CN206297727U - Propeller, Power Component and aircraft - Google Patents
Propeller, Power Component and aircraft Download PDFInfo
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- CN206297727U CN206297727U CN201621311450.3U CN201621311450U CN206297727U CN 206297727 U CN206297727 U CN 206297727U CN 201621311450 U CN201621311450 U CN 201621311450U CN 206297727 U CN206297727 U CN 206297727U
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Abstract
The utility model provides a kind of propeller, including propeller hub and the blade being connected on propeller hub, and blade is rotated centered on propeller hub and forms oar disk, wherein：Blade apart from propeller hub center be oar disk radius 59.06% at the angle of attack be 18.2 ± 2.5 °, chord length be 15.6mm ± 3mm, blade apart from propeller hub center be oar disk radius 72.18% at the angle of attack be 16.7 ± 2.5 °, chord length be 13.3mm ± 3mm；Blade apart from propeller hub center be oar disk radius 85.3% at the angle of attack be 14.5 ± 2.5 °, chord length be 10.7mm ± 3mm.The propeller that the utility model is provided is by the improvement to the angle of attack and chord length in blade, at rear portion, propeller is increased to rotate a circle the air capacity of discharge, improve maximum thrust, and resistance of the propeller in rotation process can be reduced, improve the flying speed of aircraft, extend distance to go under the supply of energy consumption identical condition, lift flying quality.The utility model additionally provides a kind of Power Component and aircraft using above-mentioned propeller.
Description
Technical field
The utility model is related to Propeller technology field, more particularly to a kind of propeller, Power Component and aircraft.
Background technology
Carry-on propeller, used as the important Primary Component of aircraft, it is used for rotating shaft in motor or engine
Rotation be converted into thrust or lift.Propeller of the prior art, its outer shape is mostly rectangular, and its resistance is big, efficiency
Low, the flying speed that causes aircraft is slow, cruising time is short, has had a strong impact on the flying quality of aircraft.
Utility model content
Based on this, it is necessary to which the resistance that exists for current propeller is big, the low problem of efficiency, there is provided one kind can subtract
Few resistance, raising efficiency, and aircraft cruising time can be increased, lift the propeller of aircraft flight performance.
Above-mentioned purpose is achieved through the following technical solutions：
A kind of propeller, including propeller hub and the blade being connected on propeller hub, the blade rotate formation centered on propeller hub
Oar disk, wherein：
The blade is being that the angle of attack at the oar disk radius 59.06% is 18.2 ± 2.5 °, chord length apart from propeller hub center
It is 15.6mm ± 3mm；
The blade is being that the angle of attack at the oar disk radius 72.18% is 16.7 ± 2.5 °, chord length apart from propeller hub center
It is 13.3mm ± 3mm；
The blade is being that the angle of attack at the oar disk radius 85.3% is 14.5 ± 2.5 ° apart from propeller hub center, and chord length is
10.7mm±3mm。
Wherein in one embodiment, the blade is being attacking at the oar disk radius 45.93% apart from propeller hub center
Angle is 19.4 ± 2.5 °, and chord length is 17.5mm ± 3mm.
Wherein in one embodiment, the blade is being attacking at the oar disk radius 32.81% apart from propeller hub center
Angle is 20.6 ± 2.5 °, and chord length is 18.8mm ± 3mm.
Wherein in one embodiment, the blade is being attacking at the oar disk radius 98.43% apart from propeller hub center
Angle is 11.6 ± 2.5 °, and chord length is 6.1mm ± 3mm.
Wherein in one embodiment, the blade is being attacking at the oar disk radius 19.69% apart from propeller hub center
Angle is 22.8 ± 2.5 °, and chord length is 17.3mm ± 3mm.
Wherein in one embodiment, a diameter of 152.4mm ± 30mm of the oar disk.
Wherein in one embodiment, the blade includes blade back, a blade face directed downwardly upward, is connected to institute
A leading edge between the side on blade back and the blade face is stated, and is connected between the opposite side on the blade back and the blade face
The cross section on one trailing edge, the cross section of the blade back and the blade face bends, and the trailing edge is located at the lower section of leading edge.
Wherein in one embodiment, the blade face includes a curved first downwardly projecting protuberance, described
Leading edge includes a curved second outwardly protuberance, and the trailing edge includes one curved outwardly the
Three protuberances.
Wherein in one embodiment, first protuberance, the second protuberance, the 3rd protuberance are close to propeller hub.
Wherein in one embodiment, the pitch of the propeller is 105mm.
Wherein in one embodiment, the blade at least two panels on propeller hub is connected to, the blade is circumferential around propeller hub
Even distribution.
Wherein in one embodiment, blade is folding blade.
The utility model additionally provides a kind of Power Component, including actuator and any above-mentioned propeller, the driving
Part is connected with propeller hub, and the KV values of the actuator are that 1000-1500 turns/(minute volt).
The utility model additionally provides a kind of aircraft, including fuselage and at least one above-mentioned Power Component, described dynamic
Power component is connected with fuselage.
The beneficial effects of the utility model are：The propeller that the utility model is provided in blade, at rear portion by attacking
Angle and the improvement of chord length, increased propeller and rotate a circle the air capacity of discharge, improve maximum thrust, and can reduce spiral shell
Rotation resistance of the oar in rotation process, improves the flying speed of aircraft, extend under the supply of energy consumption identical condition navigation away from
From lifting flying quality.
Brief description of the drawings
Fig. 1 is the front view of the rotating forward blade of the propeller of the utility model embodiment；
Fig. 2 is the front view of the reversion blade of the propeller of the utility model embodiment.
Fig. 3 is the stereogram of the rotating forward blade of the propeller of the utility model embodiment；
Fig. 4 is the sectional view in R-R directions in Fig. 1；
Fig. 5 is the sectional view in T-T directions in Fig. 1；
Fig. 6 is the sectional view in U-U directions in Fig. 1；
Fig. 7 is the sectional view in V-V directions in Fig. 1；
Fig. 8 is the sectional view in W-W directions in Fig. 1；
Fig. 9 is the sectional view in Y-Y directions in Fig. 1；
Figure 10 is the sectional view in AA-AA directions in Fig. 1.
Wherein：
100- propeller hubs；
200- blades；
210- blade backs；
220- blade faces；
230- trailing edges；
240- leading edges.
Specific embodiment
In order that the purpose of this utility model, technical scheme and advantage become more apparent, by the following examples, and tie
Accompanying drawing is closed, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only used to solve
The utility model is released, is not used to limit the utility model.
The propeller that the utility model is provided can be positive oar or anti-oar, and so-called positive oar refers to dextrorotation and transfers to produce
The propeller of raw lift；So-called anti-oar, refers to rotate counterclockwise and produces the propeller of lift.As depicted in figs. 1 and 2, just
The structure of oar is symmetrical in minute surface with the structure of anti-oar, is only illustrated by taking the structure of positive oar as an example in the present embodiment, ability
Field technique personnel can be extended according to present embodiment and obtain the structure of anti-oar.
As shown in figures 1 and 3, the propeller that the utility model is provided includes propeller hub 100 and the oar being connected on propeller hub 100
Leaf 200, blade 200 is rotated centered on propeller hub 100 and forms oar disk, and the quantity of blade 200 can be more for more than a piece of or two panels
Piece blade 200 can circumferentially be uniformly distributed around propeller hub 100, and the blade 200 in this implementation is two panels, and two panels blade 200 is with propeller hub
100 revenue centre is symmetrical, i.e., wherein a piece of blade 200 can be complete with another blade 200 around 180 ° of 100 central rotation of propeller hub
Overlap.
Blade 200 includes 210, blade face directed downwardly 220 of a blade back upward, is connected to blade back 210 and blade face 220
Side between a leading edge 240, and be connected to a trailing edge 230 between the opposite side on blade back 210 and blade face 220, leaf
The cross section of the back of the body 210 and the cross section on blade face 220 bend, and trailing edge 230 is located at the lower section of leading edge 240.
Blade face 220 include a curved first downwardly projecting protuberance, leading edge 240 include one it is curved to
Second protuberance of outer protrusion, trailing edge 230 includes curved a 3rd outwardly protuberance.First protuberance,
Two protuberances, the 3rd protuberance are close to propeller hub.The surface of blade 200 is and seamlessly transits, without part is drastically reversed, so tool
There is less stress, intensity is high, is not easily broken, with reliability higher.
Referring to shown in Fig. 4 to Figure 10, this programme is improved the shape and sectional dimension of blade, to improve propeller
Performance.It is described for the ease of pair cross-section size-modify point, the definition involved by improvement is illustrated first：Chord length,
Refer to blade leading edge in the end points of the leftmost side on the section, in the end points of the section rightmost side, two-end-point is in the horizontal direction for trailing edge
Distance；The angle of attack refers to leading edge in the end points of the leftmost side on the section, trailing edge in the end points of the section rightmost side, two-end-point it
Between line and horizontal direction angle, the angle of attack is exactly the angle between blade wing chord and speed of incoming flow in other words；Pitch, refer to
Propeller rotates a circle, theoretical climb.
Blade main thrust (lift) is primarily generated on the paddle member apart between propeller hub center 60%-90% radiuses,
Maximum thrust occurs at the propeller-blade section of radius of turn about 75%, therefore, at the V-V in Fig. 7, at the W-W in Fig. 8 and figure
The improvement of size is mostly important at Y-Y in 9, and specific sectional dimension is as follows：
As shown in fig. 7, blade apart from propeller hub center be oar disk radius 59.06% at angle of attack A4 be 18.2 ± 2.5 °,
Chord length D4 is 15.6mm ± 3mm.
As shown in figure 8, blade apart from propeller hub center be oar disk radius 72.18% at angle of attack A5 be 16.7 ± 2.5 °,
Chord length D5 is 13.3mm ± 3mm.
As shown in figure 9, blade apart from propeller hub center be oar disk radius 85.3% at angle of attack A6 be 14.5 ± 2.5 °, string
D6 long is 10.7mm ± 3mm.
Further,
As shown in figure 4, blade apart from propeller hub center be oar disk radius 19.69% at angle of attack A1 be 22.8 ± 2.5 °,
Chord length D1 is 17.3mm ± 3mm.
As shown in figure 5, blade apart from propeller hub center be oar disk radius 32.81% at angle of attack A2 be 20.6 ± 2.5 °,
Chord length D2 is 18.8mm ± 3mm.
As shown in fig. 6, blade apart from propeller hub center be oar disk radius 45.93% at angle of attack A3 be 19.4 ± 2.5 °,
Chord length D3 is 17.5mm ± 3mm.
As shown in Figure 10, blade apart from propeller hub center be oar disk radius 98.43% at angle of attack A7 be 11.6 ± 2.5 °,
Chord length D7 is 6.1mm ± 3mm.
The setting that this programme passes through the chord length and the angle of attack in the above-mentioned section in propeller blade, increased propeller rotation
One week air capacity of discharge, improves maximum thrust, and can reduce resistance of the propeller in rotation process, improves flight
The flying speed of device, distance to go is extended under the supply of energy consumption identical condition, lifts flying quality.
For above technical scheme, the present embodiment provides a kind of specific propeller, propeller oar disk it is a diameter of
152.4mm ± 30mm, the distance at the center of propeller hub 100 to the blade tip of blade 200 is the half of propeller oar disk diameter, i.e. propeller hub
100 center to the blade tip of blade 200 distance be 76.2mm ± 15mm.
By taking a diameter of 152.4mm of propeller oar disk as an example, blade apart from propeller hub center 45mm (i.e. 76.2mm's
59.06%) angle of attack A4 at place is 18.2 °, and chord length D4 is 15.6mm.
Blade is 16.7 ° in the angle of attack A5 apart from propeller hub center 55mm (i.e. the 72.18% of 76.2mm) place, and chord length D5 is
13.3mm。
Blade is 14.5 ° in the angle of attack A6 apart from propeller hub center 65mm (i.e. the 85.3% of 76.2mm) place, and chord length D6 is
10.7mm。
Further, blade is 19.4 ° in the angle of attack A3 apart from propeller hub center 35mm (i.e. the 45.93% of 76.2mm) place,
Chord length D3 is 17.5mm.
Blade is 20.6 ° in the angle of attack A2 apart from propeller hub center 25mm (i.e. the 32.81% of 76.2mm) place, and chord length D2 is
18.8mm。
Blade is 11.6 ° in the angle of attack A7 apart from propeller hub center 75mm (i.e. the 98.43% of 76.2mm) place, and chord length D7 is
6.1mm。
Blade is 22.8 ° in the angle of attack A1 apart from propeller hub center 15mm (i.e. the 19.69% of 76.2mm) place, and chord length D1 is
17.3mm。
To those skilled in the art, seven positions in section of the above can change, accordingly, above-mentioned seven sections
The angle of attack chord long value at place can also change accordingly.
In the above-described embodiments, the pitch of propeller rotates a circle for 105mm, i.e. propeller, and the distance that theory rises is
105mm。
The propeller that the present embodiment is provided, compared with propeller of the prior art, performance has a distinct increment, concrete
Can contrast and see the following table of comparisons.
Can substantially be learnt from the above performance table of comparisons, in the case where identical thrust (lift) is obtained, the spiral shell that the present embodiment is provided
The rotating speed for revolving oar is low, and noise is small, low in energy consumption；In rotating speed in the case of, the thrust of the propeller that the present embodiment is provided (rises
Power) it is big.
The utility model additionally provides the propeller in a kind of Power Component, including actuator and any of the above-described embodiment,
Actuator is connected with propeller hub.
Actuator output end drives propeller integral-rotation to produce thrust, and wherein actuator is preferably motor, the KV of motor
It is worth for 1000-1500 turns/(minute volt).
The utility model additionally provides a kind of aircraft, including fuselage and at least one above-mentioned Power Component, power packages
Part is connected with fuselage.Propeller wherein in Power Component is increased by the improvement to the angle of attack and chord length in blade, at rear portion
Add propeller to rotate a circle the air capacity of discharge, improve maximum thrust, and propeller can have been reduced in rotation process
Resistance, improve the flying speed of aircraft, extend distance to go under the supply of energy consumption identical condition, lift flying quality.
For the propeller provided in above example, propeller hub and blade can be integrally machined shaping, or divide
Not Jia Gong after be connected；Meanwhile, blade can be integral type blade, it is also possible in order to save accommodation space, and make composition
The collapsible blade of body, as long as collapsible blade meets the invention that this patent is can reach with the dimension limitation of upper section after deployment
Purpose.
Embodiment described above only expresses several embodiments of the present utility model, and its description is more specific and detailed,
But therefore can not be interpreted as the limitation to the utility model the scope of the claims.It should be pointed out that common for this area
For technical staff, without departing from the concept of the premise utility, various modifications and improvements can be made, these all belong to
In protection domain of the present utility model.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (14)
1. a kind of propeller, including propeller hub and the blade being connected on propeller hub, the blade are rotated centered on propeller hub and form oar
Disk, it is characterised in that
The blade is being that the angle of attack at the oar disk radius 59.06% is 18.2 ± 2.5 ° apart from propeller hub center, and chord length is
15.6mm±3mm；
The blade is being that the angle of attack at the oar disk radius 72.18% is 16.7 ± 2.5 ° apart from propeller hub center, and chord length is
13.3mm±3mm；
The blade is being that the angle of attack at the oar disk radius 85.3% is 14.5 ± 2.5 ° apart from propeller hub center, and chord length is
10.7mm±3mm。
2. propeller according to claim 1, it is characterised in that the blade is being the oar disk half apart from propeller hub center
The angle of attack at footpath 45.93% is 19.4 ± 2.5 °, and chord length is 17.5mm ± 3mm.
3. propeller according to claim 1, it is characterised in that the blade is being the oar disk half apart from propeller hub center
The angle of attack at footpath 32.81% is 20.6 ± 2.5 °, and chord length is 18.8mm ± 3mm.
4. propeller according to claim 1, it is characterised in that the blade is being the oar disk half apart from propeller hub center
The angle of attack at footpath 98.43% is 11.6 ± 2.5 °, and chord length is 6.1mm ± 3mm.
5. propeller according to claim 1, it is characterised in that the blade is being the oar disk half apart from propeller hub center
The angle of attack at footpath 19.69% is 22.8 ± 2.5 °, and chord length is 17.3mm ± 3mm.
6. according to any described propeller of claim 1 to 5, it is characterised in that a diameter of 152.4mm of the oar disk ±
30mm。
7. according to any described propeller of claim 1 to 5, it is characterised in that the blade include a blade back upward,
One blade face directed downwardly, is connected to a leading edge between the side on the blade back and the blade face, and be connected to the blade back
And a trailing edge between the opposite side on the blade face, the cross section on the cross section of the blade back and the blade face bends, institute
Trailing edge is stated positioned at the lower section of leading edge.
8. propeller according to claim 7, it is characterised in that the blade face include one it is curved downwardly projecting
First protuberance, the leading edge includes a curved second outwardly protuberance, and the trailing edge includes a curved surface
The 3rd outwardly protuberance of shape.
9. propeller according to claim 8, it is characterised in that first protuberance, the second protuberance, the 3rd protrude
Portion is close to propeller hub.
10. according to any described propeller of claim 1 to 5, it is characterised in that the pitch of the propeller is 105mm.
11. according to any described propeller of claim 1 to 5, it is characterised in that the blade being connected on propeller hub is at least two
Piece, the blade is circumferentially uniformly distributed around propeller hub.
12. propellers according to claim 11, it is characterised in that the blade is folding blade.
A kind of 13. Power Components, it is characterised in that the propeller including actuator and as described in claim 1 to 12 is any, institute
State actuator to be connected with propeller hub, the KV values of the actuator are that 1000-1500 turns/(minute volt).
A kind of 14. aircraft, including fuselage, it is characterised in that also including at least one power packages as claimed in claim 13
Part, the Power Component is connected with fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621311450.3U CN206297727U (en) | 2016-12-01 | 2016-12-01 | Propeller, Power Component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621311450.3U CN206297727U (en) | 2016-12-01 | 2016-12-01 | Propeller, Power Component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206297727U true CN206297727U (en) | 2017-07-04 |
Family
ID=59211973
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621311450.3U Active CN206297727U (en) | 2016-12-01 | 2016-12-01 | Propeller, Power Component and aircraft |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109071005A (en) * | 2017-07-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN109071006A (en) * | 2017-12-26 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| WO2019019332A1 (en) * | 2017-07-28 | 2019-01-31 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| WO2019019343A1 (en) * | 2017-07-25 | 2019-01-31 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| WO2019029026A1 (en) * | 2017-08-11 | 2019-02-14 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
| WO2019056558A1 (en) * | 2017-09-20 | 2019-03-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| WO2019148879A1 (en) * | 2018-01-31 | 2019-08-08 | 深圳市大疆创新科技有限公司 | Propeller, power component and aircraft |
| CN110896624A (en) * | 2018-05-25 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
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2016
- 2016-12-01 CN CN201621311450.3U patent/CN206297727U/en active Active
Cited By (14)
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| CN109937174A (en) * | 2017-07-25 | 2019-06-25 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| WO2019019343A1 (en) * | 2017-07-25 | 2019-01-31 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| CN109071005A (en) * | 2017-07-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| WO2019019332A1 (en) * | 2017-07-28 | 2019-01-31 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| US11364999B2 (en) | 2017-07-28 | 2022-06-21 | SZ DJI Technology Co., Ltd. | Rotor, power assembly and air vehicle |
| CN110214110A (en) * | 2017-07-28 | 2019-09-06 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| WO2019029026A1 (en) * | 2017-08-11 | 2019-02-14 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
| WO2019056558A1 (en) * | 2017-09-20 | 2019-03-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| CN109952247B (en) * | 2017-09-20 | 2022-05-10 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN109952247A (en) * | 2017-09-20 | 2019-06-28 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN109071006A (en) * | 2017-12-26 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN109071006B (en) * | 2017-12-26 | 2022-04-08 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| WO2019148879A1 (en) * | 2018-01-31 | 2019-08-08 | 深圳市大疆创新科技有限公司 | Propeller, power component and aircraft |
| CN110896624A (en) * | 2018-05-25 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Screw, power component and aircraft Effective date of registration: 20180102 Granted publication date: 20170704 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.) Pledgor: ZEROTECH (BEIJING) INTELLIGENCE TECHNOLOGY Co.,Ltd.|CHONGQING ZERO INTELLIGENT CONTROL TECHNOLOGY CO.,LTD. Registration number: 2017990001217 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20221008 Granted publication date: 20170704 Pledgee: XinDa national equity investment fund (Shanghai) partnership (L.P.) Pledgor: CHONGQING ZERO INTELLIGENT CONTROL TECHNOLOGY CO.,LTD. Registration number: 2017990001217 |