CN106275418A - There is rotor hanger and the unmanned plane of good aerodynamic configuration - Google Patents
There is rotor hanger and the unmanned plane of good aerodynamic configuration Download PDFInfo
- Publication number
- CN106275418A CN106275418A CN201610873121.6A CN201610873121A CN106275418A CN 106275418 A CN106275418 A CN 106275418A CN 201610873121 A CN201610873121 A CN 201610873121A CN 106275418 A CN106275418 A CN 106275418A
- Authority
- CN
- China
- Prior art keywords
- rotor hanger
- aerodynamic configuration
- hanger
- shell
- rotor
- Prior art date
- 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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Classifications
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
This application discloses a kind of rotor hanger with good aerodynamic configuration and unmanned plane, this rotor hanger includes shell, the structure of described shell is to carry out circular arc process at the trailing edge of aerofoil profile, and bottom carries out the structure after level of approximation process, and the cross sectional shape of described shell is the shape of biconvex.Invention also provides for a kind of unmanned plane, including the above-mentioned rotor hanger with good aerodynamic configuration being arranged on wing.The rotor hanger of the present invention is that aerofoil profile is carried out correction of the flank shape, is changed being adapted to fit into the rotor hanger of motor.The basic profile of hanger of the present invention derives from existing aerofoil profile, and its aeroperformance is by far better than conventional rotor hanger.
Description
Technical field
The disclosure relates generally to unmanned plane field, is specifically related to rotor hanger and the unmanned plane with good aerodynamic configuration.
Background technology
Along with the fast development of unmanned plane industry, unmanned plane kind gets more and more, and wherein mixed layout unmanned plane is by knot
Close four rotor wing unmanned aerial vehicle VTOL and the unmanned captain of fixed-wing navigate the feature of duration voyage, have vast potential for future development and
Range of application.In existing unmanned plane, the vitals rotor hanger as mixed layout unmanned plane is frequently used outside pipe
Shape, it is not intended that its impact on complete machine aeroperformance, it often produces bigger resistance.
Summary of the invention
In view of drawbacks described above of the prior art or deficiency, it is desirable to provide a kind of rotor with good aerodynamic configuration to hang
Frame, it addition, also provide for a kind of unmanned plane being provided with this rotor hanger.
First aspect, it is provided that a kind of rotor hanger with good aerodynamic configuration, including shell, the structure of described shell is
Carrying out circular arc process at the trailing edge of aerofoil profile, and bottom carries out the structure after horizontal processing, the cross sectional shape of described shell is double
Convex shape.
Second aspect, it is provided that a kind of unmanned plane, including the above-mentioned rotation with good aerodynamic configuration being arranged on wing
Wing hanger.
The rotor hanger of the present invention is that aerofoil profile is carried out correction of the flank shape, is changed being adapted to fit into the rotor hanger of motor.This
The basic profile of bright hanger derives from existing aerofoil profile, and its aeroperformance is by far better than conventional rotor hanger.
Accompanying drawing explanation
By the detailed description that non-limiting example is made made with reference to the following drawings of reading, other of the application
Feature, purpose and advantage will become more apparent upon:
The front view of the rotor hanger that Fig. 1 provides for the embodiment of the present invention；
The top view of the rotor hanger that Fig. 2 provides for the embodiment of the present invention；
The using effect figure that the rotor hanger that Fig. 3 provides for the embodiment of the present invention is arranged on wing；
Fig. 4 is the A-A sectional view of Fig. 3；
The rotor hanger that Fig. 5 provides for the embodiment of the present invention and the resistance coefficient figure of conventional rotor hanger.
Detailed description of the invention
With embodiment, the application is described in further detail below in conjunction with the accompanying drawings.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related invention, rather than the restriction to this invention.It also should be noted that, in order to
It is easy to describe, accompanying drawing illustrate only and invent relevant part.
It should be noted that in the case of not conflicting, the embodiment in the application and the feature in embodiment can phases
Combination mutually.Describe the application below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
Refer to Fig. 1, Fig. 2, Fig. 3 and Fig. 4, a kind of rotor hanger with good aerodynamic configuration, including shell 1, shell 1
The trailing edge that structure is aerofoil profile at carry out circular arc process, and bottom is carried out the structure after level of approximation process, the cross section of shell 1
It is shaped as the shape of biconvex.
The present embodiment is on the basis of above-described embodiment, and the lower section of shell 1 is provided with the first space accommodating motor 2.
The present invention installs motor for convenience, the shape of the cross sectional shape biconvex of shell, the projection of cross section lower part radian
The radian being significantly less than upper part is protruding, and the radian of lower part is close to level, but has again sub-fraction arc relative to level
Degree.
The present embodiment is on the basis of above-described embodiment, and the first space is two, is arranged on the two ends of shell 1.
The present embodiment is on the basis of above-described embodiment, and the lower section of motor is used for installing propeller 3.
The present embodiment is on the basis of above-described embodiment, and the chord length of shell 1 is L, and the width of shell 1 is 0.05-0.15L.
Chord length refers to the leading edge point air line distance to trailing edge point, the i.e. the highest summit of leading edge to the distance between the highest summit of trailing edge.
Preferably, the width of shell 1 is 0.1L.The chord length of shell 1 is 820-860mm；It is preferably 837mm.
Preferably, in order to reach more preferable aeroperformance, the cross section of shell 1 is that the cross section of aerofoil profile NACA2408 is in chord length
By circular arc by the structure after aerofoil profile afterbody correction of the flank shape at 0.65-0.80L；Preferably chord length is 0.75L.
Cross sectional shape of the present invention is based on aerofoil profile NACA2408, and its trailing edge shape is modified to conveniently install motor and spiral
Oar.
See Fig. 3 and Fig. 4, one unmanned plane of the present invention, including be arranged on wing 4 above-mentioned have good pneumatic outside
The rotor hanger of shape.
Preferably, shell 1 and wing 4 are integrative-structures.I.e. in actual production, rotor hanger and wing can be made
Integrative-structure, it is not necessary to carry out extra installation again.
Calculated by fluid mechanical emulation, the novel rotor hanger in the present invention and the resistance of common cylindrical shaped rotor hanger
Coefficient is as shown in Figure 5.The resistance coefficient of the most novel rotor hanger is far smaller than conventional hanger, and the design of the present invention is described
There is more preferable aerodynamic configuration.
Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.People in the art
Member should be appreciated that invention scope involved in the application, however it is not limited to the technology of the particular combination of above-mentioned technical characteristic
Scheme, also should contain in the case of without departing from described inventive concept simultaneously, above-mentioned technical characteristic or its equivalent feature carry out
Combination in any and other technical scheme of being formed.Such as features described above has similar merit with (but not limited to) disclosed herein
The technical scheme that the technical characteristic of energy is replaced mutually and formed.
Claims (10)
1. a rotor hanger with good aerodynamic configuration, it is characterised in that include that shell, the structure of described shell are aerofoil profile
Carrying out circular arc process at trailing edge, and bottom carries out the structure after level of approximation process, the cross sectional shape of described shell is biconvex
Shape.
The rotor hanger with good aerodynamic configuration the most according to claim 1, it is characterised in that the lower section of described shell
Being provided with the first space accommodating motor, described motor is arranged on described motor cabinet.
The rotor hanger with good aerodynamic configuration the most according to claim 2, it is characterised in that described first space is two
Individual, it is arranged on the two ends of shell.
The rotor hanger with good aerodynamic configuration the most according to claim 3, it is characterised in that the lower section of described motor is used for
Propeller is installed.
5. according to the rotor hanger with good aerodynamic configuration described in any one of claim 1-4, it is characterised in that outside described
The chord length of shell is L, and the width of described shell is 0.05-0.15L.
The rotor hanger with good aerodynamic configuration the most according to claim 5, it is characterised in that the width of described shell
For 0.1L.
The rotor hanger with good aerodynamic configuration the most according to claim 6, it is characterised in that the chord length of described shell
For 820-860mm.
The rotor hanger with good aerodynamic configuration the most according to claim 7, it is characterised in that the cross section of described shell
For the cross section of aerofoil profile NACA 2408 at chord length 0.65-0.80L by circular arc by the structure after aerofoil profile afterbody correction of the flank shape.
9. a unmanned plane, it is characterised in that include having well described in any one of claim 1-8 being arranged on wing
The rotor hanger of aerodynamic configuration.
Unmanned plane the most according to claim 9, it is characterised in that described shell and wing are integrative-structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610873121.6A CN106275418A (en) | 2016-09-30 | 2016-09-30 | There is rotor hanger and the unmanned plane of good aerodynamic configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610873121.6A CN106275418A (en) | 2016-09-30 | 2016-09-30 | There is rotor hanger and the unmanned plane of good aerodynamic configuration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275418A true CN106275418A (en) | 2017-01-04 |
Family
ID=57716697
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610873121.6A Pending CN106275418A (en) | 2016-09-30 | 2016-09-30 | There is rotor hanger and the unmanned plane of good aerodynamic configuration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106275418A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204197290U (en) * | 2014-09-17 | 2015-03-11 | 南昌航空大学 | A kind of novel tiltrotor aircraft |
| CN205273862U (en) * | 2016-01-12 | 2016-06-01 | 成都纵横自动化技术有限公司 | Composite wing VTOL unmanned aerial vehicle |
| CN105882959A (en) * | 2015-02-13 | 2016-08-24 | 空中客车防卫和太空有限责任公司 | Aircraft capable of vertical takeoff |
| WO2016140987A1 (en) * | 2015-03-03 | 2016-09-09 | Amazon Technologies, Inc. | Unmanned aerial vehicle with a tri-wing configuration |
| CN206068151U (en) * | 2016-09-30 | 2017-04-05 | 顺丰科技有限公司 | Rotor hanger with good aerodynamic configuration and unmanned plane |
-
2016
- 2016-09-30 CN CN201610873121.6A patent/CN106275418A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204197290U (en) * | 2014-09-17 | 2015-03-11 | 南昌航空大学 | A kind of novel tiltrotor aircraft |
| CN105882959A (en) * | 2015-02-13 | 2016-08-24 | 空中客车防卫和太空有限责任公司 | Aircraft capable of vertical takeoff |
| WO2016140987A1 (en) * | 2015-03-03 | 2016-09-09 | Amazon Technologies, Inc. | Unmanned aerial vehicle with a tri-wing configuration |
| CN205273862U (en) * | 2016-01-12 | 2016-06-01 | 成都纵横自动化技术有限公司 | Composite wing VTOL unmanned aerial vehicle |
| CN206068151U (en) * | 2016-09-30 | 2017-04-05 | 顺丰科技有限公司 | Rotor hanger with good aerodynamic configuration and unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170104 |