CN108750074A - propeller - Google Patents
propeller Download PDFInfo
- Publication number
- CN108750074A CN108750074A CN201810563390.1A CN201810563390A CN108750074A CN 108750074 A CN108750074 A CN 108750074A CN 201810563390 A CN201810563390 A CN 201810563390A CN 108750074 A CN108750074 A CN 108750074A
- Authority
- CN
- China
- Prior art keywords
- blade
- propeller
- fixed seat
- leading edge
- attack
- 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.)
- Pending
Links
Classifications
-
- 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
-
- 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
Abstract
The present invention provides a kind of propellers, it includes fixed seat and blade, and the blade is connected in the fixed seat, apart from the center of the fixed seat be the propeller radius 40% at, the angle of attack of the blade is 13.64 ° ± 2.5 °, and the chord length of the blade is 48.74mm ± 5mm；Be apart from the center of the fixed seat radius of the propeller 70% at, the angle of attack of the blade is 8.03 ° ± 2.5 °, and the chord length of the blade is 35.84mm ± 5mm；Be apart from the center of the fixed seat radius of the propeller 97% at, the angle of attack of the blade is 5.41 ° ± 2.5 °, and the chord length of the blade is 21.79mm ± 5mm.Compared with the relevant technologies, the working efficiency higher of propeller provided by the invention.
Description
【Technical field】
The present invention relates to aircraft field more particularly to a kind of propellers.
【Background technology】
Propeller is the important component of aircraft, is used to convert the rotation of motor output shaft to thrust or lift with reality
Landing, steering, the hovering etc. of existing unmanned plane.
The propeller of the prior art, outer shape is usually rectangular, since the propeller resistance using rectangle is big, efficiency
It is low so that motor output shaft be converted into thrust or the transmission efficiency of lift is affected, so as to cause aircraft fly
Scanning frequency degree is small, endurance distance is short, cannot be satisfied expected thrust or the demand of lift at work.
Therefore, it is necessary to provide a kind of improved propeller to solve the above problems.
【Invention content】
The technical problem to be solved in the present invention is to provide a kind of propellers that can improve working efficiency.
In order to solve the above technical problems, the present invention provides a kind of propellers comprising：Fixed seat and blade, the paddle
Leaf is connected in the fixed seat,
Apart from the center of the fixed seat be the propeller radius 40% at, the angle of attack of the blade is
13.64 ° ± 2.5 °, the chord length of the blade is 48.74mm ± 5mm；
Apart from the center of the fixed seat be the propeller radius 70% at, the angle of attack of the blade is
8.03 ° ± 2.5 °, the chord length of the blade is 35.84mm ± 5mm；
Apart from the center of the fixed seat be the propeller radius 97% at, the angle of attack of the blade is
5.41 ° ± 2.5 °, the chord length of the blade is 21.79mm ± 5mm.
Preferably, the propeller rotates a circle a diameter of 560mm ± 40mm for the paddle disk to be formed, apart from the fixation
At seat center 114.1mm, the angle of attack of the blade is 13.64 ° ± 2.5 °, and the chord length of the blade is 48.74mm ± 5mm.
Preferably, the propeller rotates a circle a diameter of 560mm ± 40mm for the paddle disk to be formed, apart from the fixation
At seat center 199.7mm, the angle of attack of the blade is 8.03 ° ± 2.5 °, and the chord length of the blade is 35.84mm ± 5mm.
Preferably, the propeller rotates a circle a diameter of 560mm ± 40mm for the paddle disk to be formed, apart from the fixation
At seat center 276.8mm, the angle of attack of the blade is 5.41 ° ± 2.5 °, and the chord length of the blade is 21.79mm ± 5mm.
Preferably, the blade has blade back, the blade face being oppositely arranged with the blade back, connect the blade face and the leaf
Carry on the back the leading edge of a side and the rear on the connection blade face and another side of the blade back, the blade back, the blade face, it is described before
Edge and the rear are enclosed petiole and blade tip jointly, and the petiole is located at close to the fixed seat side, the blade tip position
In far from the fixed seat side, the area of section from the petiole direction toward blade described in the blade tip direction is gradually reduced.
Preferably, the rear has extended to form the first protrusion close to the part of the blade tip toward far from the leading edge direction
Portion, area of section of first protruding portion from close to the leading edge direction toward far from the leading edge direction are gradually reduced.
Preferably, the rear has extended to form the second protrusion close to the part of the petiole toward far from the leading edge direction
Portion, area of section of second protruding portion from close to the leading edge direction toward far from the leading edge direction is gradually reduced, described
Leading edge has extended to form third protruding portion close to the part of the petiole toward far from the rear direction, and the third protruding portion is certainly
It is gradually reduced toward the area of section far from the rear direction close to the rear direction.
Preferably, there are two the blade is set, two blades are along the fixed seat center symmetric setting.
Preferably, the blade is to fold blade.
Preferably, the fixed seat is structure as a whole with the blade.
Compared with the relevant technologies, propeller of the invention passes through the shape of rational design blade so that uses the blade
Propeller can reduce air drag, to improve the working efficiency of propeller, and then increase the endurance distance of aircraft
And improve the flying quality of aircraft.
【Description of the drawings】
To describe the technical solutions in the embodiments of the present invention more clearly, make required in being described below to embodiment
Attached drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings other
Attached drawing, wherein：
Fig. 1 is the first angled arrangement schematic diagram of propeller of the present invention；
Fig. 2 is second of angled arrangement schematic diagram of propeller of the present invention；
Fig. 3 is the third angled arrangement schematic diagram of propeller of the present invention；
Fig. 4 is the sectional view of the A-A sections at the center 114.1mm in propeller shown in Fig. 1 apart from fixed seat；
Fig. 5 is the sectional view of the B-B sections at the center 199.7mm in propeller shown in Fig. 1 apart from fixed seat；
Fig. 6 is the sectional view of the C-C sections at the center 276.8mm in propeller shown in Fig. 1 apart from fixed seat.
【Specific implementation mode】
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that the described embodiments are merely a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts all other
Embodiment shall fall within the protection scope of the present invention.
Present embodiments provide for a kind of propellers 100, can be positive paddle either anti-paddles.So-called positive paddle, refers to from driving
Part such as motor tail portion is seen to motor head direction, is rotated clockwise to generate the propeller of lift；So-called anti-paddle refers to from motor tail
Portion is seen to motor head direction, is rotated to produce the propeller of lift counterclockwise.The knot of the structure of the positive paddle and the anti-paddle
Mirror symmetry between structure.
In addition, the orientation term such as upper and lower occurred in embodiment is to be installed on spiral shell after aircraft with the propeller 100
The normal operational attitude for revolving paddle and aircraft is reference, and be should not be considered as restrictive.
Fig. 1 to Fig. 3 is please referred to, the present invention provides a kind of propellers 100 comprising fixed seat (not shown) and paddle
Leaf 10.
The blade 10 is set as two, two blades 10 center symmetric setting along the center of the fixed seat.
The propeller 100 can be self-tightening paddle or folding paddle.The folding paddle is referred to by by 10 folding of the blade
It is laminated to parallel with aircraft fuselage or sticks on aircraft fuselage to reduce the volume of entire aircraft with convenience in transport and deposit
It puts.
The blade 10 is connected to the fixed seat.In present embodiment, two blades 10 are distinguished with the fixed seat
Machine-shaping is fixedly mounted integral.Certainly, two blades 10 can be integrated machine-shaping with the fixed seat and be integrated knot
Structure.
When the propeller 100 works, the blade 10 is rotated around the center of the fixed seat to form paddle disk,
Lift is generated with rough air or thrust drives the movement of aircraft.The prior art may be used in the blade 10 of the present embodiment
In arbitrary material manufactured, including but not limited to steel, aluminium alloy, plastics, carbon fiber etc..During fabrication, it can also adopt
With the processing technology for including the various prior arts such as molding, punching press, forging.
The blade 10 has blade back 11, the blade face 12 being oppositely arranged with the blade back 11, connect the blade face 12 and institute
State the leading edge 13 of 11 a side of blade back and the rear 14 on the connection blade face 12 and 11 another side of the blade back.Wherein, described
Blade back 11 is aircraft in flight course, the one side (in other words towards heading) upward of the blade 10；Blade face 12 is
Aircraft is in flight course, the one side (in other words towards heading opposite side) downward of the blade 10；The rear
14 are located at the lower section of the leading edge 13 (leading edge 13 is located closer to heading side in other words), that is to say, that in level
From 13 direction of the leading edge toward blade back 11 described in 14 direction of the rear and the blade face 12 for curved surface and simultaneously on-plane surface on direction,
And the opening direction of the curved surface on the blade back 11 and the blade face 12 is in lower section (or perhaps opposite the one of heading
Side).
The blade back 11 and the blade face 12 are curved surface and to seamlessly transit, the position that do not reverse drastically, have compared with
Small stress.
The blade back 11, the blade face 12, the leading edge 13 and the rear 14 are enclosed petiole 15 and blade tip jointly
16.The petiole 15 is located at close to the fixed seat side, and the blade tip 16 is located remotely from the fixed seat side.
Area of section from 15 direction of the petiole toward blade 10 described in 16 direction of the blade tip is gradually reduced, i.e., the described leaf
Handle 15 is the thicker side of thickness in the blade 10, and the blade tip 16 is thinner thickness side in the blade 10.
The rear 14 is extended to form toward far from 13 direction of the leading edge by the first protrusion close to the part of the blade tip 16
Portion 17.
First protruding portion 17 from close to 13 direction of the leading edge toward far from 13 direction of the leading edge area of section by
It is decrescence small.
The rear 14 is extended to form toward far from 13 direction of the leading edge by the second protruding portion close to 15 part of the petiole
18。
Second protruding portion 18 from close to 13 direction of the leading edge toward far from 13 direction of the leading edge area of section by
It is decrescence small.
The leading edge 13 is extended to form toward far from 14 direction of the rear by third protruding portion close to 15 part of the petiole
19。
The third protruding portion 19 from close to 14 direction of the rear toward far from 14 direction of the rear area of section by
It is decrescence small.
First protruding portion 17, second protruding portion 18 and the third protruding portion 19 are curved-surface structure.Wherein,
The distance that first protruding portion 17 extends in the horizontal direction is less than the distance that second protruding portion 18 extends.I.e. described
One protruding portion 17 is with projection of second protruding portion 18 in same level, and second protruding portion 18 is from the rear
14 extended distance is more than extended distance of first protruding portion 17 from the rear 14；Second protruding portion 18 with it is described
Third protruding portion 19 slightly extends toward inclined downward, and 19 place horizontal plane of the Part III is located at 18 institute of the second part
In the top of horizontal plane.I.e. vertically on, the Part III 19 is located at the upside of the second part 18.
First protruding portion 17 can reduce the vortex of 16 part of blade tip formation and reduce by 16 part of the blade tip
Vortex intensity weakens the air pressure change degree near the blade tip 16, to reduce the air drag that the blade 10 is subject to, into
And increase the blade 10 has more preferably thrust or lift when rotated.
Second protruding portion 18 can preferably reduce the sky that 15 part of the petiole is subject to the third protruding portion 19
Atmidometer so that the blade 10 has more preferably thrust or lift when rotated.
Please refer to Fig. 4.Apart from the center of the fixed seat be the propeller 100 radius 40% at, institute
The angle of attack for stating blade is 13.64 ° ± 2.5 °, and the chord length of the blade is 48.74mm ± 5mm；
In the present embodiment, a diameter of 560mm ± 40mm for the paddle disk the to be formed specifically, propeller 100 rotates a circle,
At the fixed seat center 114.1mm, the angle of attack of the blade is 13.64 ° ± 2.5 °, and the chord length of the blade is
48.74mm±5mm。
Please refer to Fig. 5.Apart from the center of the fixed seat be the propeller 100 radius 70% at, institute
The angle of attack for stating blade is 8.03 ° ± 2.5 °, and the chord length of the blade is 35.84mm ± 5mm；
In the present embodiment, a diameter of 560mm ± 40mm for the paddle disk the to be formed specifically, propeller 100 rotates a circle,
At the fixed seat center 199.7mm, the angle of attack of the blade is 8.03 ° ± 2.5 °, and the chord length of the blade is
35.84mm±5mm。
Please refer to Fig. 6.Apart from the center of the fixed seat be the propeller 100 radius 97% at, institute
The angle of attack for stating blade is 5.41 ° ± 2.5 °, and the chord length of the blade is 21.79mm ± 5mm.
In the present embodiment, specifically, the propeller rotates a diameter of 560mm ± 40mm for the paddle disk that 100 1 weeks form,
At the fixed seat center 276.8mm, the angle of attack of the blade is 5.41 ° ± 2.5 °, and the chord length of the blade is
21.79mm±5mm。
Wherein, chord length refers to the endpoint Yu the rear 14 that the leading edge 13 is located at the rightmost side on the section at the section
The distance of the endpoint of the leftmost side in the horizontal direction on the section；It is most right on the section that the angle of attack refers to that the leading edge 13 is located at
The endpoint of side and the rear 14 are located at the connecting line between the endpoint of the section leftmost side and the angle between horizontal direction, or
Person's angle of attack it can be appreciated that the wing chord and gas direction of flow of the blade 10 angle.
It is changed with chord length by the angle of attack to 100 each position of the propeller so that the propeller 100 has more
Good flight effect improves thrust or lift when flight.
Table 1 is referred to, table 1 is the design parameter data of paddle disk, the angle of attack, chord length in the present embodiment.
【Table 1】
Table 2 is referred to, the comparison of propeller 100 described in the present embodiment and the test structure of traditional propeller, by table 2
As can be seen that in identical pulling force, to reduce kwh loss, increase cruising ability so that use the flight of the propeller 100
Device can have better thrust or lift, and have longer cruise duration.
【Table 2】
Compared with the relevant technologies, propeller of the invention passes through the shape of rational design blade so that uses the blade
Propeller can reduce air drag, to improve the working efficiency of propeller, and then increase the endurance distance of aircraft
And improve the flying quality of aircraft.
Above-described is only embodiments of the present invention, it should be noted here that for those of ordinary skill in the art
For, without departing from the concept of the premise of the invention, improvement can also be made, but these belong to the protection model of the present invention
It encloses.
Claims (10)
1. a kind of propeller, including：Fixed seat and blade, the blade are connected in the fixed seat, it is characterised in that：
Be apart from the center of the fixed seat radius of the propeller 40% at, the angle of attack of the blade is 13.64 ° ±
2.5 °, the chord length of the blade is 48.74mm ± 5mm；
Be apart from the center of the fixed seat radius of the propeller 70% at, the angle of attack of the blade is 8.03 ° ±
2.5 °, the chord length of the blade is 35.84mm ± 5mm；
Be apart from the center of the fixed seat radius of the propeller 97% at, the angle of attack of the blade is 5.41 ° ±
2.5 °, the chord length of the blade is 21.79mm ± 5mm.
2. propeller according to claim 1, it is characterised in that：The propeller rotates a circle the diameter of the paddle disk to be formed
For 560mm ± 40mm, at the fixed seat center 114.1mm, the angle of attack of the blade is 13.64 ° ± 2.5 °, described
The chord length of blade is 48.74mm ± 5mm.
3. propeller according to claim 1, it is characterised in that：The propeller rotates a circle the diameter of the paddle disk to be formed
For 560mm ± 40mm, at the fixed seat center 199.7mm, the angle of attack of the blade is 8.03 ° ± 2.5 °, described
The chord length of blade is 35.84mm ± 5mm.
4. propeller according to claim 1, it is characterised in that：The propeller rotates a circle the diameter of the paddle disk to be formed
For 560mm ± 40mm, at the fixed seat center 276.8mm, the angle of attack of the blade is 5.41 ° ± 2.5 °, described
The chord length of blade is 21.79mm ± 5mm.
5. propeller according to claim 1, it is characterised in that：The blade has blade back, opposite with the blade back sets
The blade face set, the connection blade face and the leading edge of described blade back a side and it connect the blade face and another side of the blade back
Rear, the blade back, the blade face, the leading edge and the rear are enclosed petiole and blade tip jointly, and the petiole is located at
Close to the fixed seat side, the blade tip is located remotely from the fixed seat side, from the petiole direction toward the blade tip side
It is gradually reduced to the area of section of the blade.
6. propeller according to claim 5, it is characterised in that：The rear is close to the part of the blade tip toward far from institute
It states leading edge direction and has extended to form the first protruding portion, first protruding portion is from close to the past separate leading edge in the leading edge direction
The area of section in direction is gradually reduced.
7. propeller according to claim 5, it is characterised in that：The rear is close to the part of the petiole toward far from institute
It states leading edge direction and has extended to form the second protruding portion, second protruding portion is from close to the past separate leading edge in the leading edge direction
The area of section in direction is gradually reduced, and the leading edge has been extended to form close to the part of the petiole toward far from the rear direction
Third protruding portion, area of section of the third protruding portion from close to the rear direction toward far from the rear direction gradually subtract
It is small.
8. propeller according to claim 1, it is characterised in that：There are two the blade is set, two blades are described in
Fixed seat center symmetric setting.
9. propeller according to claim 1, it is characterised in that：The blade is to fold blade.
10. propeller according to claim 8, it is characterised in that：The fixed seat is structure as a whole with the blade.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810298341X | 2018-03-30 | ||
| CN201810298341 | 2018-03-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108750074A true CN108750074A (en) | 2018-11-06 |
Family
ID=64002642
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810563390.1A Pending CN108750074A (en) | 2018-03-30 | 2018-06-04 | propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108750074A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588878A (en) * | 2019-09-20 | 2019-12-20 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080240923A1 (en) * | 2007-03-27 | 2008-10-02 | Laurent Bonnet | Rotor blade for a wind turbine having a variable dimension |
| RU2374137C1 (en) * | 2008-04-01 | 2009-11-27 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Helicopter rotor, rotor blade |
| CN206719544U (en) * | 2017-05-08 | 2017-12-08 | 浙江杭一电器有限公司 | Propeller and the unmanned plane for installing the propeller |
| CN207000809U (en) * | 2017-04-07 | 2018-02-13 | 深圳市大疆创新科技有限公司 | Blade, propeller, power suit and unmanned vehicle |
| CN207045700U (en) * | 2017-07-28 | 2018-02-27 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and unmanned plane for unmanned plane |
-
2018
- 2018-06-04 CN CN201810563390.1A patent/CN108750074A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080240923A1 (en) * | 2007-03-27 | 2008-10-02 | Laurent Bonnet | Rotor blade for a wind turbine having a variable dimension |
| RU2374137C1 (en) * | 2008-04-01 | 2009-11-27 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Helicopter rotor, rotor blade |
| CN207000809U (en) * | 2017-04-07 | 2018-02-13 | 深圳市大疆创新科技有限公司 | Blade, propeller, power suit and unmanned vehicle |
| CN206719544U (en) * | 2017-05-08 | 2017-12-08 | 浙江杭一电器有限公司 | Propeller and the unmanned plane for installing the propeller |
| CN207045700U (en) * | 2017-07-28 | 2018-02-27 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and unmanned plane for unmanned plane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588878A (en) * | 2019-09-20 | 2019-12-20 | 辽宁壮龙无人机科技有限公司 | Manufacturing method of propeller and propeller |
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