bottom the 4th bottom, described the
One bottom is relative with the 4th bottom, corresponds respectively to described two surfaces of the fuselage.
Preferably, the aircraft also includes：Duct support, the duct support by the multiple second ducted fan according to
Secondary connection forms closed loop.
Preferably, the size of first ducted fan is more than the size of the multiple second ducted fan.
Preferably, the quantity of the multiple second ducted fan is six.
According to aircraft of the present utility model, the cloth around the first ducted fan is distributed in using multiple second ducted fans
Office's mode so that the flight or hovering of aircraft are more stable.The duct that first ducted fan and the second ducted fan include
Longitudinal cross-section one end it is round and smooth, the other end is pointed at shape, and the shape in the section is preferably set according to the aerofoil profile of aircraft wing
Meter, duct reduces aircraft because introducing the body resistance that ducted fan occurs equivalent to a kind of rotary body of section correspondence aerofoil profile
Power, optimizes its aeroperformance.Multiple second ducted fans are spacedly distributed around first ducted fan, Ji Nengti
The driving force of high aircraft, can also make the flight of aircraft and hover more steady.
In a preferred embodiment, the type face of propeller bracket is quiet airfoil surface, further optimizes ducted fan and flies
The aeroperformance of row device.
Brief description of the drawings
By description referring to the drawings to the utility model embodiment, of the present utility model above-mentioned and other mesh
, feature and advantage will be apparent from, in the accompanying drawings：
Fig. 1 shows the stereogram of the aircraft according to the utility model specific embodiment.
Fig. 2 shows the top view of the aircraft according to the utility model specific embodiment.
Fig. 3 shows the front view of the aircraft according to the utility model specific embodiment.
Fig. 4 shows the front view according to the utility model specific embodiment middle fuselage.
Fig. 5 shows the stereogram according to ducted fan in the utility model specific embodiment.
Fig. 6 shows the top view according to ducted fan in the utility model specific embodiment.
Fig. 7 shows the front view according to ducted fan in the utility model specific embodiment.
Fig. 8 shows the stereogram according to the duct of ducted fan in the utility model specific embodiment.
Embodiment
The utility model is more fully described hereinafter with reference to accompanying drawing.For the sake of clarity, the various pieces in accompanying drawing do not have
Have drawn to scale.Furthermore, it is possible to not shown some known parts.It describe hereinafter of the present utility model many specific
Details, but just as the skilled person will understand, this can not be realized according to these specific details
Utility model.
It should be appreciated that when describing the structure of part, being referred to as being located at another floor, another area when by a floor, a region
When domain " above " or " top ", can refer to above another layer, another region, or its with another layer, it is another
Also comprising other layers or region between individual region.Also, if by part turnover, this layer, a region will be located at it is another
Layer, another region " following " or " lower section ".
The stereogram of the aircraft according to the utility model specific embodiment, top view and preceding is shown respectively in Fig. 1 to Fig. 3
View.The aircraft includes the first ducted fan 110 and multiple second ducted fans 120, multiple 120 points of second ducted fans
Cloth is around the first ducted fan 110, and the first ducted fan 110 and multiple second ducted fans 120 include duct and spiral
Oar, propeller is rotated to provide power in duct, wherein, one end of duct longitudinal cross-section is circular arc, and the other end is pointed at shape.
I.e. duct longitudinal cross-section is a water-drop-shaped.
In such as Fig. 2, the present embodiment, the quantity of multiple second ducted fans 120 is six, above-mentioned six the second ducted fans
120, which are centrosymmetric, is distributed in around the first ducted fan 110, forms the arrangement mode of a regular hexagon, the first duct
Fan 110 is located on the center of the regular hexagon.The size of first ducted fan 110 is more than multiple second ducted fans
120 size, and the size of each the second ducted fan 120 is identical so that and aircraft forms a kind of large scale ducted fan
Between two parties, the arrangement mode of the uniform surrounding of multiple small size ducted fans so that the flight of aircraft is tethered at more stable in the air.Can
With understanding, the quantity of multiple second ducted fans 120 is not limited to six in the present embodiment, for example can also be four,
The other quantities such as eight, correspondingly its arrangement mode around the first ducted fan 110 be also not necessarily limited to the side in the present embodiment
Formula, in addition, the size of the first ducted fan 110 can be more than the size of the second ducted fan 120, might be less that or be equal to.
Multiple second ducted fans 120 are spacedly distributed around the first ducted fan 120, can improve the driving force of aircraft,
Also the flight of aircraft can be made and hovered more steady.
Preferably, such as Fig. 3, the duct that the first ducted fan 110 shown in broken lines and multiple second ducted fans 120 include
Central shaft, wherein, the center of the duct of the central shaft of the duct of multiple second ducted fans 120 and the first ducted fan 110
Axle is parallel.
Further, aircraft of the present utility model can also include duct support 140, and the duct support 140 will be multiple
Second ducted fan 120 is in turn connected to form closed loop so that Flight Vehicle Structure is more stable.
According to aircraft of the present utility model, it can also further include fuselage 130, wherein the first ducted fan 110
In fuselage 130 and through two relative surfaces of fuselage 130, multiple second ducted fans 120 are spacedly distributed in fuselage
130 edges.
Fuselage 130 can be with the first ducted fan 110 be adapted it is variously-shaped, with outer with good aeroperformance
Shape is excellent.Referring to Fig. 1 to 3 and Fig. 4, Fig. 4 shows the front view of the present embodiment middle fuselage 130.Fuselage 130 includes relative
First surface 131 and second surface 132, the first ducted fan 110 run through first surface 131 and second surface 132.This implementation
Example middle fuselage 130 is shaped as the assembly of a pair of terrace with edges, wherein the pair of terrace with edge includes the first positive terrace with edge and the second positive terrace with edge,
First positive terrace with edge and the second positive terrace with edge include 12 inclines, and the first positive terrace with edge includes the first bottom and size is more than first bottom
Second bottom, the second positive terrace with edge includes that shape is identical with second bottom and the 3rd bottom overlapped and size are less than the of the 3rd bottom
Four bottoms, the first bottom is oppositely arranged with the 4th bottom, corresponds respectively to the first surface 131 and second surface 132 of the fuselage 130.
Aircraft can also include the air equipments such as electric supply installation, guider and electric control gear, and above-mentioned aviation
Equipment can be placed in the fuselage 130.The aircraft that the utility model is provided can be used as unmanned plane is tethered at.
First ducted fan 110, multiple second ducted fans 120 can use the ducted fan of same shape, and size
Can be different.Below by by being illustrated by taking the second ducted fan 120 as an example to the ducted fan of the utility model aircraft,
The construction of first ducted fan 110 can be identical with the second ducted fan 120, therefore is no longer described in detail.
Fig. 5 to Fig. 7 shows stereogram, the top view according to the second ducted fan 120 in the utility model specific embodiment
And front view.Second ducted fan 120 includes duct 121 and propeller 122, and propeller 122 rotates to carry in duct 121
For power.In addition, the second ducted fan 120 also includes propeller bracket 123, propeller bracket 123 consolidates the propeller 122
Be scheduled in duct 121, and propeller 122 pivot on the central shaft of duct 121.In the present embodiment, propeller branch
Frame 123 includes from the central shaft radiation profiles of duct 121 and extends to multiple rod members of the inwall of duct 121, e.g. six rod members,
Stable support is provided.To be that aircraft has more preferable aeroperformance, the type face that can set propeller bracket 123 is quiet
Airfoil surface.It should be noted that in turbomachine, blade is commonly divided into relatively-stationary stator blade and moving for relatively rotating
Leaf, the type face of the propeller bracket 123 of the present embodiment corresponds to quiet airfoil surface, so as to reach further optimization ducted fan and fly
The purpose of row device aeroperformance.
One end of the longitudinal cross-section of duct 121 is round and smooth, and the other end is pointed at shape, and duct 121 can be regarded as above-mentioned longitudinal direction
Section rotates obtained rotary body around a longitudinal axis.Preferably, the shape of the longitudinal cross-section of duct 121 can be according to aircraft wing
It is designed.Fig. 8 shows to be the display cross sectional shape of duct 121 in the stereogram of the duct 121 of the second ducted fan 120, figure, will
The interception of duct 121 half shows that duct 121 can rotate a circle in section according to dash area around rotary shaft shown in phantom
Obtain.In the present embodiment, the shape of the longitudinal cross-section of duct 121 is corresponding to the biconvex profile in aircraft wing, it is of course possible to manage
Solution, the cross sectional shape of duct 121 can also correspond to other aerofoil profiles in craft wing design, e.g. plano-convex aerofoil profile, recessed
Other aerofoil profiles such as convex wing type.The type selecting of the section of duct 121 correspondence aerofoil profile and the design of the second ducted fan 120 need to fly
The actual demand of device is foundation.The method designed in a kind of second ducted fan 120 of this example：First according to aircraft power need
Ask, the quantity of ducted fan determine duct 121 size, such as internal diameter of duct 121, duct 121 height scope；Then press
According to the requirement of the performances such as vehicle flight speeds, according to example and equalising torque relation during flight, ducted fan power set are determined
Apart from the position of itself gyroaxis of fuselage 130；Finally, from high-lift airfoil, such as NACA4418 aerofoil profiles, to duct 121
Such as section is designed, while determining the design parameter of the suitable parameter of propeller 122 and duct 121, optimal duct is high
Spend hoptimal, duct lip radius rLE, duct cone angle beta, duct thickest b, duct outlet diameter Doutlet, oar disk position hP、
Oar disk tip clearance ΔtipDeng.It should be noted that for the design of the first ducted fan 110 in the utility model embodiment,
After above-mentioned design process, it can also include：Duct type face and the type face of fuselage 130 are subjected to integrated design so that flight
Device globality is stronger, and stability is more preferable.It is the one of the design method for the duct that aerofoil profile is corresponded to the utility model middle section above
Example is planted, the design method of this ducted fan can be not limited to the above method.
According to aircraft of the present utility model, the first ducted fan is distributed in 110 weeks using multiple second ducted fans 120
The layout type enclosed so that the flight of aircraft is tethered at more stable in the air.First ducted fan 110 and the second ducted fan
One end of the longitudinal cross-section of 120 ducts included is round and smooth, and the other end is pointed at shape, forms the section of approximate water-drop-shaped；It is preferred that will
The aerofoil profile that the section corresponds to aircraft wing is designed, and duct is reduced equivalent to a kind of rotary body of section correspondence aerofoil profile
Aircraft optimizes its aeroperformance because introducing the form drag that ducted fan occurs.Multiple second ducted fans 120 are at equal intervals
It is distributed in around the first ducted fan 120, the driving force of aircraft can be improved, can also makes the flight of aircraft and hover more
Steadily.
It should be noted that herein, such as first and second or the like relational terms are used merely to a reality
Body or operation make a distinction with another entity or operation, and not necessarily require or imply these entities or deposited between operating
In any this actual relation or order.Moreover, term " comprising ", "comprising" or its any other variant are intended to
Nonexcludability is included, so that process, method, article or equipment including a series of key elements not only will including those
Element, but also other key elements including being not expressly set out, or also include being this process, method, article or equipment
Intrinsic key element.In the absence of more restrictions, the key element limited by sentence "including a ...", it is not excluded that
Also there is other identical element in process, method, article or equipment including the key element.
According to embodiment of the present utility model as described above, these embodiments do not have all details of detailed descriptionthe,
Also it is only described specific embodiment not limit the utility model.Obviously, as described above, many modifications and change can be made
Change.This specification is chosen and specifically describes these embodiments, be in order to preferably explain principle of the present utility model and it is actual should
With so that skilled artisan can repairing using the utility model and on the basis of the utility model well
Change and use.The utility model is only limited by claims and its four corner and equivalent.
Claims (12)
1. a kind of aircraft, it is characterised in that including：
First ducted fan；And
Multiple second ducted fans, the multiple second ducted fan is spacedly distributed around first ducted fan,
First ducted fan and the multiple second ducted fan include duct and propeller, and the propeller is contained described
Rotated in road to provide power,
Wherein, one end of the duct longitudinal cross-section is circular arc, and the other end is pointed at shape.
2. aircraft according to claim 1, it is characterised in that the shape of the duct longitudinal cross-section corresponds to the aircraft wing
Biconvex profile in type.
3. aircraft according to claim 1, it is characterised in that first ducted fan and/or the multiple second
Ducted fan also includes propeller bracket, and the propeller is fixed in the duct by the propeller bracket, the spiral
The pivot of oar is on the central shaft of the duct.
4. aircraft according to claim 3, it is characterised in that the type face of the propeller bracket is quiet airfoil surface.
5. aircraft according to claim 3, it is characterised in that the propeller bracket is included from the duct central shaft
Radiation profiles and the multiple rod members for extending to the duct.
6. aircraft according to claim 1, it is characterised in that in the duct of the multiple second ducted fan
Heart axle is parallel with the central shaft of the duct of first ducted fan.
7. aircraft according to claim 1, it is characterised in that also include：
Fuselage, first ducted fan is located in the fuselage and through two relative surfaces of the fuselage, described many
Individual second ducted fan is distributed in the fuselage edge.
8. aircraft according to claim 7, it is characterised in that also include：
Electric supply installation, guider and electric control gear, the electric supply installation, the guider and electric control gear position
In in the fuselage.
9. aircraft according to claim 7, it is characterised in that the fuselage shape is the assembly of a pair of terrace with edges, its
Described in a pair of terrace with edges include the first positive terrace with edge and the second positive terrace with edge, the first positive terrace with edge includes the first bottom and size is more than institute
State second bottom at the first bottom, the second positive terrace with edge includes shape identical with second bottom and the 3rd bottom of coincidence and size are small
The 4th bottom in the 3rd bottom, first bottom is relative with the 4th bottom, corresponds respectively to the described two of the fuselage
Surface.
10. aircraft according to claim 1, it is characterised in that also include：
The multiple second ducted fan is in turn connected to form closed loop by duct support, the duct support.
11. aircraft according to claim 1, it is characterised in that the size of first ducted fan is more than described many
The size of individual second ducted fan.
12. aircraft according to claim 1, it is characterised in that the quantity of the multiple second ducted fan is six.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621488340.4U CN206446792U (en) | 2016-12-30 | 2016-12-30 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621488340.4U CN206446792U (en) | 2016-12-30 | 2016-12-30 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206446792U true CN206446792U (en) | 2017-08-29 |
Family
ID=59670757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621488340.4U Expired - Fee Related CN206446792U (en) | 2016-12-30 | 2016-12-30 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206446792U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107719657A (en) * | 2017-10-09 | 2018-02-23 | 武汉卓尔无人机制造有限公司 | A kind of rotor wing unmanned aerial vehicle of ducted fan four |
| CN108263600A (en) * | 2016-12-30 | 2018-07-10 | 深圳光启空间技术有限公司 | Aircraft |
| CN108945418A (en) * | 2018-07-20 | 2018-12-07 | 酷黑科技（北京）有限公司 | A kind of culvert type unmanned plane and its shell |
| WO2021134543A1 (en) * | 2019-12-31 | 2021-07-08 | 李庆远 | High-lift for ring-wing fan engine |
-
2016
- 2016-12-30 CN CN201621488340.4U patent/CN206446792U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108263600A (en) * | 2016-12-30 | 2018-07-10 | 深圳光启空间技术有限公司 | Aircraft |
| CN107719657A (en) * | 2017-10-09 | 2018-02-23 | 武汉卓尔无人机制造有限公司 | A kind of rotor wing unmanned aerial vehicle of ducted fan four |
| CN108945418A (en) * | 2018-07-20 | 2018-12-07 | 酷黑科技（北京）有限公司 | A kind of culvert type unmanned plane and its shell |
| WO2021134543A1 (en) * | 2019-12-31 | 2021-07-08 | 李庆远 | High-lift for ring-wing fan engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170829 Termination date: 20201230 |