CN207773438U - Propeller, Power Component and aircraft - Google Patents
Propeller, Power Component and aircraft Download PDFInfo
- Publication number
- CN207773438U CN207773438U CN201721852806.9U CN201721852806U CN207773438U CN 207773438 U CN207773438 U CN 207773438U CN 201721852806 U CN201721852806 U CN 201721852806U CN 207773438 U CN207773438 U CN 207773438U
- Authority
- CN
- China
- Prior art keywords
- propeller
- blade
- leading edge
- center
- aircraft
- 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
- 238000005452 bending Methods 0.000 claims description 14
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000000007 visual effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of propeller, Power Component and aircraft.Propeller includes blade.Blade includes blade root, the blade tip away from blade root, pressure face, the suction surface opposite with pressure face, the leading edge for being connected to pressure face and suction surface a side, the rear for being connected to pressure face and another side of suction surface and the sweepback portion for being formed in blade tip.Leading edge from blade root extend to towards where pressure face side tilt extend and close to blade tip part towards suction surface where side reversion tilt and be intersected in blade tip with rear, sweepback portion tilts extension from leading edge to rear.Air drag can reduced using the propeller, Power Component and aircraft of the blade, improve pulling force and efficiency, increase aircraft after boat distance and while improve the flying quality of aircraft, also reduce the noise that blade generates at work, so that aircraft is quieter in hovering, user experience is improved.
Description
Technical field
The utility model is related to aircraft fields, more particularly to propeller, Power Component and aircraft.
Background technology
Carry-on propeller is used for as the important Primary Component of aircraft by shaft in motor or engine
Rotation be converted into thrust or lift.
For propeller in the prior art in rotation, the turbulent flow and downwash flow of blade each section impact aircraft skin
Structure will produce larger noise.It is often superimposed with noise of motor and structure quake noise, and amplifies certain frequencies
Section noise, causes aircraft global noise larger, usage experience is poor.
Utility model content
The embodiment of the utility model provides a kind of propeller, Power Component and aircraft.
The propeller of the utility model embodiment includes blade.
The blade include blade root, the blade tip away from the blade root, pressure face, the suction surface opposite with the pressure face,
It is connected to the leading edge of the pressure face and described suction surface a side, is connected to the pressure face and another side of the suction surface
Rear and be formed in the sweepback portion of the blade tip；
The leading edge, which is extended from the blade root to towards the side inclination where the pressure face, to be extended and close to the paddle
Side reversion where the part towards the suction surface of point tilts and is intersected in the blade tip with the rear, and the sweepback portion is certainly
The leading edge is tilted to the rear to be extended.
In some embodiments, the blade is formed in the position of the blade tip at back bending, and the leading edge is returned from described
Crook is extended tilts extension to the side where the suction surface.
In some embodiments, the leading edge evagination is formed with the leading edge of shape in curved surface close to the blade root and arches upward
Portion；Or/and
The rear that the rear evagination is formed with the shape in curved surface close to the blade root arches upward portion.
In some embodiments, the propeller further includes propeller hub, and the blade is at least two, described at least two
The center that blade is connected on the propeller hub and about the propeller hub is centrosymmetric.
In some embodiments, it is the radius of the propeller apart from the center of the propeller hub at the back bending
90.9%.
In some embodiments, the blade has across the central axes at the center of the propeller hub, and the leading edge has
It is parallel to the leading edge tangent line of the central axes, the rear has the rear tangent line for being parallel to the central axes, the sweepback portion
Between the leading edge tangent line and the rear tangent line.
In some embodiments, the suction surface and the pressure face are curved surface.
In some embodiments, apart from the center of the propeller hub be the propeller radius 45.5% at, institute
The angle of attack for stating blade is 19.78 ° ± 2.5 °, and the chord length of the blade is 26.58mm ± 5mm.
In some embodiments, a diameter of 220mm ± 22mm of the propeller；
At the center 50mm apart from the propeller hub, the angle of attack of the blade is 19.78 °, and the chord length of the blade is
26.58mm。
In some embodiments, apart from the center of the propeller hub be the propeller radius 54.6% at, institute
The angle of attack for stating blade is 17.83 ° ± 2.5 °, and the chord length of the blade is 24.75mm ± 5mm.
In some embodiments, a diameter of 220mm ± 22mm of the propeller；
At the center 60mm apart from the propeller hub, the angle of attack of the blade is 17.83 °, and the chord length of the blade is
24.75mm。
In some embodiments, apart from the center of the propeller hub be the propeller radius 63.6% at, institute
The angle of attack for stating blade is 16.42 ° ± 2.5 °, and the chord length of the blade is 22.65mm ± 5mm.
In some embodiments, a diameter of 220mm ± 22mm of the propeller；
At the center 70mm apart from the propeller hub, the angle of attack of the blade is 16.42 °, and the chord length of the blade is
22.65mm。
In some embodiments, apart from the center of the propeller hub be the propeller radius 72.7% at, institute
The angle of attack for stating blade is 14.97 ° ± 2.5 °, and the chord length of the blade is 20.07mm ± 5mm.
In some embodiments, a diameter of 220mm ± 22mm of the propeller；
At the center 80mm apart from the propeller hub, the angle of attack of the blade is 14.97 °, and the chord length of the blade is
20.07mm。
In some embodiments, the screw pitch of the blade is 4.8 ± 0.5 inches.
The Power Component of the utility model embodiment includes the spiral shell described in actuator and above-mentioned any one embodiment
Paddle is revolved, the propeller is connect by the propeller hub with the actuator.
In some embodiments, the actuator is motor, and the KV values of the motor are 300 to 800 turns/(minute
Volt).
The aircraft of the utility model embodiment includes the power packages described in fuselage and above-mentioned any one embodiment
Part, the Power Component are connect with the fuselage.
In some embodiments, the aircraft includes multiple Power Components, the rotation side of the multiple Power Component
To difference.
In some embodiments, the aircraft is multi-rotor aerocraft.
The leading edge of propeller blade provided by the utility model, which is extended from blade root to towards the side inclination where pressure face, prolongs
It stretches and is tilted in the side reversion where the part towards suction surface close to blade tip and be intersected in blade tip with rear, sweepback portion is from leading edge
It tilts and extends to rear, air drag can reduced using the propeller, Power Component and aircraft of the blade, improving pulling force
And efficiency, increase aircraft after boat distance and while improve the flying quality of aircraft, also reduce blade in work
As when the noise that generates so that aircraft is quieter in hovering, improves user experience.
The additional aspect and advantage of the embodiment of the utility model will be set forth in part in the description, partly will be from
Become apparent in following description, or is recognized by the practice of the embodiment of the utility model.
Description of the drawings
In description of the above-mentioned and/or additional aspect and advantage of the utility model from combination following accompanying drawings to embodiment
It will be apparent and be readily appreciated that, wherein：Illustrating in newly-increased attached drawing modification, specification
Fig. 1 is the stereogram for the propeller that the utility model embodiment provides.
Fig. 2 is the stereogram at another visual angle of propeller in Fig. 1.
Fig. 3 is the floor map of propeller in Fig. 1.
Fig. 4 is the floor map of propeller in Fig. 1.
Fig. 5 is the floor map of propeller in Fig. 1.
Fig. 6 is that the sweepback portion of propeller in Fig. 1 tilts the Parameter Map extended from leading edge to rear.
Fig. 7 is that the leading edge of propeller in Fig. 1 is extended from back bending to the parameter for tilting extension to the side where suction surface
Figure.
Fig. 8 is the sectional view of the A-A sections at center 30mm of the propeller apart from propeller hub in Fig. 5.
Fig. 9 is the sectional view of the B-B sections at the center 40mm in Fig. 5 in propeller apart from propeller hub.
Figure 10 is the sectional view of the C-C sections at the center 50mm in Fig. 5 in propeller apart from propeller hub.
Figure 11 is the sectional view of the D-D sections at the center 60mm in Fig. 5 in propeller apart from propeller hub.
Figure 12 is the sectional view of the E-E sections at the center 70mm in Fig. 5 in propeller apart from propeller hub.
Figure 13 is the sectional view of the F-F sections at the center 80mm in Fig. 5 in propeller apart from propeller hub.
Figure 14 is the sectional view of the G-G sections at the center 90mm in Fig. 5 in propeller apart from propeller hub.
Figure 15 is the sectional view of the H-H sections at the center 100mm in Fig. 5 in propeller apart from propeller hub.
Figure 16 is the sectional view of the I-I sections at the center 110mm in Fig. 5 in propeller apart from propeller hub.
Figure 17 is the propeller and existing propeller of the utility model in identical hovering operating mode acoustical behavior test-strips
Frequency response curve schematic diagram under part.
Specific implementation mode
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment
Described in embodiment do not represent all embodiments consistent with the utility model.On the contrary, they be only with such as
The example of the consistent device and method of some aspects be described in detail in the appended claims, the utility model.
It is the purpose only merely for description specific embodiment in the term that the utility model uses, is not intended to be limiting this reality
With novel.In the "an" of the utility model and singulative used in the attached claims, " described " and "the"
It is intended to include most forms, unless context clearly shows that other meanings.It is also understood that term used herein " and/
Or " refer to and include one or more associated list items purposes any or all may combine.
It will be appreciated that though various information may be described using term first, second, third, etc. in the utility model,
But these information should not necessarily be limited by these terms.These terms are only used for same type of information being distinguished from each other out.For example, not
In the case of being detached from the scope of the utility model, the first information can also be referred to as the second information, and similarly, the second information can also
It is referred to as the first information.Depending on context, word as used in this " if " can be construed to " ... when " or
" when ... " or " in response to determination ".
The utility model embodiment provides a kind of propeller, can be positive paddle either anti-paddle.So-called positive paddle, refers to from driving
Part such as motor tail portion is seen to motor head direction, is rotated clockwise to generate the propeller of lift；So-called anti-paddle refers to from motor tail
Portion is seen to motor head direction, is rotated to produce the propeller of lift counterclockwise.The knot of the structure of the positive paddle and the anti-paddle
Mirror symmetry between structure, therefore hereafter only illustrate the structure of the propeller by taking positive paddle as an example.
In addition, the orientation term such as upper and lower occurred in the present embodiment be with the propeller be installed on the aircraft with
The normal operational attitude of the propeller and the aircraft is reference afterwards, and be should not be considered as restrictive.
Below in conjunction with the accompanying drawings, the propeller of the utility model, Power Component and aircraft are described in detail.It is not rushing
In the case of prominent, the feature in following embodiment and embodiment can be combined with each other.
Also referring to Fig. 1 and Fig. 2, the utility model provides a kind of propeller 100.Propeller 100 includes blade 20.
Blade 20 includes pressure face 21, suction surface 22, rear 23, leading edge 24, blade root 25, blade tip 26 and sweepback portion 261.
Blade tip 26 deviates from blade root 25.Suction surface 22 is opposite with pressure face 21.Leading edge 24 is connected to the side of pressure face 21 and suction surface 22
Side, rear 23 are connected to another side of pressure face 21 and suction surface 22.Sweepback portion 261 is formed in blade tip 26.Leading edge 24 is from paddle
Root 25, which is extended, to be extended and to towards the side inclination where pressure face 21 close to one where the part of blade tip 26 towards suction surface 22
Side reversion tilts and is intersected in blade tip 26 with rear 23.Sweepback portion 261 tilts extension from leading edge 24 to rear 23.Wherein, pressure
The surface towards ground of blade 20 when face 21 is normal vehicle operation, blade 20 when suction surface 22 is normal vehicle operation
The surface towards sky.
The leading edge 24 of the propeller 100 of the utility model, which is extended from blade root 25 to towards the side inclination where pressure face 21, prolongs
It stretches and is being tilted close to the side reversion where the part of blade tip 26 towards suction surface 22 and be intersected in blade tip 26, sweepback with rear 23
Portion 261 tilts extension from leading edge 24 to rear 23, can reduce air drag using the propeller 100 of the blade 20, improve
Pulling force and efficiency, increase aircraft after boat distance and while improve the flying quality of aircraft, also reduce blade
20 noises generated at work so that aircraft is quieter in hovering, improves user experience.
Also referring to Fig. 1 to Fig. 4, in the present embodiment, optionally, blade 20 is formed in the position of blade tip 26 at back bending
262, leading edge 24 262 extends and extends to being tilted to the side where suction surface 22 from back bending.262 position MM tables at back bending
Show.
In the present embodiment, propeller 100 further includes propeller hub 10, and blade 20 is at least two, the connection of at least two blades 20
Center on propeller hub 10 and about propeller hub 10 is centrosymmetric.The balance of propeller 100 can be improved as a result,.262 at back bending
It is the 90.9% of the radius of propeller 100 apart from the center of propeller hub 10.262 center far from propeller hub 10 at back bending as a result, is promoted
Blade 20 it is overall beautiful.
In the present embodiment, optionally, the leading edge that 24 evagination of leading edge is formed with the shape in curved surface close to blade root 25 arches upward portion
241；Or/and 23 evagination of rear is formed with the rear of the shape in curved surface close to blade root 25 and arches upward portion 231.
Specifically, 24 evagination of leading edge is formed with the leading edge of the shape in curved surface close to blade root 25 and arches upward portion 241；Alternatively, rear
The rear that 23 evaginations are formed with the shape in curved surface close to blade root 25 arches upward portion 231；Alternatively, 24 evagination of leading edge is formed with close to blade root
The leading edge of 25 shape in curved surface arches upward portion 241, and 23 evagination of rear is formed with the rear close to the shape in curved surface of blade root 25 and arches upward
Portion 231, to play the effect for the pulling force for further increasing blade 20.
Wherein, it can be the shapes such as ellipse, diamond shape that propeller hub 10, which can be cylindric or propeller hub 10 section,.Propeller hub 10
Center is equipped with connecting hole, and connecting hole is used to be set in the output end of motor.Blade 20 can be in strip, blade 20 and propeller hub
10 connections, and radially extending along propeller hub 10.
Referring to Fig. 5, in the present embodiment, optionally, blade 20 has the central axes J-J across the center of propeller hub 10, preceding
There is edge 24 the leading edge tangent line K-K for being parallel to central axes J-J, rear 23 to have the rear tangent line L-L for being parallel to central axes J-J.
Sweepback portion 261 is located between leading edge tangent line K-K and rear tangent line L-L.Sweepback portion 261 can reduce the generation of blade 20 as a result,
Turbulent flow and downwash flow, to reduce the turbulent flow and downwash flow got on aircraft skin, in the air for reducing propeller 100
Resistance improves the navigability of aircraft, makes the noise that aircraft entirety is further decreased while aircraft is more steady.
In the present embodiment, optionally, suction surface 22 and pressure face 21 are curved surface.Suction surface 22 and pressure face 21 are curved surface
Aerodynamic configuration, be avoided that 20 each section of blade generate turbulent flow and downwash flow directly impact aircraft skin, to subtract
The noise of bug entirety.
Also referring to table 1 and Fig. 5-6, in the present embodiment, sweepback portion 261 tilts extension from leading edge 24 to rear 23.Tool
Body, abscissa Blade Radius (mm) indicate a certain position (such as at MM) of the blade 20 in spanwise direction apart from propeller hub
The distance at 10 centers.Starting point is 10 center of propeller hub, and distance of the blade 20 apart from the center of propeller hub 10 is 0mm at this time, and terminal is
The free end 261 of blade tip 26, distance of the blade 20 apart from the center of propeller hub 10 is 110mm at this time.Ordinate Sweep Length
(mm) (distance of sweepback, the inclined degree in sweepback portion 261) indicates the point at the 1/2 of the section chord length of blade 20 with respect to central axes
The distance of J-J.Since the angle of attack of embodiment is respectively less than 25 degree, the section chord length of blade 20 1/2 at point and Fig. 5 in bow
Depending on visual angle blade 20 1/2 at point difference it is smaller, therefore in Fig. 1 vertical view visual angle blade 20 1/2 at point it is opposite
The distance of central axes J-J indicates SweepLength.Wherein, the positive value of ordinate Sweep Length (mm) is sweepback, negative value
For sweepforward.
Table 1
As shown in Table 1, when the distance in blade 20 apart from the center of propeller hub 10 is 90.75mm, sweepback portion 261 starts before
Edge 24 is tilted to rear 23 to be extended.When multiple blades 20 work at the same time, sweepback portion 261 is regularly from leading edge 24 to rear 23
It tilts and extends, the turbulent flow and downwash flow since multiple blades 20 interact and generate can be reduced, and reduce and get to flight
Turbulent flow on device shell and downwash flow reduce the air drag that blade 20 is subject to, improve the navigability of aircraft, make flight
Device is more steady, meanwhile, further reduce the noise due to turbulent flow and downwash flow impact aircraft skin generation.
Also referring to Fig. 5, Fig. 7 and table 2, in the present embodiment, leading edge 24 262 is extended to 22 institute of suction surface from back bending
Side tilt extend.Specifically, abscissa Blade Radius (mm) indicate a certain position of the blade 20 in spanwise direction
Set the distance of (such as at MM) apart from 10 center of propeller hub.Starting point is 10 center of propeller hub, and blade 20 is in propeller hub 10 at this time
The distance of the heart is 0mm, and terminal is the free end 261 of blade tip 26, and distance of the blade 20 apart from the center of propeller hub 10 is at this time
110mm.Ordinate Anhedral Length (mm) (upper anti-distance, the inclined degree of leading edge 24) indicate the section of blade 20
The distance of the opposite horizontal reference line across the center of propeller hub 10 of point at the 1/2 of chord length.Wherein, ordinate Anhedral
The positive value of Length (mm) is upper anti-, and negative value is lower anti-.
Table 2
As shown in Table 2, when the distance in blade 20 apart from the center of propeller hub 10 is 90.75mm, leading edge 24 start to extend to
Tilt and extend to the side where suction surface 22, i.e., when the distance in blade 20 apart from the center of propeller hub 10 is 90.75mm on it is anti-.
Leading edge 24 262 is extended and is increased to tilting the degree extended to the side where suction surface 22 from back bending.It is same in multiple blades 20
When working, leading edge 24 regularly 262 extends and extends to being tilted to the side where suction surface 22 from back bending, can reduce
Due to multiple blades 20 interact and generate turbulent flow and downwash flow, and reduce get to the turbulent flow on aircraft skin and under
Gas washing stream, in addition it is possible to which the lift point of specified blade 20, enables aircraft to correct flight attitude automatically, increase aircraft
Inertial stability, it is more steady when making aircraft flight, meanwhile, further reduce since turbulent flow and downwash flow impact fly
The noise that row device shell generates.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Fig. 8
The angle of attack 1 of D1 at the 27.2% of radius, blade 20 are 21.64 ° ± 2.5 °, and the chord length L1 of blade 20 is 27.53mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 1 of blade 20 can be with
For 19.14 ° or 21.64 ° or 24.14 ° or 19.64 °, 20.14 °, 20.64 °, 21.14 °, 22.14 °, 22.64 °,
Any one or above-mentioned arbitrary numerical value between the two, the chord length L1 of blade 20 in 23.14 °, 23.64 ° etc. can be
22.53mm or 27.53mm or 32.53mm or 23.53mm, 24.53mm, 25.53mm, 26.53mm, 28.53mm,
Any one in 29.53mm, 30.53mm, 31.53mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Fig. 9
The angle of attack 2 of D2 at the 36.3% of radius, blade 20 are 20.43 ° ± 2.5 °, and the chord length L2 of blade 20 is 27.78mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 2 of blade 20 can be with
For 17.93 ° or 20.43 ° or 22.93 ° or 18.43 °, 18.93 °, 19.43 °, 19.93 °, 20.93 °, 21.43 °,
Any one or above-mentioned arbitrary numerical value between the two, the chord length L2 of blade 20 in 21.93 °, 22.43 ° etc. can be
22.78mm or 27.78mm or 32.78mm or 23.78mm, 24.78mm, 25.78mm, 26.78mm, 28.78mm,
Any one in 29.78mm, 30.78mm, 31.78mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 10
The angle of attack 3 of D3 at the 45.5% of radius, blade 20 are 19.78 ° ± 2.5 °, and the chord length L3 of blade 20 is 26.58mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 3 of blade 20 can be with
For 17.28 ° or 19.78 ° or 22.28 ° or 17.78 °, 18.28 °, 18.78 °, 19.28 °, 20.28 °, 20.78 °,
Any one or above-mentioned arbitrary numerical value between the two, the chord length L3 of blade 20 in 21.28 °, 21.78 ° etc. can be
21.58mm or 26.58mm or 31.58mm or 22.58mm, 23.58mm, 24.58mm, 25.58mm, 27.58mm,
Any one in 28.58mm, 29.58mm, 30.58mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 11
The angle of attack 4 of D4 at the 54.6% of radius, blade 20 are 17.83 ° ± 2.5 °, and the chord length L4 of blade 20 is 24.75mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 4 of blade 20 can be with
For 15.33 ° or 17.83 ° or 20.33 ° or 15.83 °, 16.33 °, 16.83 °, 17.33 °, 18.33 °, 18.83 °,
Any one or above-mentioned arbitrary numerical value between the two, the chord length L4 of blade 20 in 19.33 °, 19.83 ° etc. can be
19.75mm or 24.75mm or 29.75mm or 20.75mm, 21.75mm, 22.75mm, 23.75mm, 25.75mm,
Any one in 26.75mm, 27.75mm, 28.75mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 12
The angle of attack 5 of D5 at the 63.6% of radius, blade 20 are 16.42 ° ± 2.5 °, and the chord length L5 of blade 20 is 22.65mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 5 of blade 20 can be with
For 13.92 ° or 16.42 ° or 18.92 ° or 14.42 °, 14.92 °, 15.42 °, 15.92 °, 16.92 °, 17.42 °,
Any one or above-mentioned arbitrary numerical value between the two, the chord length L5 of blade 20 in 17.92 °, 18.42 ° etc. can be
17.65mm or 22.65mm or 27.65mm or 18.65mm, 19.65mm, 20.65mm, 21.65mm, 23.65mm,
Any one in 24.65mm, 25.65mm, 26.65mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 13
The angle of attack 6 of D6 at the 72.7% of radius, blade 20 are 14.97 ° ± 2.5 °, and the chord length L6 of blade 20 is 20.07mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 6 of blade 20 can be with
For 12.47 ° or 14.97 ° or 17.47 ° or 12.97 °, 13.47 °, 13.97 °, 14.47 °, 15.47 °, 15.97 °,
Any one or above-mentioned arbitrary numerical value between the two, the chord length L6 of blade 20 in 16.47 °, 16.97 ° etc. can be
15.07mm or 20.07mm or 25.07mm or 16.07mm, 17.07mm, 18.07mm, 19.07mm, 21.07mm,
Any one in 22.07mm, 23.07mm, 24.07mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 14
The angle of attack 7 of D7 at the 81.8% of radius, blade 20 are 13.17 ° ± 2.5 °, and the chord length L7 of blade 20 is 16.64mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 7 of blade 20 can be with
For 10.67 ° or 13.17 ° or 15.67 ° or 11.17 °, 11.67 °, 12.17 °, 12.67 °, 13.67 °, 14.17 °,
Any one or above-mentioned arbitrary any value between the two, the chord length L7 of blade 20 in 14.67 °, 15.17 ° etc. can be
11.64mm or 16.64mm or 21.64mm or 12.64mm, 13.64mm, 14.64mm, 15.64mm, 17.64mm,
Any one in 18.64mm, 19.64mm, 20.64mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 15
The angle of attack 8 of D8 at the 90.9% of radius, blade 20 are 10.68 ° ± 2.5 °, and the chord length L8 of blade 20 is 11.15mm ± 5mm, with
It is further reduced the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 8 of blade 20 can be with
For 8.18 ° or 10.68 ° or 13.18 ° or 8.68 °, 9.18 °, 9.68 °, 10.18 °, 11.18 °, 11.68 °, 12.18 °,
12.68 ° it is equal in any one or above-mentioned arbitrary numerical value between the two, the chord length L8 of blade 20 can be 6.15mm or
11.15mm or 16.15mm or 7.15mm, 8.15mm, 9.15mm, 10.15mm, 12.15mm, 13.15mm, 14.15mm,
Any one in 15.15mm etc. or above-mentioned arbitrary numerical value between the two.
It is being propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment also referring to Fig. 5 and Figure 16
D9 at the 100% of radius, the angle of attack 9 of blade 20 are 6.63 ° ± 2.5 °, and the chord length L9 of blade 20 is 3.92mm ± 2mm, with into
One step reduces the air drag of propeller 100, improves pulling force and efficiency, reduces noise.Wherein, the angle of attack 9 of blade 20 can be
In 4.13 ° or 6.63 ° or 9.13 ° or 4.63 °, 5.13 °, 5.63 °, 6.13 °, 7.13 °, 7.63 °, 8.13 °, 8.63 ° etc.
Any one or above-mentioned arbitrary numerical value between the two, the chord length L9 of blade 20 can be 1.92mm or 3.92mm or
Any one in 5.92mm or 2.42mm, 2.92mm, 3.42mm, 4.42mm, 4.92mm, 5.42mm etc. or above-mentioned
It anticipates numerical value between the two.
Wherein, angle of attack refers to the angle between the wing chord and speed of incoming flow of blade 20, and chord length L refers to 20 cross section of blade
Length.
Please again together refering to Fig. 5 and Fig. 8, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 1 of the D1 at the center 30mm apart from propeller hub 10, blade 20 are 21.64 °, and the chord length L1 of blade 20 is
27.53mm.Wherein, the diameter of propeller 100 can be 198mm or 220mm or 242mm or 200mm, 205mm,
Any one in 210mm, 215mm, 225mm, 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Fig. 9, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 2 of the D2 at the center 40mm apart from propeller hub 10, blade 20 are 20.43 °, and the chord length L2 of blade 20 is
27.78mm.Wherein, the diameter of propeller 100 can be 198mm or 220mm or 242mm or 200mm, 205mm,
Any one in 210mm, 215mm, 225mm, 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Figure 10, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 3 of the D3 at the center 50mm apart from propeller hub 10, blade 20 are 19.78 °, and the chord length L3 of blade 20 is
26.58mm.Wherein, the diameter of propeller 100 can be 198mm or 220mm or 242mm or 200mm, 205mm,
Any one in 210mm, 215mm, 225mm, 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Figure 11, in the present embodiment, optionally, a diameter of 220mm ± 22mm of propeller 100.
The angle of attack 4 of the D4 at the center 60mm apart from propeller hub 10, blade 20 are 17.83 °, and the chord length L4 of blade 20 is 24.75mm.Its
In, the diameter of propeller 100 can be 198mm or 220mm or 242mm or 200mm, 205mm, 210mm, 215mm,
Any one in 225mm, 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Again together refering to Fig. 5 and Figure 12, in the present embodiment, optionally, a diameter of 220mm ± 22mm of propeller 100.
The angle of attack 5 of the D5 at the center 70mm apart from propeller hub 10, blade 20 are 16.42 °, and the chord length L5 of blade 20 is 22.65mm.By
This, can be further reduced the air drag of propeller 100, improve pulling force and efficiency, reduce noise.Wherein, propeller 100 is straight
Diameter can be 198mm or 220mm or 242mm or 200mm, 205mm, 210mm, 215mm, 225mm, 230mm, 235mm,
Any one in 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Figure 13, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 6 of the D6 at the center 80mm apart from propeller hub 10, blade 20 are 14.97 °, and the chord length L6 of blade 20 is
20.07mm.It can be further reduced the air drag of propeller 100 as a result, improve pulling force and efficiency, reduce noise.Wherein, spiral shell
Revolve paddle 100 diameter can be 198mm or 220mm or 242mm or 200mm, 205mm, 210mm, 215mm, 225mm,
Any one in 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Figure 14, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 7 of the D7 at the center 90mm apart from propeller hub 10, blade 20 are 13.17 °, and the chord length L7 of blade 20 is
16.64mm.Wherein, the diameter of propeller 100 can be 198mm or 220mm or 242mm or 200mm, 205mm,
Any one in 210mm, 215mm, 225mm, 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Figure 15, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 8 of the D8 at the center 100mm apart from propeller hub 10, blade 20 are 10.68 °, and the chord length L8 of blade 20 is
11.15mm.Wherein, the diameter of propeller 100 can be 198mm or 220mm or 242mm or 200mm, 205mm,
Any one in 210mm, 215mm, 225mm, 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to Fig. 5 and Figure 16, in the present embodiment, optionally, a diameter of 220mm of propeller 100 ±
22mm.The angle of attack 9 of the D9 at the center 110mm apart from propeller hub 10, blade 20 are 6.63 °, and the chord length L9 of blade 20 is
3.92mm.It can be further reduced the air drag of propeller 100 as a result, improve pulling force and efficiency, reduce noise.Wherein, spiral
The diameter of paddle 100 can be 198mm or 220mm or 242mm or 200mm, 205mm, 210mm, 215mm, 225mm,
Any one in 230mm, 235mm, 240mm etc. or above-mentioned arbitrary numerical value between the two.
Please again together refering to fig. 1 and Fig. 5, in the present embodiment, optionally, the screw pitch of blade 20 is 4.8 ± 0.5 inches.By
This, can reduce the resistance of air, improve the pulling force of blade 20.Wherein, the screw pitch of blade 20 can be 4.3 inches or 4.8 inches
Or 5.3 inches or 4.4 inches, 4.5 inches, 4.6 inches, 4.7 inches, 4.9 inches, 5.0 inches, 5.1 inches, 5.2 English
Any one in very little etc. or above-mentioned arbitrary numerical value between the two.
Please refer to table 3 and Figure 17, the ratio of propeller 100 and the test result of existing propeller provided in this embodiment
It is right.By can be seen that in table 3, under identical hovering operating mode acoustical behavior test condition, propeller 100 that the present embodiment is provided
For the noise of generation compared with the noise that existing propeller generates, the noise for the propeller 100 that the present embodiment is provided is integrally low
In existing propeller.The propeller 100 that the present embodiment is provided as a result, can effectively reduce power noise.In addition, by Figure 17
Frequency response curve (Frequency (Hz)-Loudness (dB-A)) can be seen that, under conditions of most of identical frequency, this reality
The loudness for applying the propeller 100 that example is provided is less than existing propeller.Especially under identical high frequency condition, the present embodiment
The loudness of the propeller 100 provided is significantly lower than the loudness of existing propeller.The propeller that the present embodiment is provided as a result,
100 can effectively reduce high frequency noise, alleviate the sense of discomfort that high frequency noise causes human ear, improve user experience.In addition to this,
The propeller 100 that the present embodiment is provided can be applied in the scene high to sound requirement, for example investigate, take photo by plane and (recorded when taking photo by plane
Enter image and audio) etc..
Table 3
Due to mirror symmetry between the structure and the structure of positive paddle of anti-paddle, the structure of anti-paddle is repeated no more.
To sum up, air drag can be reduced using the propeller 100 of the blade 20 of the utility model above-described embodiment, improved
Pulling force and efficiency, increase aircraft after boat distance and improve the flying quality of aircraft.Meanwhile having on the market relatively
Propeller, under identical hovering operating mode acoustical behavior test condition, using the blade 20 propeller 100 generate noise
Entirety be less than existing propeller.The propeller 100 that the present embodiment is provided as a result, can effectively reduce power noise.In addition,
Under conditions of most of identical frequency, the loudness using the propeller 100 of the blade 20 of the utility model above-described embodiment is low
In existing propeller.Especially under identical high frequency condition, the loudness for the propeller 100 that the present embodiment is provided is obviously low
In the loudness of existing propeller.The propeller 100 that the present embodiment is provided as a result, can effectively reduce high frequency noise, alleviate
High frequency noise causes the sense of discomfort of human ear, improves user experience.It is whole to be less than existing propeller.The present embodiment institute as a result,
The propeller 100 of offer can effectively reduce power noise.
The utility model embodiment also provides a kind of Power Component, including actuator and the utility model any embodiment
Propeller 100, propeller 100 are connect by propeller hub 10 with actuator.Wherein, the concrete structure of propeller 100 and aforementioned implementation
Example is similar, and details are not described herein again.The description as described in propeller 100 is equally applicable to this in embodiment and embodiment i.e. as above
The Power Component that utility model embodiment provides.
In the Power Component of the utility model, the leading edge 24 of 100 blade 20 of propeller is extended from blade root 25 to towards pressure
Side where power face 21 tilt extend and tilted close to the side reversion where the part of blade tip 26 towards suction surface 22 and with
Rear 23 is intersected in blade tip 26, and sweepback portion 261 tilts extension from leading edge 24 to rear 23.Using the power packages of the propeller 100
Part can reduce air drag, improve pulling force and efficiency, increase aircraft after boat distance and improve flying for aircraft
While row performance, the noise that blade 20 generates at work is also reduced so that aircraft is quieter in hovering, improves
User experience.
In the present embodiment, optionally, actuator is motor, the KV values of motor are 300 to 800 turns/(minute volt).By
This, can ensure the power performance of Power Component.
The utility model embodiment also provides a kind of aircraft, includes the power of fuselage and the utility model any embodiment
Component, Power Component are connect with fuselage.The concrete structure of wherein Power Component is similar with previous embodiment, and details are not described herein again.
The description as described in propeller 100 is equally applicable to the utility model embodiment offer in embodiment and embodiment i.e. as above
Aircraft.
In the present embodiment, optionally, aircraft includes multiple Power Components, and the rotation direction of multiple Power Components is different.
In the present embodiment, optionally, aircraft is multi-rotor aerocraft.
In the aircraft of the utility model, since the leading edge 24 of the blade 20 of propeller 100 is extended from blade root 25 to court
Side where pressure face 21, which tilts, to be extended and is tilted simultaneously close to the side reversion where the part of blade tip 26 towards suction surface 22
It is intersected in blade tip 26 with rear 23, sweepback portion 261 tilts extension from leading edge 24 to rear 23, using the flight of the propeller 100
Device can reduce air drag, improve pulling force and efficiency, increase aircraft after boat distance and improve flying for aircraft
While row performance, the noise that blade 20 generates at work is also reduced so that aircraft is quieter in hovering, improves
User experience.
The above is only the preferred embodiment of the present utility model, not does limit in any form to the utility model
System, although the utility model has been disclosed with preferred embodiment as above, is not limited to the utility model, any to be familiar with sheet
Technical professional, in the range of not departing from technical solutions of the utility model, when the technology contents using the disclosure above
It makes a little change or is modified to the equivalent embodiment of equivalent variations, as long as being without departing from technical solutions of the utility model
Hold, any simple modification, equivalent change and modification made by the above technical examples according to the technical essence of the present invention, still
It is within the scope of the technical solutions of the present invention.
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright
Owner does not oppose the patent document in the presence of anyone replicates the proce's-verbal of Patent＆Trademark Office and archives or should
Patent discloses.
Claims (21)
1. a kind of propeller, the propeller includes blade, it is characterised in that：
The blade includes blade root, the blade tip away from the blade root, pressure face, the suction surface opposite with the pressure face, connection
In the leading edge of the pressure face and described suction surface a side, be connected to the pressure face and another side of the suction surface after
Edge and the sweepback portion for being formed in the blade tip；
The leading edge, which is extended from the blade root to towards the side inclination where the pressure face, to be extended and close to the blade tip
Part tilts towards the side reversion where the suction surface and is intersected in the blade tip with the rear, and the sweepback portion is described in
Leading edge is tilted to the rear to be extended.
2. propeller according to claim 1, which is characterized in that the blade forms back bending in the position of the blade tip
Place, the leading edge extend to the side where the suction surface from the back bending and tilt extension.
3. propeller according to claim 2, which is characterized in that the leading edge evagination is formed with is in close to the blade root
Curved leading edge arches upward portion；Or/and
The rear that the rear evagination is formed with the shape in curved surface close to the blade root arches upward portion.
4. propeller according to claim 2, which is characterized in that the propeller further includes propeller hub, and the blade is extremely
Two few, the center that at least two blades are connected on the propeller hub and about the propeller hub is centrosymmetric.
5. propeller according to claim 4, which is characterized in that apart from the center of the propeller hub be described at the back bending
The 90.9% of the radius of propeller.
6. propeller according to claim 4, which is characterized in that the blade has in the center of the propeller hub
Axis, the leading edge have the leading edge tangent line for being parallel to the central axes, and the rear is with after being parallel to the central axes
Edge tangent line, the sweepback portion is between the leading edge tangent line and the rear tangent line.
7. propeller according to claim 1, which is characterized in that the suction surface and the pressure face are curved surface.
8. according to claim 1-7 any one of them propellers, which is characterized in that in the propeller hub apart from the propeller
The heart is at the 45.5% of the radius of the propeller, and the angle of attack of the blade is 19.78 ° ± 2.5 °, and the chord length of the blade is
26.58mm±5mm。
9. propeller according to claim 8, it is characterised in that：
A diameter of 220mm ± 22mm of the propeller；
At the center 50mm apart from the propeller hub, the angle of attack of the blade is 19.78 °, and the chord length of the blade is
26.58mm。
10. according to the propeller described in claim 1-7 any one, which is characterized in that in the propeller hub apart from the propeller
Center be the propeller radius 54.6% at, the angle of attack of the blade is 17.83 ° ± 2.5 °, the string of the blade
A length of 24.75mm ± 5mm.
11. propeller according to claim 10, it is characterised in that：
A diameter of 220mm ± 22mm of the propeller；
At the center 60mm apart from the propeller hub, the angle of attack of the blade is 17.83 °, and the chord length of the blade is
24.75mm。
12. according to the propeller described in claim 1-7 any one, which is characterized in that in the propeller hub apart from the propeller
Center be the propeller radius 63.6% at, the angle of attack of the blade is 16.42 ° ± 2.5 °, the string of the blade
A length of 22.65mm ± 5mm.
13. propeller according to claim 12, it is characterised in that：
A diameter of 220mm ± 22mm of the propeller；
At the center 70mm apart from the propeller hub, the angle of attack of the blade is 16.42 °, and the chord length of the blade is
22.65mm。
14. according to the propeller described in claim 1-7 any one, which is characterized in that in the propeller hub apart from the propeller
Center be the propeller radius 72.7% at, the angle of attack of the blade is 14.97 ° ± 2.5 °, the string of the blade
A length of 20.07mm ± 5mm.
15. propeller according to claim 14, it is characterised in that：
A diameter of 220mm ± 22mm of the propeller；
At the center 80mm apart from the propeller hub, the angle of attack of the blade is 14.97 °, and the chord length of the blade is
20.07mm。
16. according to any propeller in claim 1-7, which is characterized in that the screw pitch of the blade is 4.8 ± 0.5
Inch.
17. a kind of Power Component, including the propeller described in any one of actuator and claim 1-16, feature exist
In the propeller is connect by the propeller hub of the propeller with the actuator.
18. Power Component according to claim 17, which is characterized in that the actuator is motor, the KV of the motor
Value for 300 to 800 turns/(minute volt).
19. a kind of aircraft, which is characterized in that including the Power Component described in fuselage and claim 17 or 18, the power
Component is connect with the fuselage.
20. aircraft according to claim 19, which is characterized in that the aircraft includes multiple Power Components, described
The rotation direction of multiple Power Components is different.
21. aircraft according to claim 19, which is characterized in that the aircraft is multi-rotor aerocraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721852806.9U CN207773438U (en) | 2017-12-26 | 2017-12-26 | Propeller, Power Component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721852806.9U CN207773438U (en) | 2017-12-26 | 2017-12-26 | Propeller, Power Component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207773438U true CN207773438U (en) | 2018-08-28 |
Family
ID=63224594
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721852806.9U Expired - Fee Related CN207773438U (en) | 2017-12-26 | 2017-12-26 | Propeller, Power Component and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207773438U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2017
- 2017-12-26 CN CN201721852806.9U patent/CN207773438U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| WO2019127028A1 (en) * | 2017-12-26 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Propeller, power assembly 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109071006A (en) | Propeller, Power Component and aircraft | |
| CN208149614U (en) | Propeller, Power Component and aircraft | |
| CN208291465U (en) | Propeller, Power Component and aircraft | |
| CN205366054U (en) | Screw, power component and aircraft | |
| WO2017124781A1 (en) | Propeller, power assembly and unmanned aircraft | |
| WO2017148133A1 (en) | Propeller, power assembly and aircraft | |
| WO2017148134A1 (en) | Propeller, power assembly and aircraft | |
| CN207917131U (en) | Propeller, Power Component and aircraft | |
| CN109071004A (en) | Propeller, power suit and unmanned vehicle | |
| WO2018157426A1 (en) | Propeller, power assembly and aircraft | |
| WO2017143771A1 (en) | Propeller, power assembly, and aircraft | |
| CN206155775U (en) | Screw, power component and aircraft | |
| CN207773438U (en) | Propeller, Power Component and aircraft | |
| CN110214110A (en) | Propeller, Power Component and aircraft | |
| WO2019019343A1 (en) | Propeller, power assembly and aircraft | |
| CN208291466U (en) | Propeller, Power Component and aircraft | |
| US5252381A (en) | Airfoil with thick trailing edge | |
| US20210078698A1 (en) | Propeller assembly, power assembly, and aircraft | |
| CN207917132U (en) | Propeller, Power Component and aircraft | |
| CN110155318A (en) | It determines the method for the initial leading edge circle of the aerofoil profile of blade and improves blade to increase the method for its negative stalling angle | |
| CN206954494U (en) | Propeller, Power Component and aircraft | |
| CN209479979U (en) | Propeller, Power Component and aircraft | |
| CN208439418U (en) | Propeller, Power Component and aircraft | |
| CN108750074A (en) | propeller | |
| CN108820187A (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: 20180828 |