CN207045700U - Propeller, Power Component and unmanned plane for unmanned plane - Google Patents
Propeller, Power Component and unmanned plane for unmanned plane Download PDFInfo
- Publication number
- CN207045700U CN207045700U CN201720930041.XU CN201720930041U CN207045700U CN 207045700 U CN207045700 U CN 207045700U CN 201720930041 U CN201720930041 U CN 201720930041U CN 207045700 U CN207045700 U CN 207045700U
- Authority
- CN
- China
- Prior art keywords
- blade
- propeller
- oar
- attack
- angle
- 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.)
- Expired - Fee Related
Links
Abstract
A kind of propeller for unmanned plane, including blade；The blade includes blade root (110) and the blade tip (120) away from the blade root (110)；The blade has the leading edge (150) of blade face (130), blade back (140), connection blade face (130) and the side of blade back (140) one and connects the trailing edge (160) of blade face (130) and blade back (140) another side；And, the leading edge (150) is bent to form toward first direction close to the part of blade tip (120) and opens up the first suppressing portion to flowing for suppressing air, wherein the first direction is the direction that the leading edge (150) arrives trailing edge (160).Propeller of the present utility model can reduce the noise during propeller rotational, improve the security performance of aircraft.The utility model also provides a kind of Power Component and unmanned plane.
Description
Technical field
A kind of propeller, Power Component and unmanned plane for unmanned plane is the utility model is related to, belongs to unmanned air vehicle technique
Field.
Background technology
Propeller is the important component of rotary wind type unmanned plane, and it is used to the rotation of motor output shaft being converted into thrust or liter
Power is to realize the landing of unmanned plane, steering, hovering etc..Due to the structure and working characteristics of propeller, when it rotates, have one
Determine thickness blade can periodically inswept ambient air medium, cause the periodicity non-stationary motion of air micelle, so as to produce
Raw thickness noise, at the same time, the pressure field on blade blade face can also change, so as to produce load noise.These thickness are made an uproar
Sound and load noise, which are superimposed, forms the major part of unmanned plane noise, and it not only pollutes the spatial domain environment of surrounding,
And these noises can be traveled on the fuselage of unmanned plane, cause the vibration of unmanned aerial vehicle body, have a strong impact on the flight of unmanned plane
Safety.
Utility model content
In order to solve above-mentioned present in prior art or other potential problems, the utility model embodiment provides a kind of use
In the propeller, Power Component and unmanned plane of unmanned plane.
According to the embodiment of the utility model one, there is provided a kind of propeller for unmanned plane, including blade；The blade bag
Include blade root and the blade tip away from the blade root；Before the blade has blade face, blade back, connection blade face and the side of blade back one
Edge and the trailing edge of connection blade face and another side of blade back；And the leading edge close to the part of blade tip toward first direction bent
The first suppressing portion to flowing is opened up for suppressing air into having, wherein the first direction is the leading edge to the direction of trailing edge.
Propeller as described above, wherein, the blade has an axis, the leading edge and trailing edge have respectively parallel to
The tangent line of the axis, at least one in the blade tip and the first suppressing portion are located between two tangent lines.
Propeller as described above, wherein, the blade rotates to form oar disk, in first suppressing portion and the oar disk
The distance of the heart and the ratio of the propeller radius are 79.4%-88.8%.
Propeller as described above, wherein, the trailing edge is also bent to form close to the part of blade tip toward the first direction
Have and open up the second suppressing portion to flowing for suppressing air.
Propeller as described above, wherein, the blade has an axis, the leading edge and trailing edge have respectively parallel to
The tangent line of the axis, second suppressing portion is between two tangent lines.
Propeller as described above, wherein, the blade back and blade face are curved surface.
Propeller as described above, wherein, the leading edge has the curved portion that arches upward.
Propeller as described above, wherein, the propeller includes multiple blades, and the propeller also includes Jiang Grains, institute
Circumference of multiple blades along the Jiang Grains is stated to be uniformly arranged.
Propeller as described above, wherein, the propeller is self-tightening oar, in the propeller hub of the self-tightening oar formed with for
With the connecting hole of the output axis connection of motor.
Propeller as described above, wherein, to fold oar, the propeller hub for folding oar is included described in connection the propeller
The first connecting portion of blade, the second connecting portion for connecting actuator and the first connecting portion and second connecting portion it
Between spaced 3rd connecting portion.
Propeller as described above, wherein, the blade root is formed with the mounting hole for being fixed with the first connecting portion.
Propeller as described above, wherein, the thickness of the blade is gradually reduced from the blade root to the blade tip.
Propeller as described above, wherein, the blade rotates to form oar disk, is being apart with the oar disk center
At 79.4%, the chord length of the blade is 16.39mm ± 5mm, and the angle of attack is 12.94 ° ± 2.5 °；With the oar disk center apart
At 84.1%, the chord length of the blade is 15.05mm ± 5mm, and the angle of attack is 11.55 ° ± 2.5 °；With oar disk center phase
Away from at 88.8%, the chord length of the blade is 11.42mm ± 5mm, and the angle of attack is 10.69 ° ± 2.5 °.
Propeller as described above, wherein, the radius of the propeller is 107mm, is being apart with the oar disk center
At 85mm, the chord length of the blade is 16.39mm, and the angle of attack is 12.94 °；It is described at the oar disk center apart for 90mm
The chord length of blade is 15.05mm, and the angle of attack is 11.55 °；At with the oar disk center apart for 95mm, the chord length of the blade
For 11.42mm, the angle of attack is 10.69 °.
Propeller as described above, wherein, at the oar disk center apart for 42.1%, the chord length of the blade is
23.98mm ± 5mm, the angle of attack are 20.96 ° ± 2.5 °.
Propeller as described above, wherein, the radius of the propeller is 107mm, is being apart with the oar disk center
At 45mm, the chord length of the blade is 23.98mm, and the angle of attack is 20.96 °.
Propeller as described above, wherein, at oar disk center apart for 60.7%, the chord length of the blade is
20.03mm ± 5mm, the angle of attack are 16.61 ° ± 2.5 °.
Propeller as described above, wherein, the radius of the propeller is 107mm, is being apart 65mm with oar disk center
Place, the chord length of the blade is 20.03mm, and the angle of attack is 16.61 °.
Propeller as described above, wherein, at the oar disk center apart for 93.5%, the chord length of the blade is
8.29mm ± 5mm, the angle of attack are 10.04 ° ± 2.5 °.
Propeller as described above, wherein, the radius of the propeller is 107mm, is being apart with the oar disk center
At 100mm, the chord length of the blade is 8.29mm, and the angle of attack is 10.04 °.
Propeller as described above, wherein, at the oar disk center apart for 98.1%, the chord length of the blade is
6.18mm ± 5mm, the angle of attack are 9.35 ° ± 2.5 °.
Propeller as described above, wherein, the radius of the propeller is 107mm, is being apart with the oar disk center
At 105mm, the chord length of the blade is 6.18mm, and the angle of attack is 9.35 °.
Propeller as described above, wherein, the pitch of the propeller is 31mm.
Propeller as described above, wherein, the length of the blade is 98mm.
According to the embodiment of the utility model one, there is provided a kind of Power Component, it is characterised in that including：Motor and more than
Propeller described in any one, the output axis connection of the propeller hub of the propeller and the motor.
Power Component as described above, wherein, the KV values of the motor turn/(minute volt) for 1300-1500.
According to an embodiment of the present utility model, there is provided a kind of unmanned plane, including：Frame, horn and any of the above item
Described Power Component, one end of the horn are connected with the frame, and the other end of the horn is used to install the power
Component.
Unmanned plane as described above, wherein, the horn is rotatably connected with the frame.
According to the technical scheme of the utility model embodiment, by being formed in leading edge close to the part of blade tip toward trailing edge direction
First suppressing portion of bending, can cut off exhibition of the air on blade to flowing, so as to reduce the formation in blade tip whirlpool or weakening
The intensity in blade tip whirlpool, and then the rotational noise in propeller rotary course is reduced, improve the effect of unmanned plane security.
Brief description of the drawings
By referring to the described in detail below of accompanying drawing, the above and other purpose of the utility model embodiment, feature and excellent
Point will become more clearly understood from.In the accompanying drawings, will by example and it is nonrestrictive in a manner of to multiple implementations of the present utility model
Example illustrates, wherein：
Fig. 1 is the structural representation for the blade that the embodiment of the utility model one provides；
Fig. 2 is Fig. 1 front view；
Fig. 3 is Fig. 1 right view；
Fig. 4 is Fig. 1 left view；
Fig. 5 is Fig. 1 upward view；
Fig. 6 is Fig. 1 upward view；
Fig. 7 is the sectional position schematic diagram for the blade that the embodiment of the utility model one provides；
Fig. 8 be in Fig. 7 A-A to sectional view；
Fig. 9 is B-B direction sectional view in Fig. 7；
Figure 10 be in Fig. 7 C-C to sectional view；
Figure 11 be in Fig. 7 D-D to sectional view；
Figure 12 be in Fig. 7 E-E to sectional view；
Figure 13 be in Fig. 7 F-F to sectional view；
Figure 14 be in Fig. 7 G-G to sectional view；
Figure 15 is the structural representation for the propeller that the embodiment of the utility model one provides；
Figure 16 is the structural representation for the wheel hub that the embodiment of the utility model one provides；
Figure 17 is the structural representation for the aircraft that the embodiment of the utility model one provides.
In figure：
110th, blade root；120th, blade tip；
130th, blade face；140th, blade back；
150th, leading edge；160th, trailing edge；
170th, mounting hole；180th, the first suppressing portion；
190th, the second suppressing portion；200th, propeller hub；
210th, connecting hole；220th, first connecting portion；
230th, second connecting portion；240th, the 3rd connecting portion；
10th, frame；20th, horn；
30th, Power Component.
Embodiment
Below in conjunction with the accompanying drawings, some embodiments of the present utility model are elaborated.In the case where not conflicting, under
Feature in the embodiment and embodiment stated can be mutually combined.
Fig. 1 is the structural representation for the blade that the present embodiment provides；Fig. 2 is Fig. 1 front view；The right side that Fig. 3 is Fig. 1 regards
Figure；Fig. 4 is Fig. 1 left view；Fig. 5 is Fig. 1 upward view；Fig. 6 is Fig. 1 upward view.
As shown in figures 1 to 6, the propeller that the present embodiment provides, is included in Power Component, such as motor or engine
Lower rotation is driven to produce the blade of lift or motive force.Blade includes being used for the blade root 110 and the back of the body being fixed on wheel hub
From the blade tip 120 of the blade root 110.When propeller works, blade is rotated so as to form oar disk around a pivot, with disturbance
Air-flow produces lift, and either thrust drives manned or not manned vehicle motion, such as dirigible or rotary wind type unmanned plane.
The blade of the present embodiment can be manufactured using arbitrary material in the prior art, including but not limited to steel, aluminium alloy, modeling
Material, carbon fiber etc..During fabrication, the processing technology for including the various prior arts such as molding, punching press, forging can also be used.
Blade also has leading edge 150, the Yi Jilian on blade face 130 and blade back 140, connection blade face 130 and the side of blade back 140 1
Connect the trailing edge 160 of 140 another side of blade face 130 and blade back.Wherein, blade back 140 be aircraft in flight course, blade is upward
One side；Blade face 130 be aircraft in flight course, the blade one side (in other words towards ground) down.
The first suppressing portion 180 is bent to form toward first direction close to the part of blade tip 120 in leading edge 150, first suppression
Portion 180 processed is used to suppress exhibition of the air on blade to flowing, wherein, first direction is from leading edge 150 to the side of trailing edge 160
To.Specifically, in fig. 2, leading edge 150, which is turned left, has been bent to form the first suppressing portion 180, and first suppressing portion 180 can be cut off
Exhibition of the air on blade is to flowing when blade rotates, so as to reduce the vortex of the part of blade tip 120 formation and reduce blade tip
The intensity of 120 partial vortices, so as to weaken the degree of air pressure change near blade, also reduce with certain thickness blade
The degree of periodicity cutting steam, and then reduce rotational noise caused by the blade rotation of propeller.
In the present embodiment, the particular location of the first suppressing portion 180 can be according to aircraft overall noise and pneumatic effect
The specific requirement of rate is designed., can be from the first suppressing portion 180 and oar specifically when designing the position of the first suppressing portion 180
The position of point 120 and the first suppressing portion 180 are paid attention to apart from oar disk center apart from the two aspects：
For example, as shown in Fig. 2 in a kind of optional scheme, there is blade an axis (to be used in figure among blade
Dotted line represent), and the leading edge 150 of blade and trailing edge 160 respectively have one parallel to the axis tangent line (in figure with difference
Represented on the left of blade with the solid line on right side), the first suppressing portion 180 and blade tip 120 can be arranged between this two tangent lines.
Certainly, those skilled in the art would certainly understand from, and the position of above-mentioned first suppressing portion 180 and blade tip 120 is not to the present embodiment spiral shell
The specific restriction of oar is revolved, the first suppressing portion 180 or blade tip 120 only can also be arranged on this two in actual design process
Between tangent line.By by the first suppressing portion 180, blade tip 120 or both be arranged on above-mentioned two tangent lines between, Ke Yi
The pneumatic efficiency of propeller is not influenceed while reducing the rotational noise of propeller excessively again, so as to have good fly in propeller
Balance is obtained between row performance and smaller noise.
In another example in another optional scheme, the first suppressing portion 180 rotates formed oar disk center with blade
The ratio of distance and the propeller radius is 79.4%-88.8%, so that the first suppressing portion 180 can reduce propeller noise
While again excessively influence propeller pneumatic efficiency.
Certainly, it should it is understood that above-mentioned two scheme can also be combined, so that propeller is reducing rotational noise
While can also keep the pneumatic efficiency basically identical with ordinary rectangular propeller, wherein rectangular coil oar refers to blade tip 120
Part is the propeller of rectangle.
With continued reference to Fig. 1 and Fig. 2, alternatively, trailing edge 160 is also bent to form close to the part of blade tip 120 toward first direction
Have and open up the second suppressing portion 190 to flow for suppressing air.It is specifically past close to the part of blade tip 120 for trailing edge 160 in fig. 2
A left side has been bent to form the second suppressing portion 190.Similarly, can also be as the first suppression when designing the position of the second suppressing portion 190
Portion 180 equally consider the second suppressing portion 190 and blade tip 120 bending degree and the second suppressing portion 190 relative to oar disk center
Distance.For example, in a kind of optional embodiment, the second suppressing portion 190 can also be located at above-mentioned two parallel to axis
Between the tangent line of line, so as to reduce propeller noise and keep propeller that there is the pneumatic effect roughly the same with rectangular coil oar
Balance is obtained in terms of rate.
In the present embodiment, as shown in Figure 3 and Figure 4, blade back 140 and blade face 130 may be alternatively arranged as curved surface, and bend
Trend is：When blade is generally in horizontality, the location of leading edge 150 is lower than the location of trailing edge 160.Passing through will
The blade back 140 of blade and blade face 130 are arranged to curved surface, that is, the surface of blade is arranged to seamlessly transit so that blade does not have
Part is drastically reversed, can make blade that there is less stress, and intensity is higher is not easily broken, and has higher reliability.
With continued reference to Fig. 3 and Fig. 4, the thickness of blade, which is optionally from blade root 110 to blade tip 120, to be gradually reduced, so that
The one end of blade away from oar disk center is the most thin part of blade, to reduce air drag, improves the flying quality of propeller.
In the present embodiment, as depicted in figs. 1 and 2, leading edge 150 is optionally provided with the curved portion that arches upward, and this arches upward
The remainder of portion and leading edge 150 is to be connected smoothly.Specifically, Fig. 2 shows that the portion of arching upward of blade is positioned close to oar
The position of the root 110 and portion that arches upward is towards right side.
The propeller of the present embodiment close to the part of blade tip 120 in leading edge 150 by forming what is bent toward the direction of trailing edge 160
First suppressing portion 180, exhibition of the air on blade can be cut off to flowing, so as to reduce the formation in blade tip whirlpool or weaken blade tip
The intensity in whirlpool, and then the rotational noise in propeller rotary course is reduced, raising includes manned or not manned vehicle
The effect of (such as unmanned plane or dirigible) security.
Fig. 7 is the sectional position schematic diagram for the blade that the present embodiment provides；Fig. 8 be in Fig. 7 A-A to sectional view；Fig. 9 is figure
B-B direction sectional view in 7；Figure 10 be in Fig. 7 C-C to sectional view；Figure 11 be in Fig. 7 D-D to sectional view；Figure 12 be Fig. 7 in E-E to
Sectional view；Figure 13 be in Fig. 7 F-F to sectional view；Figure 14 be in Fig. 7 G-G to sectional view.
As shown in Fig. 7 to Figure 13, the present embodiment provides a kind of size-modify example for being suitable for rotary wind type unmanned plane, but this
Art personnel can be manned or non-manned directly or through other are applied to after simple change according to following description
On aircraft.
Specifically, the size at seven sections in the blade of rotary wind type unmanned plane is improved in the present embodiment,
Wherein, being improved possessed by the size at C-C sections, D-D sections and the E-E sections has optimal effect：
At with oar disk center apart for 79.4%, i.e.,：It is as shown in Figure 7 at the C-C sections that oar disk center is H3,
The chord length L3 of blade as shown in Figure 10 is 16.39mm ± 5mm, and angle of attack 3 is 12.94 ° ± 2.5 °.Wherein, chord length refers to
At the section, leading edge 150 is located at the end points of the leftmost side on the section and is located at the end points of the rightmost side on the section in water with trailing edge 160
Square to distance, the angle of attack is that leading edge 150 be located at the end points of the leftmost side and trailing edge 160 on the section and is located at the rightmost side on the section
End points between line and horizontal direction angle, or, the angle of attack is it can be appreciated that be the string wing and the gas incoming of blade
The angle in direction.
At with oar disk center apart for 84.1%, i.e.,：It is as shown in Figure 7 at the D-D sections that oar disk center is H4,
The chord length L4 of blade as shown in figure 11 is 15.05mm ± 5mm, and angle of attack 4 is 11.55 ° ± 2.5 °.
At with oar disk center apart for 88.8%, i.e.,：It is as shown in Figure 7 at the E-E sections that oar disk center is H5,
The chord length L5 of blade as shown in figure 12 is 11.42mm ± 5mm, and angle of attack 5 is 10.69 ° ± 2.5 °.
The present embodiment can be reduced propeller and rotated by the setting to above three section chord length and the angle of attack in blade
During caused rotational noise, improve the security of aircraft, and do not influence the pneumatic efficiency of aircraft.
On the basis of above-mentioned technical proposal, to Section A-A, section B-B, F-F sections and the chord length in G-G sections in blade
It is improved respectively with the angle of attack, can further reduces propeller and wait caused rotational noise when rotated, so as to improves flight
The security performance of device.
At with oar disk center apart for 42.1%, i.e.,：It is as shown in Figure 7 at the Section A-A that oar disk center is H1,
The chord length L1 of blade as shown in Figure 8 is 23.98mm ± 5mm, and angle of attack 1 is 20.96 ° ± 2.5 °.
At with oar disk center apart for 60.7%, i.e.,：It is as shown in Figure 7 at the section B-B that oar disk center is H2,
The chord length L2 of blade as shown in Figure 9 is 20.03mm ± 5mm, and angle of attack 2 is 16.61 ° ± 2.5 °.
At with oar disk center apart for 93.5%, i.e.,：It is as shown in Figure 7 at the F-F sections that oar disk center is H6,
The chord length L6 of blade is 8.29mm ± 5mm as shown in fig. 13 that, and angle of attack 6 is 10.04 ° ± 2.5 °.
At with oar disk center apart for 98.1%, i.e.,：It is as shown in Figure 7 at the G-G sections that oar disk center is H7,
The chord length L7 of blade as shown in figure 14 is 6.18mm ± 5mm, and angle of attack 7 is 9.35 ° ± 2.5 °.
It will be appreciated by persons skilled in the art that above-mentioned section A-A, section B-B, section F-F and section G-G position
Such scheme is not limited to, can slightly be changed.
For above-mentioned technical proposal, a kind of specific propeller of the present embodiment offer, a diameter of 107mm of the propeller,
The length of wherein blade is optionally 95mm.At with oar disk center apart for 85mm, the chord length of blade is specially 16.39mm,
The angle of attack is 12.94 °.At with oar disk center apart for 90mm, the chord length of blade is 15.05mm, and the angle of attack is 11.55 °.With oar
Disk center is at a distance of at 95mm, the chord length of blade is 11.42mm, and the angle of attack is 10.69 °.
Further, at oar disk center apart for 45mm, the chord length of blade is 23.98mm, and the angle of attack is 20.96 °.
With oar disk center at a distance of at 65mm, the chord length of blade is 20.03mm, and the angle of attack is 16.61 °.It is being apart with oar disk center
At 100mm, the chord length of blade is 8.29mm, and the angle of attack is 10.04 °.At with oar disk center apart for 105mm, the chord length of blade
For 6.18mm, the angle of attack is 9.35 °.It is appreciated that because section A-A, section B-B, section F-F and section G-G position can be slightly
Change, therefore correspondingly, the angle of attack chord long value at section A-A, section B-B, section F-F and section G-G also can accordingly change.
In the present embodiment, the pitch of propeller can be 31mm, i.e.,：Blade rotates a circle, and the distance that theory rises is
31mm。
The above-mentioned propeller that the present embodiment is provided, by being contrasted with propeller of the prior art, propeller
Overall noise can be reduced to 69dB from 72dB, and the hovering power consumption of propeller can only reduce 4-5%, that is, the present embodiment
Above-mentioned propeller also has good pneumatic efficiency while noise is reduced.
Further, the propeller that the present embodiment provides is applicable to twin shaft aircraft, four-axle aircraft or the flight of eight axles
Device etc..Figure 15 is the structural representation for the propeller that the embodiment of the utility model one provides.As shown in figure 15, propeller is alternatively
Including propeller hub 200, the blade of two, three or more than three can be connected on propeller hub 200.The Jiang Grains drive blade to turn
It is dynamic to form oar disk.Certainly, propeller hub 200 and blade can be structure as a whole or blade are arranged separately on propeller hub 200
The split type propeller formed, for example, mounting hole 170 can be formed on the blade root 110 of blade, so as to pass through mounting hole 170
Blade is installed on propeller hub 200.
Specifically, propeller can be self-tightening oar as shown in figure 15, in the propeller hub 200 of the self-tightening oar formed with for
The connecting hole 210 of the output axis connection of motor.In the present embodiment, self-tightening oar refer on the propeller hub 200 of the propeller formed with
The supporting self-locking mechanism with fuselage, when the connecting hole 210 of propeller hub 200 is enclosed on the output shaft of motor and starts aircraft,
The self-locking mechanism to be cooperated on fuselage and on propeller hub 200 can be by propeller lock on fuselage, so as to avoid flying oar or fried
Machine.For example, can open up groove on propeller hub 200, the ratchet controlled by cam mechanism is set on fuselage, so as to
When aircraft starts, axial movement of the cam mechanism rotational band pawl along propeller hub 200 is to lock propeller hub 200.Or also may be used
With by axial movement of the disk-like structure of magnet control along propeller hub 200, so as to which wheel hub is pressed on into disk-like structure and fuselage
Between so as to realizing the locking of more propeller hubs 200.
Propeller can also be fold oar, so as to by by multiple blades and horn fold into it is parallel with fuselage or
Abut on fuselage to reduce the volume of whole aircraft with convenience in transport and storage.Figure 16 is the folding oar that the present embodiment provides
The structural representation of middle wheel hub.As shown in figure 16, the propeller hub 200 of the folding oar can include the connection of first connecting portion 220, second
The connecting portion 240 of portion 230 and the 3rd.Wherein, first connecting portion 220 is connected with blade, for example, passing through the oar of blade using fastener
The mounting hole 170 opened up on root 110 is so that the blade is fixed in first connecting portion 220.Second connecting portion 230 connects with actuator
Connect, such as second connecting portion 230 is set on the output shaft of motor or engine, will pass through motor or engine driving
Wheel hub drives blade rotation, and to form oar disk, so as to produce lift, either thrust drives manned or non-manned vehicle motion.
3rd connecting portion 240, which is arranged between first connecting portion 220 and second connecting portion 230, to be used to connect the He of first connecting portion 220
Second connecting portion 230.
Alternatively, the 3rd connecting portion 240 can be two, three or more than three, be disposed on first connecting portion
Between 220 and second connecting portion 230.Above-mentioned multiple 3rd connecting portions 240 can be evenly arranged in first connecting portion 220 and second
Between connecting portion 230.For example, three evenly spaced can be set between first connecting portion 220 and second connecting portion 230
Three connecting portions 240.
The folding oar of the present embodiment, first connecting portion 220 and second connecting portion 230 are connected by the 3rd connecting portion 240
Together, the weight of propeller can be mitigated, improve the flying quality of propeller.Especially when propeller hub 200 and blade are integrated
During the propeller of structure, its flying quality can be greatly improved.And it is disposed on the connection of first connecting portion 220 and second
The 3rd connecting portion 240 between portion 230 can not only improve the structural strength of propeller, and can further improve propeller
Stability in flight course, so as to improve the flying quality of propeller.In addition, in specifically manufacture propeller hub 200, can incite somebody to action
Seamlessly transitted at 3rd connecting portion 240 and the link position of first connecting portion 220 and second connecting portion 230, so as to the company of reduction
The stress of position is connect, improves the reliability of propeller hub 200.
It should be appreciated by those skilled in the art that above-mentioned propeller can be positive oar or anti-oar.Wherein, positive oar refers to from vertical view
From the point of view of aircraft, dextrorotation transfers to produce the propeller of lift；Anti- oar refer to from overlook aircraft from the point of view of, the inverse time
Pin rotates and produces the propeller of lift.The structure of positive oar is symmetrical for minute surface with the structure of anti-oar.
The present embodiment also provides a kind of Power Component, including actuator and such as the propeller that above-mentioned content is provided, the spiral shell
Revolve output axis connection of the oar by wheel hub and actuator.Wherein, actuator is specifically as follows motor, and the KV values of motor are 1300
Turn/(minute volt), 1500 turns/(minute volt) or both between arbitrary value, such as, 1400 turns/(minute
Volt).
The Power Component of the present embodiment, formed by the leading edge 150 in blade close to the part of blade tip 120 toward trailing edge 160
First suppressing portion 180 of direction bending, can cut off exhibition of the air on blade to flowing, so as to reduce the formation in blade tip whirlpool or
Person weakens the intensity in blade tip whirlpool, and then reduces the rotational noise in propeller rotary course, and raising includes manned or not
The effect of manned vehicle (such as unmanned plane or dirigible) security.
Figure 17 is the structural representation for the aircraft that the present embodiment provides.As shown in figure 17, the present embodiment also provides one kind
Aircraft, including frame 10, horn 20 and at least one above-mentioned Power Component 30, one end of horn 20 are connected with frame 10,
The other end of horn 20 is used to install Power Component 30.Aircraft as described above can be manned vehicle, such as dirigible,
Can be rotary wind type unmanned vehicle, such as four rotor wing unmanned aerial vehicles.The aircraft uses above-mentioned Power Component 30, by blade
Leading edge 150 close to the part of blade tip 120 formed toward the direction of trailing edge 160 bending the first suppressing portion 180, air can be cut off and existed
Exhibition on blade so as to reduce the formation in blade tip whirlpool or weaken the intensity in blade tip whirlpool, and then reduces propeller to flowing
Rotational noise in rotary course, improving includes manned either not manned vehicle (such as unmanned plane or dirigible) security
Effect.
Alternatively, horn 20 can be fixed in frame 10 or is rotatably connected with frame 10.When horn 20 is rotatable
When ground is connected in frame 10, the volume of aircraft occupancy can be reduced, facilitate its storage and transport.
Finally, although being described in the context of these embodiments associated with certain embodiments of the present technology
Advantage, but other embodiment can also include the advantages of such, and simultaneously this practicality is all described in detail in not all embodiments
New all advantages, the utility model is regarded as objective the advantages of bringing by the technical characteristic institute in embodiment and is different from now
There is the advantages of technology, belong to the scope of protection of the utility model.
Claims (28)
1. a kind of propeller for unmanned plane, it is characterised in that including blade；
The blade includes blade root and the blade tip away from the blade root；
The blade has the leading edge and connection blade face and blade back opposite side of blade face, blade back, connection blade face and the side of blade back one
The trailing edge on side；And
The leading edge close to the part of blade tip toward first direction be bent to form for suppress air open up to flowing first suppress
Portion, wherein the first direction is the leading edge to the direction of trailing edge.
2. propeller according to claim 1, it is characterised in that the blade has axis, the leading edge and trailing edge
There is the tangent line parallel to the axis respectively, at least one in the blade tip and the first suppressing portion, which is located at described in two, to be cut
Between line.
3. propeller according to claim 1, it is characterised in that the blade rotates to form oar disk, and described first suppresses
Portion is 79.4%-88.8% with the distance of the oar disk center and the ratio of the propeller radius.
4. propeller according to claim 1, it is characterised in that the trailing edge is close to the part of blade tip also toward described first
Direction is bent to form opens up the second suppressing portion to flowing for suppressing air.
5. propeller according to claim 4, it is characterised in that the blade has axis, the leading edge and trailing edge
There is the tangent line parallel to the axis respectively, second suppressing portion is between two tangent lines.
6. propeller according to claim 1, it is characterised in that the blade back and blade face are curved surface.
7. propeller according to claim 1, it is characterised in that the leading edge has the curved portion that arches upward.
8. propeller according to claim 1, it is characterised in that the propeller includes multiple blades, the propeller
Also include Jiang Grains, circumference of the multiple blade along the Jiang Grains is uniformly arranged.
9. propeller according to claim 8, it is characterised in that the propeller is self-tightening oar, the oar of the self-tightening oar
Formed with the connecting hole for the output axis connection with motor in hub.
10. propeller according to claim 8, it is characterised in that the propeller is folding oar, the oar of the folding oar
Hub includes connecting the first connecting portion of the blade, the second connecting portion for connecting actuator and in the first connecting portion
Spaced 3rd connecting portion between second connecting portion.
11. propeller according to claim 10, it is characterised in that the blade root with described first formed with for being connected
The mounting hole that portion is fixed.
12. propeller according to claim 1, it is characterised in that the thickness of the blade is from the blade root to the oar
Point is gradually reduced.
13. according to the propeller described in claim any one of 1-12, it is characterised in that the blade rotates to form oar disk,
At with the oar disk center apart for 79.4%, the chord length of the blade is 16.39mm ± 5mm, and the angle of attack is 12.94 °
±2.5°；
At with the oar disk center apart for 84.1%, the chord length of the blade is 15.05mm ± 5mm, and the angle of attack is 11.55 °
±2.5°；
At with the oar disk center apart for 88.8%, the chord length of the blade is 11.42mm ± 5mm, and the angle of attack is 10.69 °
±2.5°。
14. propeller according to claim 13, it is characterised in that the radius of the propeller is 107mm,
At with the oar disk center apart for 85mm, the chord length of the blade is 16.39mm, and the angle of attack is 12.94 °；
At with the oar disk center apart for 90mm, the chord length of the blade is 15.05mm, and the angle of attack is 11.55 °；
At with the oar disk center apart for 95mm, the chord length of the blade is 11.42mm, and the angle of attack is 10.69 °.
15. propeller according to claim 13, it is characterised in that at the oar disk center apart for 42.1%,
The chord length of the blade is 23.98mm ± 5mm, and the angle of attack is 20.96 ° ± 2.5 °.
16. propeller according to claim 15, it is characterised in that the radius of the propeller is 107mm, with it is described
Oar disk center is at a distance of at 45mm, the chord length of the blade is 23.98mm, and the angle of attack is 20.96 °.
17. propeller according to claim 13, it is characterised in that described at oar disk center apart for 60.7%
The chord length of blade is 20.03mm ± 5mm, and the angle of attack is 16.61 ° ± 2.5 °.
18. propeller according to claim 17, it is characterised in that the radius of the propeller is 107mm, with oar disk
Center is at a distance of at 65mm, the chord length of the blade is 20.03mm, and the angle of attack is 16.61 °.
19. propeller according to claim 13, it is characterised in that at the oar disk center apart for 93.5%,
The chord length of the blade is 8.29mm ± 5mm, and the angle of attack is 10.04 ° ± 2.5 °.
20. propeller according to claim 19, it is characterised in that the radius of the propeller is 107mm, with it is described
Oar disk center is at a distance of at 100mm, the chord length of the blade is 8.29mm, and the angle of attack is 10.04 °.
21. propeller according to claim 13, it is characterised in that at the oar disk center apart for 98.1%,
The chord length of the blade is 6.18mm ± 5mm, and the angle of attack is 9.35 ° ± 2.5 °.
22. propeller according to claim 21, it is characterised in that the radius of the propeller is 107mm, with it is described
Oar disk center is at a distance of at 105mm, the chord length of the blade is 6.18mm, and the angle of attack is 9.35 °.
23. propeller according to claim 13, it is characterised in that the pitch of the propeller is 31mm.
24. according to the propeller described in claim 14,16,18,20 or 22, it is characterised in that the length of the blade is
98mm。
A kind of 25. Power Component, it is characterised in that including：Propeller described in motor and claim any one of 1-24,
The output axis connection of the propeller hub of the propeller and the motor.
26. Power Component according to claim 25, it is characterised in that the KV values of the motor be 1300-1500 turn/
(minute volt).
A kind of 27. unmanned plane, it is characterised in that including：Power Component described in frame, horn and claim 25 or 26,
One end of the horn is connected with the frame, and the other end of the horn is used to install the Power Component.
28. unmanned plane according to claim 27, it is characterised in that the horn is rotatably connected with the frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720930041.XU CN207045700U (en) | 2017-07-28 | 2017-07-28 | Propeller, Power Component and unmanned plane for unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720930041.XU CN207045700U (en) | 2017-07-28 | 2017-07-28 | Propeller, Power Component and unmanned plane for unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207045700U true CN207045700U (en) | 2018-02-27 |
Family
ID=61496727
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720930041.XU Expired - Fee Related CN207045700U (en) | 2017-07-28 | 2017-07-28 | Propeller, Power Component and unmanned plane for unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207045700U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108688794A (en) * | 2018-04-18 | 2018-10-23 | 中山市朗宇模型有限公司 | propeller |
| CN108750075A (en) * | 2018-08-10 | 2018-11-06 | 深圳市道通智能航空技术有限公司 | A kind of propeller component, Power Component and unmanned vehicle |
| CN108750074A (en) * | 2018-03-30 | 2018-11-06 | 中山市朗宇模型有限公司 | propeller |
| CN108820187A (en) * | 2018-03-30 | 2018-11-16 | 中山市朗宇模型有限公司 | Propeller, Power Component and aircraft |
| CN108945396A (en) * | 2018-03-30 | 2018-12-07 | 中山市朗宇模型有限公司 | propeller |
| 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 |
| WO2019223193A1 (en) * | 2018-05-25 | 2019-11-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and air vehicle |
| WO2019223205A1 (en) * | 2018-05-25 | 2019-11-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
| CN110896625A (en) * | 2018-04-25 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN111655575A (en) * | 2018-06-26 | 2020-09-11 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
-
2017
- 2017-07-28 CN CN201720930041.XU patent/CN207045700U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11364999B2 (en) | 2017-07-28 | 2022-06-21 | SZ DJI Technology Co., Ltd. | Rotor, power assembly and air vehicle |
| 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 |
| CN108750074A (en) * | 2018-03-30 | 2018-11-06 | 中山市朗宇模型有限公司 | propeller |
| CN108820187A (en) * | 2018-03-30 | 2018-11-16 | 中山市朗宇模型有限公司 | Propeller, Power Component and aircraft |
| CN108945396A (en) * | 2018-03-30 | 2018-12-07 | 中山市朗宇模型有限公司 | propeller |
| CN108688794A (en) * | 2018-04-18 | 2018-10-23 | 中山市朗宇模型有限公司 | propeller |
| CN110896625A (en) * | 2018-04-25 | 2020-03-20 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| WO2019223193A1 (en) * | 2018-05-25 | 2019-11-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and air vehicle |
| WO2019223205A1 (en) * | 2018-05-25 | 2019-11-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, 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 |
| CN110896626A (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 |
| CN111655575A (en) * | 2018-06-26 | 2020-09-11 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN108750075A (en) * | 2018-08-10 | 2018-11-06 | 深圳市道通智能航空技术有限公司 | A kind of propeller component, Power Component and unmanned vehicle |
| CN108750075B (en) * | 2018-08-10 | 2024-04-12 | 深圳市道通智能航空技术股份有限公司 | Propeller assembly, power assembly and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207045700U (en) | Propeller, Power Component and unmanned plane for unmanned plane | |
| EP2799334B1 (en) | Blade rotary assembly with aerodynamic outer toroid spoiler for a shrouded propulsion rotary assembly | |
| CA2762247C (en) | Co-rotating stacked rotor disks for improved hover performance | |
| US7281900B2 (en) | Cascade rotor blade for low noise | |
| CN206202665U (en) | Propeller, Power Component and aircraft | |
| CN205345321U (en) | Screw, power suit and unmanned vehicles | |
| CN107031850A (en) | Can variable-geometry ducted fan and correlation technique | |
| CN202642093U (en) | Propeller and aircraft with propeller | |
| CN104968893A (en) | Unducted thrust producing system architecture | |
| CN206297727U (en) | Propeller, Power Component and aircraft | |
| JPH0362598B2 (en) | ||
| CN102897314B (en) | For the flow field velocity of angle of rake reduction | |
| CN206155775U (en) | Screw, power component and aircraft | |
| CN206141830U (en) | Screw, power suit and unmanned vehicles | |
| CN206394871U (en) | Propeller, Power Component and aircraft | |
| CN205891216U (en) | Screw, power suit and unmanned vehicles | |
| CN206926806U (en) | Propeller, Power Component and aircraft | |
| CN109153449A (en) | Propeller, Power Component and unmanned vehicle | |
| CN207072430U (en) | Propeller, Power Component and aircraft | |
| CN208993923U (en) | Propeller, Power Component and unmanned vehicle | |
| JP2011527253A (en) | Aircraft having at least two propeller drives spaced apart from each other in the span span direction of the wing | |
| CN207000809U (en) | Blade, propeller, power suit and unmanned vehicle | |
| CN206394870U (en) | Propeller, Power Component and aircraft | |
| CN207631487U (en) | Propeller, Power Component and unmanned vehicle | |
| CN206954494U (en) | Propeller, Power Component and aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180227 |