CN106741858A - Propeller fin - Google Patents
Propeller fin Download PDFInfo
- Publication number
- CN106741858A CN106741858A CN201611108774.1A CN201611108774A CN106741858A CN 106741858 A CN106741858 A CN 106741858A CN 201611108774 A CN201611108774 A CN 201611108774A CN 106741858 A CN106741858 A CN 106741858A
- Authority
- CN
- China
- Prior art keywords
- wing
- aerofoil profile
- section aerofoil
- slightly
- root
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
This application discloses a kind of propeller fin, including multiple section aerofoil profiles that spacing of being waited from wing root to the wing is arranged side by side, wing root to the wing slightly between connected by the bezier surface of each section aerofoil profile of sweeping, there is wing root oar to press from both sides, the vertical height at the center that each section aerofoil profile leading edge point is pressed from both sides to oar is slightly gradually reduced from wing root to the wing, the torsion angle of each section aerofoil profile is extended to being sequentially reduced from blade root position, and the horizontal range that each section aerofoil profile leading edge point to Jiang Jia centers is projected in correspondence section aerofoil profile is gradually reduced from the middle part of the propeller fin to two ends.Above-mentioned propeller fin, the surface of fin is formed by bezier surface, and by the restriction of pair cross-section aerofoil position and torsion angle, so that the propeller fin has good aeroperformance, lift is significantly improved, and resistance is reduced, therefore unmanned plane payload can be improved using the propeller fin and endurance is lifted.
Description
Technical field
Present application relates generally to vehicle technology field, more particularly to propeller fin.
Background technology
With the hot commercial market of multi-rotor unmanned aerial vehicle recent years, unmanned plane as scientific and technological industry focus increasingly
Paid close attention to by everybody.At present, unmanned plane is shot in WirelessHD, express delivery the field such as is sent with charge free and is applied.Particularly fast
Pass and send aspect with charge free, there is bigger difference due to sending part size weight with charge free, before meeting unmanned plane and there is versatility, compact
Put, as much as possible come to improve its load-carrying ability be the main research topic of current art personnel.And improving nothing
How the aspects such as man-machine payload, lifting endurance, improve the lift of propeller fin, and it is this area skill to reduce windage
The demand that art personnel seek assiduously.
The content of the invention
The application provides a kind of propeller fin, is used to improve the lift of propeller fin, and effectively reduces its windage, with
Reach and improve unmanned plane payload, the purpose of lifting endurance.
The application provides a kind of propeller fin, including multiple section wings that spacing of being waited from wing root to the wing is arranged side by side
Type, the wing root to the wing slightly between connected by the bezier surface of each section aerofoil profile of sweeping, there is the wing root oar to press from both sides,
The vertical height at the center that each section aerofoil profile leading edge point is pressed from both sides to the oar is slightly gradually reduced from the wing root to the wing, respectively
The torsion angle of the section aerofoil profile is extended to being sequentially reduced from blade root position, and each section aerofoil profile leading edge point to Jiang Jia centers is in correspondence
The horizontal range projected in the section aerofoil profile is gradually reduced from the middle part of the propeller fin to two ends.
The application provide propeller fin, by bezier surface formed fin surface, and leading edge point to oar press from both sides in
The vertical height of the heart is slightly gradually reduced from wing root to the wing, and each section aerofoil profile leading edge point to Jiang Jia centers is in correspondence section aerofoil profile upslide
The horizontal range of shadow is gradually reduced from the middle part of the propeller fin to two ends, namely by pair cross-section aerofoil position, torsion angle
And the restriction of leading edge distribution so that the propeller fin has good aeroperformance, and lift is significantly improved, and reduces
Resistance, therefore unmanned plane payload can be improved using the propeller fin and endurance is lifted.
Brief description of the drawings
By the detailed description made to non-limiting example made with reference to the following drawings of reading, the application other
Feature, objects and advantages will become more apparent upon：
Fig. 1 is the front view of propeller fin provided in an embodiment of the present invention；
Fig. 2 is the A-A profiles of Fig. 1；
Fig. 3 is the B-B profiles of Fig. 1；
Fig. 4 is the C-C profiles of Fig. 1；
Fig. 5 is the D-D profiles of Fig. 1；
Fig. 6 is the E-E profiles of Fig. 1.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related invention, rather than the restriction to the invention.It also should be noted that, in order to
It is easy to description, the part related to invention is illustrate only in accompanying drawing.
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the application in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
As described in Fig. 1-Fig. 6, propeller fin provided in an embodiment of the present invention, including from wing root 2 to the wing slightly 3 equidistantly simultaneously
The multiple section aerofoil profiles for setting are arranged, the bezier surface between wing root 2 to the wing slightly 3 by each section aerofoil profile of sweeping is connected, wing root 2
With oar folder 1, each section aerofoil profile leading edge point is gradually reduced to the vertical height at the center of oar folder 1 from wing root 2 to the wing slightly 3, each section
The torsion angle of face aerofoil profile is extended to being sequentially reduced from blade root position, and each section aerofoil profile leading edge point to oar presss from both sides 1 center in correspondence section
The horizontal range projected in aerofoil profile is gradually reduced from the middle part of the propeller fin to two ends.Before each section aerofoil profile mentioned here
Edge point presss from both sides the horizontal range that 1 center projects in correspondence section aerofoil profile to oar, refers to for each section aerofoil profile, its leading edge point
1 center the distance between subpoint thereon is pressed from both sides to oar.
The propeller fin that the application is provided, the surface of fin is formed by bezier surface, and leading edge point presss from both sides 1 to oar
The vertical height at center is gradually reduced from wing root 2 to the wing slightly 3, and each section aerofoil profile leading edge point is to the center of oar folder 1 in correspondence section
The horizontal range projected in aerofoil profile is gradually reduced from the middle part of the propeller fin to two ends, namely by pair cross-section aerofoil profile position
Put, torsion angle and leading edge distribution restriction so that the propeller fin has good aeroperformance, and lift is significantly carried
Height, and resistance is reduced, therefore unmanned plane payload can be improved using the propeller fin and endurance is lifted.
In actually used, section aerofoil profile can use NACA (National Advisory Committee for
Aeronautics；National Advisory Committee for Aeronautics) aerofoil profile, at wing root 2 set oar folder 1 be for oar seat connect, and
Oar seat typically be connected with drive system, and such as but not limited to, oar seat is connected in the rotating shaft of motor, oar seat be individual straight panel or
Straight rod member, sets fluted at the two ends of oar seat, and oar folder 1 is installed in groove and is fixedly connected on oar with by the propeller fin
On seat.Used as a preferred mode, oar folder 1 can be using cylinder, and it can also be using the knot such as other cylindricalitys, spherical certainly
Structure, cylindrical oar folder 1 and other positions of fin are integrally connecteds in this embodiment, therefore be can be seen that to the greatest extent in Fig. 1
The semicircle sideline of cylinder.In this application technical scheme, the center of oar folder 1 is a reference point, is limited by the reference point
The position of each aerofoil profile and attitude, and after determining good position and attitude, each aerofoil profile is connected by bezier surface, just constitute this Shen
Please in can improve unmanned plane payload and lift the propeller fin of endurance.
Further, five section aerofoil profiles are provided with altogether in the embodiment, each slice location is a section wing in Fig. 1
Type.Certainly according to actual needs, the section aerofoil profile of other quantity can also be set.For example, five section aerofoil profiles can be
NACA6417, NACA6415, NACA6408, NACA6411, NACA6409, certainly, the selection of aerofoil profile be not limited solely to this five
Kind, can also according to actual needs from the aerofoil profile of other models, five for enumerating here are only to illustrate.
Further, from wing root 2 to the direction of the wing slightly 3, the torsion angle of five section aerofoil profiles is followed successively by：23.288~
29.288deg, 13.735~19.735deg, 9.619~15.619deg, 6.144~12.144deg, 4.09~10.09deg.
Torsion angle β mentioned here is aerofoil profile leading edge point and trailing edge point line and the angle of horizontal plane.By the setting of the torsion angle, can
Preferably to lift lift, resistance is reduced.
Further, from wing root 2 to the direction of the wing slightly 3, the torsion angle of five section aerofoil profiles is followed successively by：26.288deg、
16.735deg、12.619deg、9.144deg、7.09deg.That is, the torsion angle near section aerofoil profile at wing root 2 is maximum, far
Torsion angle from the section aerofoil profile of wing root 2 is tapered into.
Further, from wing root 2 to the direction of the wing slightly 3, vertical height is followed successively by：8.939~12.939mm, 6.391~
10.391mm, 2.803~6.803mm, -0.372~3.628mm, -2.222~1.778mm.By the setting of the vertical height,
Lift can be preferably lifted, resistance is reduced, the reference point of the vertical height is the center of oar folder 1.
Further, from wing root 2 to the direction of the wing slightly 3, vertical height is followed successively by：10.939mm、8.391mm、
4.803mm、1.628mm、-0.222mm。
Further, from wing root 2 to the direction of the wing slightly 3, horizontal range is followed successively by：19.559~23.559mm, 26.498
~30.498mm, 28.601~32.601mm, 27.976~31.976mm, 24.949~28.949mm.By the horizontal range
Setting, can preferably lift lift, reduce resistance, the reference point of the horizontal range is the center of oar folder 1.
Further, from wing root 2 to the direction of the wing slightly 3, horizontal range is followed successively by：21.559mm、28.498mm、
30.601mm、29.976mm、26.949mm。
Further, from wing root 2 to the direction of the wing slightly 3, the chord length of five section aerofoil profiles is followed successively by：47.57~
57.57mm, 60.63~70.63mm, 53.11~63.11mm, 42.24~52.24mm, 31.04~41.04mm.
Further, from wing root 2 to the direction of the wing slightly 3, the chord length of five section aerofoil profiles is followed successively by：52.57mm、
65.63mm、58.11mm、47.24mm、36.04mm。
Above description is only the preferred embodiment and the explanation to institute's application technology principle of the application.People in the art
Member is it should be appreciated that involved invention scope in the application, however it is not limited to the technology of the particular combination of above-mentioned technical characteristic
Scheme, while should also cover in the case where the inventive concept is not departed from, is carried out by above-mentioned technical characteristic or its equivalent feature
Other technical schemes for being combined and being formed.Such as features described above has similar work(with (but not limited to) disclosed herein
The technical scheme that the technical characteristic of energy is replaced mutually and formed.
Claims (10)
1. multiple section aerofoil profiles that a kind of propeller fin, including spacing of being waited from wing root to the wing is arranged side by side, it is characterised in that
The wing root to the wing slightly between connected by the bezier surface of each section aerofoil profile of sweeping, there is the wing root oar to press from both sides, respectively
The vertical height at the center that the section aerofoil profile leading edge point is pressed from both sides to the oar is slightly gradually reduced from the wing root to the wing, each institute
The torsion angle for stating section aerofoil profile is extended to being sequentially reduced from blade root position, and each section aerofoil profile leading edge point to Jiang Jia centers is in correspondence institute
The horizontal range projected in the aerofoil profile of section is stated to be gradually reduced to two ends from the middle part of the propeller fin.
2. propeller fin according to claim 1, it is characterised in that be provided with five section aerofoil profiles altogether.
3. propeller fin according to claim 2, it is characterised in that the direction from the wing root to the wing slightly, five
The torsion angle of the individual section aerofoil profile is followed successively by：23.288~29.288deg, 13.735~19.735deg, 9.619~
15.619deg, 6.144~12.144deg, 4.09~10.09deg.
4. propeller fin according to claim 3, it is characterised in that the direction from the wing root to the wing slightly, five
The torsion angle of the individual section aerofoil profile is followed successively by：26.288deg、16.735deg、12.619deg、9.144deg、7.09deg.
5. propeller fin according to claim 2, it is characterised in that the direction from the wing root to the wing slightly, institute
Vertical height is stated to be followed successively by：8.939~12.939mm, 6.391~10.391mm, 2.803~6.803mm, -0.372~
3.628mm, -2.222~1.778mm.
6. propeller fin according to claim 5, it is characterised in that the direction from the wing root to the wing slightly, institute
Vertical height is stated to be followed successively by：10.939mm、8.391mm、4.803mm、1.628mm、-0.222mm.
7. propeller fin according to claim 2, it is characterised in that the direction from the wing root to the wing slightly, institute
Horizontal range is stated to be followed successively by：19.559~23.559mm, 26.498~30.498mm, 28.601~32.601mm, 27.976~
31.976mm, 24.949~28.949mm.
8. propeller fin according to claim 7, it is characterised in that the direction from the wing root to the wing slightly, institute
Horizontal range is stated to be followed successively by：21.559mm、28.498mm、30.601mm、29.976mm、26.949mm.
9. propeller fin according to claim 2, it is characterised in that the direction from the wing root to the wing slightly, five
The chord length of the individual section aerofoil profile is followed successively by：47.57~57.57mm, 60.63~70.63mm, 53.11~63.11mm, 42.24
~52.24mm, 31.04~41.04mm.
10. propeller fin according to claim 9, it is characterised in that the direction from the wing root to the wing slightly, five
The chord length of the individual section aerofoil profile is followed successively by：52.57mm、65.63mm、58.11mm、47.24mm、36.04mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611108774.1A CN106741858B (en) | 2016-12-06 | 2016-12-06 | Propeller wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611108774.1A CN106741858B (en) | 2016-12-06 | 2016-12-06 | Propeller wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106741858A true CN106741858A (en) | 2017-05-31 |
| CN106741858B CN106741858B (en) | 2023-10-03 |
Family
ID=58879249
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611108774.1A Active CN106741858B (en) | 2016-12-06 | 2016-12-06 | Propeller wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741858B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533311A (en) * | 2018-11-16 | 2019-03-29 | 中国直升机设计研究所 | A kind of high-performance ducted fan |
| CN109896009A (en) * | 2019-02-20 | 2019-06-18 | 顺丰科技有限公司 | Propeller and unmanned plane |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110064579A1 (en) * | 2008-07-29 | 2011-03-17 | Thomas James P | Active Twist Hollow Beam System |
| CN205366054U (en) * | 2016-01-28 | 2016-07-06 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205396538U (en) * | 2016-03-02 | 2016-07-27 | 深圳市道通智能航空技术有限公司 | Screw and aircraft |
| CN205469778U (en) * | 2016-02-29 | 2016-08-17 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205554565U (en) * | 2016-02-29 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN206344996U (en) * | 2016-12-06 | 2017-07-21 | 顺丰科技有限公司 | Propeller fin |
-
2016
- 2016-12-06 CN CN201611108774.1A patent/CN106741858B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110064579A1 (en) * | 2008-07-29 | 2011-03-17 | Thomas James P | Active Twist Hollow Beam System |
| CN205366054U (en) * | 2016-01-28 | 2016-07-06 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205469778U (en) * | 2016-02-29 | 2016-08-17 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205554565U (en) * | 2016-02-29 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205396538U (en) * | 2016-03-02 | 2016-07-27 | 深圳市道通智能航空技术有限公司 | Screw and aircraft |
| CN206344996U (en) * | 2016-12-06 | 2017-07-21 | 顺丰科技有限公司 | Propeller fin |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533311A (en) * | 2018-11-16 | 2019-03-29 | 中国直升机设计研究所 | A kind of high-performance ducted fan |
| CN109896009A (en) * | 2019-02-20 | 2019-06-18 | 顺丰科技有限公司 | Propeller and unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106741858B (en) | 2023-10-03 |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20210805 Address after: 518063 5th floor, block B, building 1, software industry base, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Applicant after: Fengyi Technology (Shenzhen) Co.,Ltd. Address before: 518061 Intersection of Xuefu Road (south) and Baishi Road (east) in Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Applicant before: SF TECHNOLOGY Co.,Ltd. |
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