CN206914624U - A kind of propeller, Power Component and aircraft - Google Patents
A kind of propeller, Power Component and aircraft Download PDFInfo
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- CN206914624U CN206914624U CN201720633833.0U CN201720633833U CN206914624U CN 206914624 U CN206914624 U CN 206914624U CN 201720633833 U CN201720633833 U CN 201720633833U CN 206914624 U CN206914624 U CN 206914624U
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- oar
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Abstract
It the utility model is related to unmanned air vehicle technique field, and in particular to a kind of propeller, including blade, the blade rotate to form oar disk；The blade at a distance of being that the angle of attack at the α of oar disk radius is β, and is meeting following condition with the center of the oar disk：As 0≤α≤20%, 0 ° of 17.89 ° of ＜ β ＜；As 20≤α≤40%, 17.79 ° of 21.92 ° of ＜ β ＜；As 40≤α≤60%, 11.07 ° of 17.79 ° of ＜ β ＜；As 60≤α≤80%, 7.26 ° of 11.07 ° of ＜ β ＜；As 80≤α≤100%, 2.40 ° of 7.26 ° of ＜ β ＜.Propeller, Power Component and aircraft provided by the utility model, it can reduce in flight course to the resistance of propeller, improve the lift to propeller, extend cruising time and the flying distance of aircraft, improve flight efficiency.
Description
Technical field
It the utility model is related to unmanned air vehicle technique field, and in particular to a kind of propeller, Power Component and aircraft.
Background technology
Multi-rotor unmanned aerial vehicle is called Multi-axis aircraft, is controlled by the independent power system of three or more than three each
Kind device, simple in construction, control can be achieved in the rotating speed coordinated between motor, and attitude of flight vehicle holding capacity is higher, with non-
Often wide uses field and researching value.
Primary Component of the propeller as dynamical system, it is rotated by itself is converted into power by motor rotative power；
Efficient propeller can greatly improve the flying quality of unmanned plane, but the blade of existing propeller is mostly rectangle, fly
Resistance is larger, less efficient during row, so as to shorten the cruising time of aircraft, and cause the flying speed of aircraft compared with
It is small, extreme influence is caused to the flying quality of aircraft.
Utility model content
The utility model is in order to solve the above-mentioned technical problem, there is provided a kind of propeller, Power Component and aircraft, it can be carried
High aircraft flying quality, reduce flight resistance, extend cruising time.
In order to reach above-mentioned technique effect, the utility model includes following technical scheme：A kind of propeller, including blade,
The blade rotates to form oar disk；The blade with the center of the oar disk at a distance of being that the angle of attack at the α of oar disk radius is β,
And meet following condition：
As 0≤α≤20%, 0 ° of 17.89 ° of ＜ β ＜；
As 20≤α≤40%, 17.79 ° of 21.92 ° of ＜ β ＜；
As 40≤α≤60%, 11.07 ° of 17.79 ° of ＜ β ＜；
As 60≤α≤80%, 7.26 ° of 11.07 ° of ＜ β ＜；
As 80≤α≤100%, 2.40 ° of 7.26 ° of ＜ β ＜.
Propeller as described above,
At apart from the center of the oar disk for the 20% of the oar disk radius, the chord length of the blade is the blade
35.83 millimeters, the angle of attack is 17.89 °；
At apart from the center of the oar disk for the 40% of the oar disk radius, the chord length of the blade is the blade
44.34 millimeters, the angle of attack is 17.79 °；
At apart from the center of the oar disk for the 60% of the oar disk radius, the chord length of the blade is the blade
34.43 millimeters, the angle of attack is 11.01 °；
At apart from the center of the oar disk for the 80% of the oar disk radius, the chord length of the blade is the blade
26.40 millimeters, the angle of attack is 7.26 °；
At apart from the center of the oar disk for the 100% of the oar disk radius, the chord length of the blade is the blade
12.97 millimeters, the angle of attack is 2.40 °.
The blade has two, and two blades are centrosymmetric on the center of oar disk, is pressed from both sides between two blades by oar
Connection.
In certain embodiments, the blade includes tea residue portion, leaf central part and blade tip, and the blade presss from both sides phase with the oar
It is tea residue portion to meet place, and the blade edge relative with tea residue portion is blade tip, connects the portion in the tea residue portion and the blade tip
It is divided into the leaf central part.
Further, in certain embodiments, the blade thickness is gradually reduced by tea residue portion along the direction of blade tip.
In certain embodiments, the blade width is gradually increased, by leaf central part by tea residue portion along the leaf central part direction
It is gradually reduced along the blade tip direction.
In certain embodiments, tea residue portion, leaf central part and the blade tip are collectively forming upward oar face, downward oar
The first side end for carry on the back, being connected between the oar face and oar back of the body side and it is connected to the oar face and the oar back of the body is another
The second side end between side；The oar face and the oar back of the body are all curved surface；
First side end includes the first side end a and the first side end b positioned at leaf central part positioned at tea residue portion,
Second side end a and second side end b positioned at leaf central part of second side end including being located at tea residue portion, described first
Side end a has curved the first lug boss to be arched upward to oar face, and the second side end a has curved recessed to the oar back of the body
The first sunken concave part；
The first side end b has curved the second lug boss risen laterally and to oar rear arch, second side
End b has curved the 3rd lug boss risen laterally and to oar rear arch；
The protrusion degree of second lug boss is more than the protrusion degree of the 3rd lug boss.
On the other hand, the utility model provides a kind of Power Component, including motor and above-mentioned propeller, the propeller
Pass through oar folder and the motor connection.
The another aspect of the utility model provides a kind of aircraft, including fuselage and above-mentioned Power Component, the power packages
Part is connected with the fuselage.
Using above-mentioned technical proposal, including following beneficial effect：Propeller provided by the utility model, Power Component and
Aircraft, it can reduce in flight course to the resistance of propeller, improve the lift to propeller, extend the continuous of aircraft
ETS estimated time of sailing and flying distance, improve flight efficiency.
Brief description of the drawings
Fig. 1 is provided the structural representation of propeller by the utility model embodiment；
Fig. 2 is provided the top view of blade by the utility model embodiment；
Fig. 3 is provided the schematic diagram that different cross section is divided on blade by the utility model embodiment；
Fig. 4 is the structural representation of Section A-A in Fig. 3；
Fig. 5 is the structural representation of section B-B in Fig. 3；
Fig. 6 is the structural representation in C-C sections in Fig. 3；
Fig. 7 is the structural representation in D-D sections in Fig. 3；
Fig. 8 is the structural representation in E-E sections in Fig. 3；
Fig. 9 is the left view of blade shown in Fig. 2；
Figure 10 is the right view of blade shown in Fig. 2
In figure,
1st, blade；110th, tea residue portion；111st, leaf central part；112nd, blade tip；1101st, the first side end a；1102nd, the second side
End a；1110th, the first side end b；1111st, the second side end b；121st, oar face；122nd, oar is carried on the back；2nd, oar presss from both sides.
Embodiment
To make the purpose of this utility model, technical scheme and advantage clearer, implement below in conjunction with the utility model
Accompanying drawing in example, the technical scheme in the embodiment of the utility model is clearly and completely described, it is clear that described reality
It is the utility model part of the embodiment to apply example, rather than whole embodiments.Based on the embodiment in the utility model, ability
The every other embodiment that domain those of ordinary skill is obtained under the premise of creative work is not made, it is new to belong to this practicality
The scope of type protection.
In the utility model, term " on ", " under ", "left", "right", "front", "rear", " top ", " bottom ", " interior ", " outer ",
" in ", " vertical ", " level ", " transverse direction ", the orientation of the instruction such as " longitudinal direction " or position relationship be based on orientation shown in the drawings or
Position relationship.These terms are not intended to limit indicated primarily to preferably describe the utility model and embodiment
Device, element or part must have particular orientation, or constructed and operated with particular orientation.
Also, above-mentioned part term is in addition to it can be used to indicate that orientation or position relationship, it is also possible to for representing it
His implication, such as term " on " also be likely used for representing certain relations of dependence or annexation in some cases.For ability
For the those of ordinary skill of domain, concrete meaning of these terms in the utility model can be understood as the case may be.
In addition, term " installation ", " setting ", " being provided with ", " connection ", " connected " " socket " should be interpreted broadly.For example, can
To be to be fixedly connected, it is detachably connected, or monolithic construction；Can mechanically connect, or electrical connection；Can be joined directly together,
Either it is indirectly connected by intermediary, or is connection internal between two devices, element or parts.For
For those of ordinary skill in the art, concrete meaning of the above-mentioned term in the utility model can be understood as the case may be.
Unless otherwise indicated, the implication of " multiple " is two or more.
The utility model is described in further detail below by specific embodiment and with reference to accompanying drawing.
Embodiment 1：
A kind of design of new type propeller is present embodiments provided, existing propeller is overcome and resistance in the application be present
The defects of power is big, cruising time section, the technical scheme that the embodiment provides can apply to conventional 22 cun or 28 cun of propellers,
But above-mentioned size and model are not limited to, higher flight efficiency can be obtained.
In the present embodiment, propeller can be positive oar or anti-oar, and positive oar refers to from the point of view of aircraft is overlooked, clockwise
Rotate and produce the propeller of lift；Anti- oar refers to from the point of view of aircraft is overlooked, rotate counterclockwise and the spiral shell for producing lift
Revolve oar.The present embodiment only illustrates by taking the structure of positive oar as an example, and those skilled in the art can be according to the positive oar knot provided
Structure expands to anti-oar.
In addition, the propeller that the present embodiment is provided is applied to Multi-axis aircraft, such as four-axle aircraft, six axles or eight axles
Aircraft, the blade on each propeller can be two, three or more, and the present embodiment is with two blades on a propeller
Mode exemplified by illustrate.
A kind of propeller as shown in Figure 1, including blade 1, the rotation of blade 1 form oar disk, and blade has two and closed
It is centrosymmetric in the center of oar disk, it is possible thereby to improve the balance of propeller, passes through the connection of oar folder 2 between two blades 1.
Refering to Fig. 2, blade 1 includes tea residue portion 110, leaf central part 111 and blade tip 112, and the blade 1 presss from both sides 2 joints with the oar and is
Tea residue portion 110, blade 1 edge relative with tea residue portion 110 are blade tip 112, connect the tea residue portion 110 and the end of blade
The part in portion 112 is the leaf central part 111.Further, in certain embodiments, the blade thickness is by the edge of tea residue portion 110
The direction of blade tip 112 is gradually reduced.Further, the blade width by tea residue portion 110 along the direction of leaf central part 111 by
It is cumulative plus, be gradually reduced along the direction of blade tip 110 by leaf central part 111, to the resistance of propeller when being advantageous to reduce flight,
Flying speed is improved, extends cruising time.
Refering to Fig. 3, blade is, at a distance of being that the angle of attack at the α of oar disk radius is β, the wherein angle of attack is with the center of the oar disk
The string wing and the angle of gas direction of flow, and meet following condition：
As 0≤α≤20%, 0 ° of 17.89 ° of ＜ β ＜；As 20≤α≤40%, 17.79 ° of 21.92 ° of ＜ β ＜；When 40≤
During α≤60%, 11.07 ° of 17.79 ° of ＜ β ＜；As 60≤α≤80%, 7.26 ° of 11.07 ° of ＜ β ＜；When 80≤α≤100%
When, 2.40 ° of 7.26 ° of ＜ β ＜.
As shown in figure 4, blade apart from the center of the oar disk for the oar disk radius 20% at, the string of the blade
Long L1 is 35.83 millimeters, and angle of attack M1 is 17.89 °；
As shown in figure 5, the blade apart from the center of the oar disk for the oar disk radius 40% at, the blade
Chord length L2 be 44.34 millimeters, angle of attack M2 be 17.79 °；
Blade is at apart from the center of the oar disk for the 60% of the oar disk radius as described in Figure 6, the string of the blade
Long L3 is 34.43 millimeters, and angle of attack M3 is 11.01 °；
As shown in fig. 7, the blade apart from the center of the oar disk for the oar disk radius 80% at, the blade
Chord length L4 be 26.40 millimeters, angle of attack M4 be 7.26 °；
As shown in figure 8, the blade apart from the center of the oar disk for the oar disk radius 100% at, the oar
The chord length L5 of leaf is 12.97 millimeters, and angle of attack M5 is 2.40 °.
The present embodiment at the diverse location of blade radius by setting different blade chord lengths and the angle of attack, in identical energy consumption
Under, the lift of propeller is improved, reduces air drag, extends flying distance, improves flying quality.
In the present embodiment, Fig. 9 and 10,112 common shape of the tea residue portion 110, leaf central part 111 and blade tip are referred to while
Into upward oar face 121, the downward oar back of the body 122, the first side being connected between 122 sides of the oar face 121 and the oar back of the body
End and the second side end being connected between the oar face 121 and the oar 122 opposite sides of the back of the body；The oar face 121 and oar
The back of the body 122 is all curved surface, and when blade 1 is in horizontality, the location of first side end is less than residing for the second side end
Position, the structure design can reduce resistance of the air to blade, improve propeller flight efficiency.
Wherein, the first side end is included positioned at the first side end a1101 in tea residue portion 110 and positioned at leaf central part 111
First side end b1110, the first side end a1101 are connected smoothly with the first side end b1110, the first side end b1110
Positioned at the nearly end of tea residue portion 110 of leaf central part 111；Second side end includes the second side end a1102 positioned at tea residue portion 110
And the second side end b1111 positioned at leaf central part 111, the second side end a1102 and the second side end b1111 seamlessly transit company
Connect, the first side end a1101 has curved the first lug boss to be arched upward to oar face 121, second side end
A1102 has curved the first concave part to the depression of the oar back of the body 122；First side end a1101 and the second side end a1102 with
Oar face 121 is connected smoothly everywhere, and the design of the first lug boss and the first concave part improves the lift of blade, reduces sky
Atmidometer, while be advantageous to improve the reliability of propeller.
The first side end b1110 has curved the second lug boss to arch upward laterally and to the oar back of the body 122, described
Second side end b1111 has curved the 3rd lug boss to arch upward laterally and to the oar back of the body 122；Wherein, the second lug boss
Degree of convexity be more than the 3rd lug boss degree of convexity, oar face seamlessly transits everywhere.The protrusion degree of second lug boss
More than the protrusion degree of the 3rd lug boss.
The above-mentioned propeller that the present embodiment is provided, by the contrast with propeller in the prior art, understood refering to table one,
Under identical pulling force, the power for the propeller that the present embodiment is provided is lower, and rotating speed turns apparently higher than existing propeller
Speed, i.e., there is bigger pulling force under smaller power, or under same rotational speed, spiral is smaller by required pulling force, saves electricity
Amount consumption, extends cruising time and flying distance, improves flight efficiency.
Reduced parameter of the table one by the propeller that the present embodiment provides and existing propeller.
Embodiment 2：
Present embodiments provide a kind of Power Component, including motor and above-mentioned propeller, the propeller by oar folder with
The motor connection, wherein, propeller can use the mode that is detachably connected with oar folder, and motor driven oar folder rotates, so as to band
The blade of dynamic propeller rotates, the present embodiment on the basis of embodiment 1, by blade at different radii chord length and the angle of attack
Setting, reduces the air in rotation process and, to the resistance of propeller, extends flight cruising time.
Embodiment 3：
Present embodiments provide a kind of aircraft, including fuselage and above-mentioned Power Component, the Power Component and the machine
Body connects, wherein, the number of Power Component can be aircraft multiple, that the present embodiment provides, employ dynamic in embodiment 2
Power component, unmanned plane during flying efficiency is improved, improves flying quality.
Preferred embodiment of the present utility model is the foregoing is only, is not limited to the utility model, for this
For the technical staff in field, the utility model can have various modifications and variations.It is all in the spirit and principles of the utility model
Within, any modification, equivalent substitution and improvements made etc., it should be included within the scope of protection of the utility model.
Claims (10)
1. a kind of propeller, including blade, it is characterised in that the blade rotates to form oar disk；The blade with the oar
The center of disk is apart that the angle of attack at the α of oar disk radius is β, and meets following condition：
As 0≤α≤20%, 0 ° of 17.89 ° of ＜ β ＜；
As 20≤α≤40%, 17.79 ° of 21.92 ° of ＜ β ＜；
As 40≤α≤60%, 11.07 ° of 17.79 ° of ＜ β ＜；
As 60≤α≤80%, 7.26 ° of 11.07 ° of ＜ β ＜；
As 80≤α≤100%, 2.40 ° of 7.26 ° of ＜ β ＜.
2. propeller according to claim 1, it is characterised in that
For the blade at apart from the center of the oar disk for the 20% of the oar disk radius, the chord length of the blade is 35.83
Millimeter, the angle of attack are 17.89 °；
For the blade at apart from the center of the oar disk for the 40% of the oar disk radius, the chord length of the blade is 44.34
Millimeter, the angle of attack are 17.79 °；
For the blade at apart from the center of the oar disk for the 60% of the oar disk radius, the chord length of the blade is 34.43
Millimeter, the angle of attack are 11.01 °；
For the blade at apart from the center of the oar disk for the 80% of the oar disk radius, the chord length of the blade is 26.40
Millimeter, the angle of attack are 7.26 °；
For the blade at apart from the center of the oar disk for the 100% of the oar disk radius, the chord length of the blade is 12.97
Millimeter, the angle of attack are 2.40 °.
3. propeller according to claim 1, it is characterised in that the blade（1）There are two, two blades（1）On
The center of oar disk is centrosymmetric, two blades（1）Between pass through oar folder connection.
4. propeller according to claim 3, it is characterised in that the blade（1）Including tea residue portion（110）, leaf central part
（111）And blade tip（112）, the blade（1）Pressed from both sides with the oar（2）Joint is tea residue portion（110）, with tea residue portion（110）
Relative blade edge is blade tip（112）, connect the tea residue portion（110）With the blade tip（112）Part be institute
State leaf central part（111）.
5. propeller according to claim 4, it is characterised in that the blade（1）Thickness is by tea residue portion（110）Along end of blade
Portion（112）Direction be gradually reduced.
6. propeller according to claim 5, it is characterised in that the blade（1）Width is by tea residue portion（110）Described in
Leaf central part（111）Direction gradually increases, by leaf central part（111）Along the blade tip（112）Direction is gradually reduced.
7. propeller according to claim 6, it is characterised in that the tea residue portion（110）, leaf central part（111）And end of blade
Portion（112）It is collectively forming upward oar face（121）, the downward oar back of the body（122）, be connected to the oar face（121）And the oar back of the body
（122）The first side end between side and the second side end being connected between the oar face and oar back of the body opposite side；
The oar face and the oar back of the body are all curved surface.
8. propeller according to claim 7, it is characterised in that first side end includes being located at tea residue portion（110）
The first side end a（1101）And positioned at leaf central part（111）The first side end b（1110）；Second side end includes
Positioned at tea residue portion（110）The second side end a（1102）And positioned at leaf central part（111）The second side end b（1111）, it is described
First side end a（1101）With curved to oar face（121）The first lug boss to arch upward, the second side end a
（1102）Carried on the back with curved to oar（122）First concave part of depression；
The first side end b（1110）With it is curved laterally and to oar carry on the back（122）The second lug boss to arch upward, it is described
Second side end b（1111）With it is curved laterally and to oar carry on the back（122）The 3rd lug boss to arch upward；
The protrusion degree of second lug boss is more than the protrusion degree of the 3rd lug boss.
A kind of 9. Power Component, it is characterised in that the propeller including motor and as described in claim 1-8 any one,
The propeller passes through oar folder and the motor connection.
10. a kind of aircraft, including fuselage, it is characterised in that also including the Power Component described in claim 9, the power
Component is connected with the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720633833.0U CN206914624U (en) | 2017-06-02 | 2017-06-02 | A kind of propeller, Power Component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720633833.0U CN206914624U (en) | 2017-06-02 | 2017-06-02 | A kind of propeller, Power Component and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN206914624U true CN206914624U (en) | 2018-01-23 |
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ID=61314429
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720633833.0U Active CN206914624U (en) | 2017-06-02 | 2017-06-02 | A kind of propeller, Power Component and aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| WO2019205497A1 (en) * | 2018-04-25 | 2019-10-31 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
-
2017
- 2017-06-02 CN CN201720633833.0U patent/CN206914624U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| WO2019205497A1 (en) * | 2018-04-25 | 2019-10-31 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
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Effective date of registration: 20180511 Address after: 210008 707 floor, 7 floor, South Tower, 1 West Spring Road, Yuhuatai District, Nanjing, Jiangsu. Patentee after: Nanjing Tuo tapping Aeronautical Science and Technology Co., Ltd. Address before: 201306 C1935 room 24, 2 New Town Road, mud town, Pudong New Area, Shanghai Patentee before: SHANGHAI TOPXGUN ROBOT CO., LTD. |
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