CN208291465U - Propeller, Power Component and aircraft - Google Patents
Propeller, Power Component and aircraft Download PDFInfo
- Publication number
- CN208291465U CN208291465U CN201820798000.4U CN201820798000U CN208291465U CN 208291465 U CN208291465 U CN 208291465U CN 201820798000 U CN201820798000 U CN 201820798000U CN 208291465 U CN208291465 U CN 208291465U
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- Prior art keywords
- blade
- propeller
- center
- apart
- propeller hub
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
Abstract
The utility model discloses a kind of propeller, Power Component and aircraft.Propeller includes propeller hub and blade, and blade is connected on propeller hub.It is at the 45.5% of the radius of propeller at the center apart from propeller hub, the angle of attack of blade is 18.16 ° ± 2.5 °；It is at the 54.5% of the radius of propeller at the center apart from propeller hub, the angle of attack of blade is 16.80 ° ± 2.5 °；It is at the 63.6% of the radius of propeller at the center apart from propeller hub, the angle of attack of blade is 15.39 ° ± 2.5 °；It is at the 72.7% of the radius of propeller at the center apart from propeller hub, the angle of attack of blade is 13.78 ° ± 2.5 °；Therefore, in the Power Component and aircraft of the utility model, the blade for having specific shape is limited by above-mentioned parameter, and air drag can reduced using the propeller of blade, pulling force and efficiency are improved, the flying quality for improving aircraft after boat distance of aircraft is increased.
Description
Technical field
The utility model relates to aircraft fields, in particular to propeller, Power Component and aircraft.
Background technique
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.
Propeller in the prior art, outer shape are in rectangle mostly, and resistance is big, low efficiency, lead to aircraft
Flying speed is small, after boat apart from short, seriously affected the flying quality of aircraft.
Utility model content
The embodiments of the present invention provides a kind of propeller, Power Component and aircraft.
The propeller of the utility model embodiment, comprising: propeller hub and blade, the blade are connected on the propeller hub,
Wherein:
It is at the 45.5% of the radius of the propeller at the center apart from the propeller hub, the angle of attack of the blade is
18.16°±2.5°；It is the angle of attack of the blade at the 54.5% of the radius of the propeller at the center apart from the propeller hub
It is 16.80 ° ± 2.5 °；It is at the 63.6% of the radius of the propeller at the center apart from the propeller hub, the blade is attacked
Angle is 15.39 ° ± 2.5 °；The center apart from the propeller hub be the propeller radius 72.7% at, the blade
The angle of attack is 13.78 ° ± 2.5 °.
In some embodiments, the center apart from the propeller hub be the propeller radius 36.4% at, institute
The angle of attack for stating blade is 19.35 ° ± 2.5 °；And/or
It is at the 81.8% of the radius of the propeller at the center apart from the propeller hub, the angle of attack of the blade is
11.97°±2.5°；And/or
It is at the 90.9% of the radius of the propeller at the center apart from the propeller hub, the angle of attack of the blade is
9.79°±2.5°；And/or
It is at the 100% of the radius of the propeller at the center apart from the propeller hub, the angle of attack of the blade is 7.91 °
±2.5°；And/or
At the center 40mm apart from the propeller hub, the angle of attack of the blade is 19.35 °；And/or
At the center 50mm apart from the propeller hub, the angle of attack of the blade is 18.16 °；And/or
At the center 60mm apart from the propeller hub, the angle of attack of the blade is 16.80 °；And/or
At the center 70mm apart from the propeller hub, the angle of attack of the blade is 15.39 °；And/or
At the center 80mm apart from the propeller hub, the angle of attack of the blade is 13.78 °；And/or
At the center 90mm apart from the propeller hub, the angle of attack of the blade is 11.97 °；And/or
At the center 100mm apart from the propeller hub, the angle of attack of the blade is 9.79 °；And/or
At the center 110mm apart from the propeller hub, the angle of attack of the blade is 7.91 °.
In some embodiments, the center apart from the propeller hub be the propeller radius 45.5% at, institute
The chord length for stating blade is 23.80mm ± 5mm；And/or
It is at the 54.5% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is
21.85mm±5mm；And/or
It is at the 63.6% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is
19.92mm±5mm；And/or
It is at the 72.7% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is
17.98mm±5mm；And/or
At the center 50mm apart from the propeller hub, the chord length of the blade is 23.80mm；And/or
At the center 60mm apart from the propeller hub, the chord length of the blade is 21.85mm；And/or
At the center 70mm apart from the propeller hub, the chord length of the blade is 19.92mm；And/or
At the center 80mm apart from the propeller hub, the chord length of the blade is 17.98mm.
In some embodiments, the center apart from the propeller hub be the propeller radius 36.4% at, institute
The chord length for stating blade is 25.72mm ± 5mm；And/or
It is at the 81.8% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is
16.03mm±5mm；And/or
It is at the 90.9% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is
12.90mm±5mm；And/or
It is at the 100% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is
4.42mm±2mm；And/or
At the center 40mm apart from the propeller hub, the chord length of the blade is 25.72mm；And/or
At the center 90mm apart from the propeller hub, the chord length of the blade is 16.03mm；And/or
At the center 100mm apart from the propeller hub, the chord length of the blade is 12.90mm；And/or
At the center 110mm apart from the propeller hub, the chord length of the blade is 4.42mm.
In some embodiments, the diameter of the propeller is 220mm ± 22mm；And/or
The screw pitch of the blade is 5.10 ± 0.5 inches.
In some embodiments, the blade includes blade root, blade tip, opposite pressure face and suction away from the blade root
Power face, the leading edge for being connected to the pressure face and described suction surface a side are connected to the pressure face and the suction surface is another
The rear of a side and the sweepback portion for being formed in the blade tip, the sweepback portion tilt extension from the leading edge to the rear；
Side where suction surface described in Zhan Xiangchao of the blade tip along the blade, which tilts, to be extended.
In some embodiments, the blade is formed at back bending in the position close to the blade tip, and the leading edge is from institute
It states the side inclination where starting suction surface described in the Zhan Xiangchao along the blade at back bending to extend, the sweepback portion is returned from described
Crook is tilted from the leading edge to the rear to be extended, and the center at the back bending apart from the propeller hub is the half of the propeller
The 88% of diameter.
In some embodiments, the leading edge that the leading edge evagination is formed with the shape in curved surface close to the blade root arches upward
Portion, the rear that the rear evagination is formed with the shape in curved surface close to the blade root arch upward portion；And/or
The blade is at least two, and at least two blades are connected on the propeller hub and about in the propeller hub
The heart is centrosymmetric；And/or
The blade has across the central axes at the center of the propeller hub, and the leading edge, which has, is parallel to the central axes
Leading edge tangent line, the rear, which has, is parallel to the rear tangent lines of the central axes, the sweepback portion be located at the leading edge tangent line and
Between the rear tangent line；And/or
The suction surface and the pressure face are curved surface；And/or
The side of the free end of the blade tip is plane.
The Power Component of the utility model embodiment, including spiral described in actuator and any of the above-described embodiment
Paddle, the propeller are connect by the propeller hub with the actuator.
In some embodiments, the actuator is motor, and the KV value of the motor is 1040 ± 104 turns/(minute
Volt).
The aircraft of the utility model embodiment includes Power Component described in fuselage and any of the above-described embodiment, institute
Power Component is stated to connect with the fuselage.
In some embodiments, the aircraft includes multiple Power Components, the rotation side of the multiple Power Component
To difference, the aircraft is multi-rotor aerocraft.
In the aircraft and Power Component of the utility model embodiment, due to being propeller at the center apart from propeller hub
At the 45.5% of radius, the angle of attack of blade is 18.16 ° ± 2.5 °；It is the radius of propeller at the center apart from propeller hub
At 54.5%, the angle of attack of blade is 16.80 ° ± 2.5 °；It is paddle at the 63.6% of the radius of propeller at the center apart from propeller hub
The angle of attack of leaf is 15.39 ° ± 2.5 °；It is at the 72.7% of the radius of propeller at the center apart from propeller hub, the angle of attack of blade is
13.78°±2.5°；Therefore, the blade for having specific shape is limited by above-mentioned parameter, can subtracted using the propeller of blade
Few air drag, improves pulling force and efficiency, increases the flying quality that aircraft is improved after boat distance of aircraft.
The additional aspect and advantage of the embodiments of the present invention will be set forth in part in the description, partially will be from
Become obvious in following description, or is recognized by the practice of the embodiments of the present invention.
Detailed description of the invention
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, in which: illustrating in newly-increased attached drawing modification, specification
Fig. 1 is a kind of floor map of propeller provided by the embodiment of the utility model.
Fig. 2 is the cross-sectional view of the B-B section at the center 50mm in the propeller of embodiment illustrated in fig. 1 apart from propeller hub.
Fig. 3 is the cross-sectional view of the C-C section at the center 60mm in the propeller of embodiment illustrated in fig. 1 apart from propeller hub.
Fig. 4 is the cross-sectional view of the D-D section at the center 70mm in the propeller of embodiment illustrated in fig. 1 apart from propeller hub.
Fig. 5 is the cross-sectional view of the E-E section at the center 80mm in the propeller of embodiment illustrated in fig. 1 apart from propeller hub.
Fig. 6 is the cross-sectional view of the A-A section in the propeller of embodiment illustrated in fig. 1 at propeller hub center 40mm.
Fig. 7 is the cross-sectional view of the F-F section at the center 90mm in the propeller of embodiment illustrated in fig. 1 apart from propeller hub.
Fig. 8 is the cross-sectional view of the G-G section in the propeller of embodiment illustrated in fig. 1 at propeller hub center 100mm.
Fig. 9 is the cross-sectional view of the H-H section at the center 110mm in the propeller of embodiment illustrated in fig. 1 apart from propeller hub.
Figure 10 is a kind of perspective view of propeller provided by the embodiment of the utility model.
Figure 11 is a kind of perspective view of propeller provided by the embodiment of the utility model.
Figure 12 is a kind of floor map of propeller provided by the embodiment of the utility model.
Figure 13 is a kind of floor map of propeller provided by the embodiment of the utility model.
Figure 14 is the coordinate schematic diagram of blade rotation center provided by the embodiment of the utility model.
Figure 15 is a kind of floor map of aircraft provided by the embodiment of the utility model.
Main element symbol description:
Propeller 100, blade 20, blade root 21, blade tip 22, sweepback portion 221, free end 222, pressure face 23, is inhaled propeller hub 10
Power face 24, leading edge 25, leading edge arch upward portion 251, rear 26, rear arch upward portion 261,27 at back bending；
Power Component 200, actuator 30, horn 40；
Aircraft 1000, fuselage 50；
Specific embodiment
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 only to be not intended to be limiting this reality merely for for the purpose of describing particular embodiments in the term that the utility model uses
With novel.In the "an" of the utility model and singular used in the attached claims, " described " and "the"
Most forms are intended to include, unless the context clearly indicates other meaning.It is also understood that term used herein " and/
Or " refer to and include that one or more associated any or all of project listed 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 to for same type of information being distinguished from each other out.For example, not
In the case where 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 be with
The referred to as first information.Depending on context, word as used in this " if " can be construed to " ... when " or
" when ... " or " in response to determination ".
The positional terms such as upper and lower occurred in the present embodiment be after being installed on aircraft with propeller the propeller with
And the normal operational attitude of the aircraft is reference, and should not be considered as restrictive.
With reference to the accompanying drawing, the propeller of the utility model, Power Component and aircraft are described in detail.It is not rushing
In the case where prominent, the feature in following embodiment and embodiment be can be combined with each other.
Referring to Figure 1 to Fig. 5, the utility model embodiment provides a kind of propeller 100, and propeller 100 includes propeller hub 10
With blade 20.
Blade 20 is connected on propeller hub 10.Certainly, blade 20 can be integrally formed with propeller hub 10, can also be processed respectively again
It is fixedly mounted integral.It is D2 at the 45.5% of the radius of propeller 100, the angle of attack 2 of blade 20 at the center apart from propeller hub 10
It is 18.16 ° ± 2.5 °.It is D3 at the 54.5% of the radius of propeller 100, the angle of attack 3 of blade 20 at the center apart from propeller hub 10
It is 16.80 ° ± 2.5 °.It is D4 at the 63.6% of the radius of propeller 100, the angle of attack 4 of blade 20 at the center apart from propeller hub 10
It is 15.39 ° ± 2.5 °.It is D5 at the 72.7% of the radius of propeller 100, the angle of attack 5 of blade 20 at the center apart from propeller hub 10
It is 13.78 ° ± 2.5 °.
In the present embodiment, due to the center apart from propeller hub 10 be propeller 100 radius 45.5% at D2, blade 20
Angle of attack 2 be 18.16 ° ± 2.5 °；It is D3 at the 54.5% of the radius of propeller 100, blade 20 at the center apart from propeller hub 10
Angle of attack 3 be 16.80 ° ± 2.5 °；It is D4 at the 63.6% of the radius of propeller 100, blade 20 at the center apart from propeller hub 10
Angle of attack 4 be 15.39 ° ± 2.5 °；It is D5 at the 72.7% of the radius of propeller 100, blade 20 at the center apart from propeller hub 10
Angle of attack 5 be 13.78 ° ± 2.5 °；Therefore, the blade 20 for having specific shape is limited by above-mentioned parameter, using blade 20
Propeller 100 can reduce air drag, improve pulling force and efficiency, increase aircraft 1000 (as shown in figure 15) after navigate away from
From the flying quality to improve aircraft 1000.
Continuing with referring to Fig. 1 to Fig. 5, the utility model embodiment provides a kind of propeller 100, and propeller 100 includes paddle
Hub 10 and blade 20.
It is D2 at the 45.5% of the radius of propeller 100 at the center apart from propeller hub 10, the angle of attack 2 of blade 20 is
18.16 ° ± 2.5 °, the chord length L2 of blade 20 is 23.80mm ± 5mm.It is the radius of propeller 100 at the center apart from propeller hub 10
54.5% at D3, the angle of attack 3 of blade 20 is 16.80 ° ± 2.5 °, and the chord length L3 of blade 20 is 21.85mm ± 5mm.In distance
The center of propeller hub 10 is D4 at the 63.6% of the radius of propeller 100, and the angle of attack 4 of blade 20 is 15.39 ° ± 2.5 °, blade 20
Chord length L4 be 19.92mm ± 5mm.It is D5 at the 72.7% of the radius of propeller 100, blade 20 at the center apart from propeller hub 10
Angle of attack 5 be 13.78 ° ± 2.5 °, the chord length L5 of blade 20 is 17.98mm ± 5mm.
It is D2 at the 45.5% of the radius of propeller 100 at the center apart from propeller hub 10 in the present embodiment, blade 20 is attacked
Angle α 2 is 18.16 ° ± 2.5 °, and the chord length L2 of blade 20 is 23.80mm ± 5mm；It is propeller 100 at the center apart from propeller hub 10
Radius 54.5% at D3, the angle of attack 3 of blade 20 is 16.80 ° ± 2.5 °, and the chord length L3 of blade 20 is 21.85mm ± 5mm；
It is D4 at the 63.6% of the radius of propeller 100 at the center apart from propeller hub 10, the angle of attack 4 of blade 20 is 15.39 ° ± 2.5 °,
The chord length L4 of blade 20 is 19.92mm ± 5mm；It is D5 at the 72.7% of the radius of propeller 100 at the center apart from propeller hub 10,
The angle of attack 5 of blade 20 is 13.78 ° ± 2.5 °, and the chord length L5 of blade 20 is 17.98mm ± 5mm；Therefore, it is limited by above-mentioned parameter
The blade 20 for providing standby specific shape can reduce air drag using the propeller 100 of blade 20, improve pulling force and effect
Rate increases the flying quality that aircraft 1000 is improved after boat distance of aircraft 1000.
Table 1 is referred to, the comparison of the test result of propeller 100 provided by the present embodiment and existing propeller, by
It can be seen that in table 1, under identical pulling force, the power of the provided propeller 100 of present embodiment is lower, namely: lesser
Under power condition, there is bigger pulling force, to reduce kwh loss, increase endurance distance.Present embodiment provides as a result,
Propeller 100, can be under the High aititude region that density reduces or the biggish extreme case of low altitude area take-off weight
Pulling force is significantly improved, guarantee enough power while extending cruise duration, improves flying quality.
Table 1
It is D2 at the 45.5% of the radius of propeller 100, blade 20 at the center apart from propeller hub 10 referring to Figure 1 to Fig. 5
Angle of attack 2 can for 15.66 ° or 18.16 ° or 20.66 ° or 16.16 °, 16.66 °, 17.16 °, 17.66 °,
Any one in 18.66 °, 19.16 °, 19.66 °, 20.16 ° etc. or above-mentioned any any value between the two, blade 20
Chord length L2 can for 18.80mm or 23.80mm or 28.80mm or 19.80mm, 20.80mm, 21.80mm,
Any one in 22.80mm, 24.80mm, 25.80mm, 26.80mm, 27.80mm etc. or above-mentioned any number between the two
Value.It is D3 at the 54.5% of the radius of propeller 100 at the center apart from propeller hub 10, the angle of attack 3 of blade 20 can be 14.30 °
Or 16.80 ° or 19.30 ° or 14.80 °, 15.30 °, 15.80 °, 16.30 °, 17.30 °, 17.80 °, 18.30 °,
18.80 ° it is equal in any one or above-mentioned any numerical value between the two, the chord length L3 of blade 20 can for 16.85mm or
21.85mm or 26.85mm or 17.85mm, 18.85mm, 19.85mm, 20.85mm, 22.85mm, 23.85mm,
Any one in 24.85mm, 25.85mm etc. or above-mentioned any numerical value between the two.It is spiral shell at the center apart from propeller hub 10
Revolve D4 at the 63.6% of the radius of paddle 100, the angle of attack 4 of blade 20 can be 12.89 ° or 15.39 ° or 17.89 °, either
Any one in 13.39 °, 13.89 °, 14.39 °, 14.89 °, 15.89 °, 16.39 °, 16.89 °, 17.39 ° etc. or above-mentioned
Anticipate numerical value between the two, the chord length L4 of blade 20 can for 14.92mm or 19.92mm or 24.92mm or 15.92mm,
Any one in 16.92mm, 17.92mm, 18.92mm, 20.92mm, 21.92mm, 22.92mm, 23.92mm etc. or above-mentioned
It anticipates numerical value between the two.It is D5 at the 72.7% of the radius of propeller 100, the angle of attack of blade 20 at the center apart from propeller hub 10
α 5 can for 11.28 ° or 13.78 ° or 16.28 ° or 11.78 °, 12.28 °, 12.78 °, 13.28 °, 14.28 °,
Any one in 14.78 °, 15.28 °, 15.78 ° etc. or above-mentioned any numerical value between the two, the chord length L5 of blade 20 can be with
For 12.98mm or 17.98mm or 22.98mm or 13.98mm, 14.98mm, 15.98mm, 16.98mm, 18.98mm,
Any one in 19.98mm, 20.98mm, 21.98mm etc. or above-mentioned any numerical value between the two.
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 long strip, blade 20 and propeller hub
10 connections, and radially extending along propeller hub 10.
It is shown in Figure 6, it is the radius of propeller 100 at the center apart from propeller hub 10 optionally in the present embodiment
D1 at 36.4%, the angle of attack 1 of blade 20 are 19.35 ° ± 2.5 °, and the chord length L1 of blade 20 is 25.72mm ± 5mm, with further
The air drag of propeller 100 is reduced, pulling force and efficiency are improved.Wherein, the angle of attack 1 of blade 20 can for 16.85 ° or
19.35 ° or 21.85 ° or 17.35 °, 17.85 °, 18.35 °, 18.85 °, 19.85 °, 20.35 °, 20.85 °, 21.35 °
Any one in or above-mentioned any numerical value between the two, the chord length L1 of blade 20 can for 20.72mm or 25.72mm or
30.72mm or 21.72mm, 22.72mm, 23.72mm, 24.72mm, 26.72mm, 27.72mm, 28.72mm, 29.72mm
Any one in or above-mentioned any numerical value between the two.
It is shown in Figure 7, it is the radius of propeller 100 at the center apart from propeller hub 10 optionally in the present embodiment
D6 at 81.8%, the angle of attack 6 of blade 20 are 11.97 ° ± 2.5 °, and the chord length L6 of blade 20 is 16.03mm ± 5mm, with further
The air drag of propeller 100 is reduced, pulling force and efficiency are improved.Wherein, the angle of attack 6 of blade 20 can be 9.47 ° or 11.97 °
Or appointing in 14.47 ° or 9.97 °, 10.47 °, 10.97 °, 11.47 °, 12.47 °, 12.97 °, 13.47 °, 13.97 ° etc.
Meaning one or above-mentioned any numerical value between the two, the chord length L6 of blade 20 can be 11.03mm or 16.03mm or 21.03mm,
Either appointing in 12.03mm, 13.03mm, 14.03mm, 15.03mm, 17.03mm, 18.03mm, 19.03mm, 20.03mm etc.
Meaning one or above-mentioned any numerical value between the two.
It is shown in Figure 8, it is the radius of propeller 100 at the center apart from propeller hub 10 optionally in the present embodiment
D7 at 90.9%, the angle of attack 7 of blade 20 are 9.79 ° ± 2.5 °, and the chord length L7 of blade 20 is 12.90mm ± 5mm, with further
The air drag of propeller 100 is reduced, pulling force and efficiency are improved.Wherein, the angle of attack 7 of blade 20 can be 7.29 ° or 9.79 °
Or it is any in 12.29 ° or 7.79 °, 8.29 °, 8.79 °, 9.29 °, 10.29 °, 10.79 °, 11.29 °, 11.79 ° etc.
One or above-mentioned any numerical value between the two, the chord length L7 of blade 20 can be 7.90mm or 12.90mm or 17.90mm, or
Person is any one in 8.90mm, 9.90mm, 10.90mm, 11.90mm, 13.90mm, 14.90mm, 15.90mm, 16.90mm etc.
A or above-mentioned any numerical value between the two.
It is shown in Figure 9, it is the radius of propeller 100 at the center apart from propeller hub 10 optionally in the present embodiment
D8 at 100%, the angle of attack 8 of blade 20 are 7.91 ° ± 2.5 °, and the chord length L8 of blade 20 is 4.42mm ± 2mm, further to subtract
The air drag of few propeller 100, improves pulling force and efficiency.Wherein, the angle of attack 8 of blade 20 can for 5.41 ° or 7.91 ° or
In 10.41 ° or 5.91 °, 6.41 °, 6.91 °, 7.41 °, 8.41 °, 8.91 °, 9.41 °, 9.91 ° etc. any one or
Above-mentioned any numerical value between the two, the chord length L8 of blade 20 can be 2.42mm or 4.42mm or 6.42mm, either
Any one in 2.92mm, 3.42mm, 3.92mm, 4.92mm, 5.42mm, 5.92mm etc. or above-mentioned any number between the two
Value.
Referring again to shown in Fig. 1 to Fig. 5, in the present embodiment, optionally, the diameter of propeller 100 be 220mm ±
22mm.The angle of attack 2 of the D2 at the center 50mm apart from propeller hub 10, blade 20 are 18.16 °, and the chord length L2 of blade 20 is
23.80mm.The angle of attack 3 of the D3 at the center 60mm apart from propeller hub 10, blade 20 are 16.80 °, and the chord length L3 of blade 20 is
21.85mm.The angle of attack 4 of the D4 at the center 70mm apart from propeller hub 10, blade 20 are 15.39 °, and the chord length L4 of blade 20 is
19.92mm.The angle of attack 5 of the D5 at the center 80mm apart from propeller hub 10, blade 20 are 13.78 °, and the chord length L5 of blade 20 is
17.98mm.It can be further reduced the air drag of propeller 100 as a result, improve pulling force and efficiency.Wherein, propeller 100
Diameter can for 198mm or 220mm or 242mm or 202mm, 208mm, 212mm, 216mm, 224mm, 228mm,
Any one in 232mm, 236mm, 240mm etc. or above-mentioned any numerical value between the two.
Referring again to shown in Fig. 6, in the present embodiment, optionally, the diameter of propeller 100 is 220mm ± 22mm.Away from
D1 at center 40mm from propeller hub 10, the angle of attack 1 of blade 20 are 19.35 °, and the chord length L1 of blade 20 is 25.72mm.As a result, may be used
It is further reduced the air drag of propeller 100, improves pulling force and efficiency.Wherein, the diameter of propeller 100 can be 198mm
Or 220mm or 242mm or 202mm, 208mm, 212mm, 216mm, 224mm, 228mm, 232mm, 236mm, 240mm etc.
In any one or above-mentioned any numerical value between the two.
Referring again to shown in Fig. 7, in the present embodiment, optionally, the diameter of propeller 100 is 220mm ± 22mm.In distance
D6 at the center 90mm of propeller hub 10, the angle of attack 6 of blade 20 are 11.97 °, and the chord length L6 of blade 20 is 16.03mm.It as a result, can be into
One step reduces the air drag of propeller 100, improves pulling force and efficiency.Wherein, the diameter of propeller 100 can for 198mm or
In 220mm or 242mm or 202mm, 208mm, 212mm, 216mm, 224mm, 228mm, 232mm, 236mm, 240mm etc.
Any one or above-mentioned any numerical value between the two.
Referring again to shown in Fig. 8, in the present embodiment, optionally, the diameter of propeller 100 is 220mm ± 22mm.Away from
D7 at center 100mm from propeller hub 10, the angle of attack 7 of blade 20 are 9.79 °, and the chord length L7 of blade 20 is 12.90mm.As a result, may be used
It is further reduced the air drag of propeller 100, improves pulling force and efficiency.Wherein, the diameter of propeller 100 can be 198mm
Or 220mm or 242mm or 202mm, 208mm, 212mm, 216mm, 224mm, 228mm, 232mm, 236mm, 240mm etc.
In any one or above-mentioned any numerical value between the two.
Referring again to shown in Fig. 9, in the present embodiment, optionally, the diameter of propeller 100 is 220mm ± 22mm.In distance
D8 at the center 110mm of propeller hub 10, the angle of attack 8 of blade 20 are 7.91 °, and the chord length L8 of blade 20 is 4.42mm.It as a result, can be into
One step reduces the air drag of propeller 100, improves pulling force and efficiency.Wherein, the diameter of propeller 100 can for 198mm or
In 220mm or 242mm or 202mm, 208mm, 212mm, 216mm, 224mm, 228mm, 232mm, 236mm, 240mm etc.
Any one or above-mentioned any numerical value between the two.
Referring to Figure 10 to Figure 13, in the present embodiment, optionally, blade 20 includes blade root 21, away from the blade tip of blade root 21
22, opposite pressure face 23 and suction surface 24.Blade tip 22 tilts extension to towards the side where suction surface 24 along the exhibition of blade 20.
In this way, air drag can not only be reduced, the pulling force of blade 20 is improved, the noise that blade 20 generates at work is also reduced, makes
It is quieter in hovering to obtain aircraft 1000, improves user experience.Wherein, when pressure face 23 is 1000 normal flight of aircraft
The surface towards ground of blade 20, the surface towards sky of blade 20 when suction surface 24 is 1000 normal flight of aircraft.
In the present embodiment, optionally, suction surface 24 and pressure face 23 are curved surface.Suction surface 24 and pressure face 23 are curved surface
Aerodynamic configuration, can not only reduce air drag, improve the pulling force of blade 20, moreover it is possible to the turbulent flow for avoiding 20 each section of blade from generating
And downwash flow directly impacts the fuselage 50 (as shown in figure 15) of aircraft 1000, to reduce, aircraft 1000 is whole to make an uproar
Sound.
In the present embodiment, optionally, blade 20 further include the leading edge 25 for being connected to 24 a side of pressure face 23 and suction surface,
It is connected to the rear 26 of pressure face 23 and another side of suction surface 24 and is formed in the sweepback portion 221 of blade tip 22, sweepback portion 221
It tilts and extends from leading edge 25 to rear 26.In this way, further increasing the pulling force of propeller 100 and the effect of efficiency to play.
In the present embodiment, optionally, blade 20 is formed 27 at back bending in the position of blade tip 22, and leading edge 25 27 is opened from back bending
The exhibition begun along blade 20 extends to tilting towards the side where suction surface 24, sweepback portion 221 since at back bending 27 from leading edge 25
It tilts and extends to rear 26.27 position is indicated with MM at back bending.
In the present embodiment, optionally, 27 center apart from propeller hub 10 is the 88% of the radius of propeller 100 at back bending.It returns
Center of the crook 27 far from propeller hub 10 promotes the beauty of blade 20, also reduces the horn 40 of propeller 100 and aircraft 1000
Influencing each other between (as shown in figure 15).
In the present embodiment, optionally, the leading edge that 25 evagination of leading edge is formed with the shape in curved surface close to blade root 21 arches upward portion
251, the rear that 26 evagination of rear is formed with the shape in curved surface close to blade root 21 arches upward portion 261.Leading edge arch upward portion 251 and rear arch
Playing portion 231 is that curved plays the effect for further increasing the pulling force of blade 20.
In the present embodiment, optionally, blade 20 be at least two, at least two blades 20 be connected on propeller hub 10 and about
The center of propeller hub 10 is centrosymmetric.The balance of propeller 100 can be improved as a result,.
In the present embodiment, optionally, the side of the free end 222 of blade tip 22 is plane.Propeller 100 can be promoted as a result,
Beauty.
Shown in Figure 1, in the present embodiment, optionally, blade 20 has the central axes N- across the center of propeller hub 10
N, leading edge 25 have the leading edge tangent line O-O for being parallel to central axes N-N, and rear 26 has the rear tangent line for being parallel to central axes N-N
P-P, sweepback portion 221 are located between leading edge tangent line O-O and rear tangent line P-P.Sweepback portion 221 can not only reduce propeller as a result,
100 air drag improves the navigability of aircraft 1000, keeps aircraft 1000 more steady, additionally it is possible to reduce blade 20
The turbulent flow and downwash flow of generation, to reduce the turbulent flow and downwash flow got on the fuselage 50 of aircraft 1000, further
Reduce the whole noise of aircraft 1000.
Also referring to Fig. 1 and Figure 10, in present embodiment, blade tip 22 along blade 20 exhibition to towards where suction surface 24
Side inclination extends, and sweepback portion 221 tilts extension from leading edge 25 to rear 26.Specifically, it such as Figure 10, is built on propeller 100
Vertical right hand rectangular coordinate system O '-X ' Y ' Z ', the center of circle O ' of coordinate system are located at the center of propeller hub 10.Incorporated by reference to Figure 14, in blade
Establish right hand rectangular coordinate system O-XYZ in 20 aerofoil profile, the center of circle O of coordinate system is located at first aerofoil profile of blade 20, and (this first
A aerofoil profile be blade 20 design when virtual aerofoil profile) aerofoil profile rotation center at, the center of propeller hub 10 is located at first aerofoil profile institute
Plane, the X-axis of 20 aerofoil profile of blade is defined as: starting point be center of circle O, propeller 100 along blade 20 exhibition to for X-axis just
Direction；The Y-axis of 20 aerofoil profile of blade is defined as: starting point is center of circle O, and thumb is directed toward X-axis, the direction of index finger meaning for Y-axis just
Direction；The Z axis of 20 aerofoil profile of blade is defined as: starting point is center of circle O, and thumb is directed toward X-axis, and middle finger direction is the pros of Z axis
To.The acquisition modes of center of circle O (the aerofoil profile rotation center of first aerofoil profile) are as follows, also referring to Figure 10 and Figure 14, it is assumed that figure
14 be first aerofoil profile of blade 20, and X ' value of the plane in coordinate system O '-X ' Y ' Z ' is it is known that change speech where first aerofoil profile
It, X value of the center of circle O in coordinate system O '-X ' Y ' Z ' is it is known that i.e. X ' o is known；Plane is in coordinate system where first aerofoil profile
Maximum value Y ' max in O '-X ' Y ' Z ' subtracts minimum value Y ' min divided by 3, is then to justify plus the coordinate of minimum Y ' min value
Y ' value of the heart O in coordinate system O '-X ' Y ' Z ', that is, Y ' o=(Y ' max-Y ' min)/3+Y ' min；Plane where first aerofoil profile
Maximum value Z ' max in coordinate system O '-X ' Y ' Z ' subtracts minimum value Z ' min divided by 2, then adds the seat of minimum Z ' min value
Mark is Z ' value of the center of circle O in coordinate system O '-X ' Y ' Z ', that is, Z ' o=(Z ' max-Z ' min)/2+Z ' min；In this way, center of circle O
(X ' o, Y ' o, Z ' o) are determined, and can be established right hand right angle as the center of circle using O and be sat for position in coordinate system O '-X ' Y ' Z '
Mark system O-XYZ.After establishing right hand rectangular coordinate system O-XYZ, the rotation center of other subsequent aerofoil profiles can be according to this side
The corresponding coordinate in right hand rectangular coordinate system O-XYZ is calculated in method, and details are not described herein.
Incorporated by reference to table 2, Blade Radius (mm) column indicate the aerofoil profile rotation center of blade 20 in coordinate system O-XYZ
(wherein, center of circle O and center of circle O ' are located in same vertical plane, the aerofoil profile rotation center of each aerofoil profile and the center of circle for X axis coordinate position
The distance of O is identical at a distance from the center O ' of each aerofoil profile and propeller hub 10 respectively), thus the aerofoil profile rotation center of blade 20 namely
X ' coordinate positions in coordinate system O '-X ' Y ' Z ', section start are the aerofoil profile rotation of the virtual aerofoil profile at the center O ' of propeller hub 10
Center, the distance of the center O ' apart from propeller hub 10 is 0mm at this time.Terminal point is blade 20 farthest away from the one of 10 center O ' of propeller hub
At a aerofoil profile rotation center, the distance of the center O ' apart from propeller hub 10 is 110mm at this time.Anhedral Length (mm) list
Show Z axis coordinate position of the aerofoil profile rotation center of blade 20 in coordinate system O-XYZ, wherein Anhedral Length's (mm)
Positive value indicates anti-on blade 20, and negative value indicates that blade 20 is lower anti-.Sweep Length (mm) column indicate the aerofoil profile rotation of blade 20
Y axis coordinate position of the center in coordinate system O-XYZ, wherein the positive value of Sweep Length (mm) indicates 20 sweepforward of blade, bears
Value indicates 20 sweepback of blade.For example, for the distance of the center O ' apart from propeller hub 10 is the aerofoil profile of 5.5mm, aerofoil profile rotation
Turning center Z value in O-XYZ is 0, and Y value is also 0, indicates that the aerofoil profile is neither upper anti-, also not sweepback；For in propeller hub 10
The distance of heart O ' be 96.8mm aerofoil profile for, aerofoil profile rotation center in O-XYZ Z value be 0.000371mm, Y value be-
0.00122mm indicates anti-in the aerofoil profile, and sweepback.
Table 2
As shown in Table 2, when the distance of the center O ' in blade 20 apart from propeller hub 10 is 96.8mm, i.e., 27 be distance at back bending
The center of propeller hub 10 be propeller 100 radius 88% when, sweepback portion 221 since at back bending 27 from leading edge 25 to rear 26
Inclination extends, and in other words, starts sweepback when the distance of center O ' of the blade 20 apart from propeller hub 10 is 96.8mm.In multiple paddles
When leaf 20 works at the same time, due to sweepback portion 221 regularly since at back bending 27 from leading edge 25 to rear 26 tilt extend, energy
It is enough to reduce the turbulent flow and downwash flow got on the fuselage 50 of aircraft 1000, reduce the air drag that blade 20 is subject to, into one
Step improves the pulling force and efficiency of propeller 100, improves the navigability of aircraft 1000, keeps aircraft 1000 more flat
Surely, simultaneously, moreover it is possible to further decrease the noise generated due to the fuselage 50 of turbulent flow and downwash flow impact aircraft 1000.
It is also known by table 2, when the distance at center of the blade 20 apart from propeller hub 10 is 96.8mm, i.e., 27 apart from paddle at back bending
When the center O ' of hub 10 is the 88% of the radius of propeller 100, leading edge 25 since at back bending 27 along blade 20 exhibition to towards suction
Side where power face 24, which tilts, to be extended, in other words, when the distance of center O ' of the blade 20 apart from propeller hub 10 is 96.8mm
Start upper anti-.When multiple blades 20 work at the same time, since leading edge 25 regularly 27 is extended along blade 20 to court from back bending
Side where suction surface 24, which tilts, to be extended, and the turbulent flow since multiple blades 20 interact and generate and lower gas washing can be reduced
Stream, the lift point of specified blade 20 enable aircraft 1000 to correct flight attitude automatically, the inertia for increasing aircraft 1000 is steady
It is qualitative, it is more steady when making 1000 flight of aircraft, simultaneously, moreover it is possible to further decrease due to turbulent flow and downwash flow impact flight
The noise that the fuselage 50 of device 1000 generates.
In some embodiments, propeller 100 the center apart from propeller hub 10 be propeller 100 radius 36.4%
Locate D1, the angle of attack 1 of blade 20 is 19.35 ° ± 2.5 °；And/or
It is D6 at the 81.8% of the radius of propeller 100 at the center apart from propeller hub 10, the angle of attack 6 of blade 20 is
11.97°±2.5°；And/or
It is D7 at the 90.9% of the radius of propeller 100 at the center apart from propeller hub 10, the angle of attack 7 of blade 20 is 9.79 °
±2.5°；And/or
It is D8 at the 100% of the radius of propeller 100 at the center apart from propeller hub 10, the angle of attack 8 of blade 20 is 7.91 °
±2.5°；And/or
The D1 at the center 40mm apart from propeller hub 10, the angle of attack 1 of blade 20 are 19.35 °；And/or
The D2 at the center 50mm apart from propeller hub 10, the angle of attack 2 of blade 20 are 18.16 °；And/or
The D3 at the center 60mm apart from propeller hub 10, the angle of attack 3 of blade 20 are 16.80 °；And/or
The D4 at the center 70mm apart from propeller hub 10, the angle of attack 4 of blade 20 are 15.39 °；And/or
The D5 at the center 80mm apart from propeller hub 10, the angle of attack 5 of blade 20 are 13.78 °；And/or
The D6 at the center 90mm apart from propeller hub 10, the angle of attack 6 of blade 20 are 11.97 °；And/or
The D7 at the center 100mm apart from propeller hub 10, the angle of attack 7 of blade 20 are 9.79 °；And/or
The D8 at the center 110mm apart from propeller hub 10, the angle of attack 8 of blade 20 are 7.91 °.
Discussion herein includes but is not limited to following methods:
(1) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 36.4% at D1, blade 20
Angle of attack 1 is 19.35 ° ± 2.5 °；
(2) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 81.8% at D6, blade 20
Angle of attack 6 is 11.97 ° ± 2.5 °；
(3) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 90.9% at D7, blade 20
Angle of attack 7 is 9.79 ° ± 2.5 °；
(4) propeller 100 is D8 at the 100% of the radius of propeller 100 at the center apart from propeller hub 10, and blade 20 attacks
Angle α 8 is 7.91 ° ± 2.5 °；
(5) D1 at the center 40mm apart from propeller hub 10 of propeller 100, the angle of attack 1 of blade 20 are 19.35 °；
(6) D2 at the center 50mm apart from propeller hub 10 of propeller 100, the angle of attack 2 of blade 20 are 18.16 °；
(7) D3 at the center 60mm apart from propeller hub 10 of propeller 100, the angle of attack 3 of blade 20 are 16.80 °；
(8) D4 at the center 70mm apart from propeller hub 10 of propeller 100, the angle of attack 4 of blade 20 are 15.39 °；
(9) D5 at the center 80mm apart from propeller hub 10 of propeller 100, the angle of attack 5 of blade 20 are 13.78 °；
(10) D6 at the center 90mm apart from propeller hub 10 of propeller 100, the angle of attack 6 of blade 20 are 11.97 °；
(11) D7 at the center 100mm apart from propeller hub 10 of propeller 100, the angle of attack 7 of blade 20 are 9.79 °；
(12) D8 at the center 110mm apart from propeller hub 10 of propeller 100, the angle of attack 8 of blade 20 are 7.91 °；
(13) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 36.4% at D1, blade 20
Angle of attack 1 is 19.35 ° ± 2.5 °；And the center apart from propeller hub 10 be propeller 100 radius 81.8% at D6, blade
20 angle of attack 6 is 11.97 ° ± 2.5 °；And the center apart from propeller hub 10 be propeller 100 radius 90.9% at D7,
The angle of attack 7 of blade 20 is 9.79 ° ± 2.5 °；And the center apart from propeller hub 10 be propeller 100 radius 100% at
D8, the angle of attack 8 of blade 20 are 7.91 ° ± 2.5 °；And the D1 at the center 40mm apart from propeller hub 10, the angle of attack 1 of blade 20 are
19.35°；And the D2 at the center 50mm apart from propeller hub 10, the angle of attack 2 of blade 20 are 18.16 °；And apart from propeller hub 10
D3 at the 60mm of center, the angle of attack 3 of blade 20 are 16.80 °；And the D4 at the center 70mm apart from propeller hub 10, blade 20 are attacked
Angle α 4 is 15.39 °；And the D5 at the center 80mm apart from propeller hub 10, the angle of attack 5 of blade 20 are 13.78 °；And apart from paddle
D6 at the center 90mm of hub 10, the angle of attack 6 of blade 20 are 11.97 °；And the D7 at the center 100mm apart from propeller hub 10, blade
20 angle of attack 7 is 9.79 °；And the D8 at the center 110mm apart from propeller hub 10, the angle of attack 8 of blade 20 are 7.91 °.
In some embodiments, propeller 100 the center apart from propeller hub 10 be propeller 100 radius 45.5%
Locate D2, the chord length L2 of blade 20 is 23.80mm ± 5mm；And/or
It is D3 at the 54.5% of the radius of propeller 100 at the center apart from propeller hub 10, the chord length L3 of blade 20 is
21.85mm±5mm；And/or
It is D4 at the 63.6% of the radius of propeller 100 at the center apart from propeller hub 10, the chord length L4 of blade 20 is
19.92mm±5mm；And/or
It is D5 at the 72.7% of the radius of propeller 100 at the center apart from propeller hub 10, the chord length L5 of blade 20 is
17.98mm±5mm；And/or
The D2 at the center 50mm apart from propeller hub 10, the chord length L2 of blade 20 are 23.80mm；And/or
The D3 at the center 60mm apart from propeller hub 10, the chord length L3 of blade 20 are 21.85mm；And/or
The D4 at the center 70mm apart from propeller hub 10, the chord length L4 of blade 20 are 19.92mm；And/or
The D5 at the center 80mm apart from propeller hub 10, the chord length L5 of blade 20 are 17.98mm.
Discussion herein includes but is not limited to following methods:
(1) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 45.5% at D2, blade 20
Chord length L2 is 23.80mm ± 5mm；
(2) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 54.5% at D3, blade 20
Chord length L3 is 21.85mm ± 5mm；
(3) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 63.6% at D4, blade 20
Chord length L4 is 19.92mm ± 5mm；
(4) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 72.7% at D5, blade 20
Chord length L5 is 17.98mm ± 5mm；
(5) D2 at the center 50mm apart from propeller hub 10 of propeller 100, the chord length L2 of blade 20 are 23.80mm；
(6) D3 at the center 60mm apart from propeller hub 10 of propeller 100, the chord length L3 of blade 20 are 21.85mm；
(7) D4 at the center 70mm apart from propeller hub 10 of propeller 100, the chord length L4 of blade 20 are 19.92mm；
(8) D5 at the center 80mm apart from propeller hub 10 of propeller 100, the chord length L5 of blade 20 are 17.98mm；
(9) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 45.5% at D2, blade 20
Chord length L2 is 23.80mm ± 5mm；And the center apart from propeller hub 10 be propeller 100 radius 54.5% at D3, blade
20 chord length L3 is 21.85mm ± 5mm；And the center apart from propeller hub 10 be propeller 100 radius 63.6% at D4,
The chord length L4 of blade 20 is 19.92mm ± 5mm；And the center apart from propeller hub 10 be propeller 100 radius 72.7% at
D5, the chord length L5 of blade 20 are 17.98mm ± 5mm；And the D2 at the center 50mm apart from propeller hub 10, the chord length L2 of blade 20
For 23.80mm；And the D3 at the center 60mm apart from propeller hub 10, the chord length L3 of blade 20 are 21.85mm；And apart from propeller hub
D4 at 10 center 70mm, the chord length L4 of blade 20 are 19.92mm；And the D5 at the center 80mm apart from propeller hub 10, blade 20
Chord length L5 be 17.98mm.
In some embodiments, propeller 100 the center apart from propeller hub 10 be propeller 100 radius 36.4%
Locate D1, the chord length L1 of blade 20 is 25.72mm ± 5mm；And/or
It is D6 at the 81.8% of the radius of propeller 100 at the center apart from propeller hub 10, the chord length L6 of blade 20 is
16.03mm±5mm；And/or
It is D7 at the 90.9% of the radius of propeller 100 at the center apart from propeller hub 10, the chord length L7 of blade 20 is
12.90mm±5mm；And/or
It is D8 at the 100% of the radius of propeller 100 at the center apart from propeller hub 10, the chord length L8 of blade 20 is 4.42mm
±2mm；And/or
At the center 40mmD1 apart from propeller hub 10, the chord length L1 of blade 20 is 25.72mm；And/or
At the center 90mmD6 apart from propeller hub 10, the chord length L6 of blade 20 is 16.03mm；And/or
At the center 100mmD7 apart from propeller hub 10, the chord length L7 of blade 20 is 12.90mm；And/or
At the center 110mmD8 apart from propeller hub 10, the chord length L8 of blade 20 is 4.42mm.
Discussion herein includes but is not limited to following methods:
(1) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 36.4% at D1, blade 20
Chord length L1 is 25.72mm ± 5mm；
(2) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 81.8% at D6, blade 20
Chord length L6 is 16.03mm ± 5mm；
(3) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 90.9% at D7, blade 20
Chord length L7 is 12.90mm ± 5mm；
(4) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 100% at D8, the string of blade 20
Long L8 is 4.42mm ± 2mm；
(5) for propeller 100 at the center 40mmD1 apart from propeller hub 10, the chord length L1 of blade 20 is 25.72mm；
(6) for propeller 100 at the center 90mmD6 apart from propeller hub 10, the chord length L6 of blade 20 is 16.03mm；
(7) for propeller 100 at the center 100mmD7 apart from propeller hub 10, the chord length L7 of blade 20 is 12.90mm；
(8) for propeller 100 at the center 110mmD8 apart from propeller hub 10, the chord length L8 of blade 20 is 4.42mm；
(9) propeller 100 the center apart from propeller hub 10 be propeller 100 radius 36.4% at D1, blade 20
Chord length L1 is 25.72mm ± 5mm；And the center apart from propeller hub 10 be propeller 100 radius 81.8% at D6, blade
20 chord length L6 is 16.03mm ± 5mm；And the center apart from propeller hub 10 be propeller 100 radius 90.9% at D7,
The chord length L7 of blade 20 is 12.90mm ± 5mm；And the center apart from propeller hub 10 be propeller 100 radius 100% at
D8, the chord length L8 of blade 20 are 4.42mm ± 2mm；And at the center 40mmD1 apart from propeller hub 10, the chord length L1 of blade 20 is
25.72mm；And at the center 90mmD6 apart from propeller hub 10, the chord length L6 of blade 20 is 16.03mm；And apart from propeller hub 10
Center 100mmD7 at, the chord length L7 of blade 20 is 12.90mm；And at the center 110mmD8 apart from propeller hub 10, blade 20
Chord length L8 be 4.42mm.
In the present embodiment, optionally, the screw pitch of blade 20 is 5.10 ± 0.5 inches.Screw pitch in the present embodiment refers to spiral
Screw pitch at the 3/4 of the radius of paddle 100.The resistance of air can be reduced as a result, improve the pulling force of blade 20.Wherein, blade 20
Screw pitch can be 5.05 inches or 5.10 inches or 5.15 inches or 5.06 inches, 5.07 inches, 5.08 inches, 5.09
Inch, 5.11 inches, 5.12 inches, 5.13 inches, any one or above-mentioned any number between the two in 5.14 inches etc.
Value.
To sum up, using the blade 20 of aerofoil profile gradual change in the utility model above-described embodiment, propeller 100 can in highlands
To significantly improve pulling force, guarantee enough power redundancies.Meanwhile performance is taken into account to a certain extent, increase after boat distance, improves
The flying quality of aircraft 1000.Existing propeller 100 is compared on the market at present, using the propeller 100 of the blade 20
It has bigger pulling force under lesser power condition, so as to reduce kwh loss, increases endurance distance.It is reduced in density
High aititude region or the biggish extreme case of low altitude area take-off weight under, can significantly improve pulling force, guarantee foot
Enough power extends cruise duration simultaneously, improves flying quality.In addition, propeller 100 provided by the present embodiment can also effectively subtract
The noise that few fuselage 50 due to turbulent flow and downwash flow impact aircraft 1000 generates, mitigates the discomfort that noise causes human ear
Sense, improves user experience.
Referring to Figure 15, the utility model embodiment provides a kind of Power Component 200, including actuator 30 and this is practical new
The propeller 100 of type any embodiment, propeller 100 are connect by propeller hub 10 with actuator 30.Power Component 200 includes at least
Two horns 40.At least two horns 40 are connected to the center of propeller component 100.Actuator 30 is arranged in horn 40
On.Wherein, the specific structure of propeller 100 is identical as previous embodiment, and details are not described herein again.Embodiment and implementation i.e. as above
The description as described in propeller 100 is equally applicable to Power Component 200 provided by the embodiment of the utility model in mode.
In the Power Component 200 of the utility model, due to being the radius of propeller 100 at the center apart from propeller hub 10
D2 at 45.5%, the angle of attack 2 of blade 20 are 18.16 ° ± 2.5 °；It is the radius of propeller 100 at the center apart from propeller hub 10
D3 at 54.5%, the angle of attack 3 of blade 20 are 16.80 ° ± 2.5 °；It is the radius of propeller 100 at the center apart from propeller hub 10
D4 at 63.6%, the angle of attack 4 of blade 20 are 15.39 ° ± 2.5 °；It is the radius of propeller 100 at the center apart from propeller hub 10
D5 at 72.7%, the angle of attack 5 of blade 20 are 13.78 ° ± 2.5 °；Therefore, the paddle for having specific shape is limited by above-mentioned parameter
Leaf 20 can reduce air drag using the propeller 100 of blade 20, improve pulling force and efficiency, increase aircraft 1000
The flying quality of aircraft 1000 is improved after boat distance.
In the present embodiment, optionally, actuator 30 is motor, and the KV value of motor is 1040 ± 104 turns/(minute volt
It is special).Wherein, the KV value of motor can for 936 turns/(minute volt) or 1040 turns/(minute volt) or 1144 turns/(point
Clock volt) or 940 turns/(minute volt), 960 turns/(minute volt), 980 turns/(minute volt), 1000
Turn/(minute volt), 1020 turns/(minute volt), 1060 turns/(minute volt), 1100 turns/(minute volt),
1140 turns/(minute volt) etc. in any one or above-mentioned any numerical value between the two.Thereby, it is possible to guarantee power packages
The power performance of part 200.
Referring again to Figure 15, the utility model embodiment provides a kind of aircraft 1000, including fuselage 50 and this is practical
The Power Component 200 of novel any embodiment, Power Component 200 are connect with fuselage 50.Multiple horns 40 of Power Component 200 with
Fuselage 50 is connected so that Power Component 200 to be mounted on fuselage 50.The wherein specific structure and previous embodiment of Power Component 200
Similar, details are not described herein again.The description as described in propeller 100 is equally applicable to this reality in embodiment and embodiment i.e. as above
The aircraft 1000 provided with new embodiment.
In the present embodiment, optionally, aircraft 1000 includes multiple Power Components 200, the rotation of multiple Power Components 200
Direction is different.
In the present embodiment, optionally, aircraft 1000 is multi-rotor aerocraft, for example, quadrotor unmanned vehicle.
In the aircraft 1000 of the utility model, due to being the radius of propeller 100 at the center apart from propeller hub 10
D2 at 45.5%, the angle of attack 2 of blade 20 are 18.16 ° ± 2.5 °；It is the radius of propeller 100 at the center apart from propeller hub 10
D3 at 54.5%, the angle of attack 3 of blade 20 are 16.80 ° ± 2.5 °；It is the radius of propeller 100 at the center apart from propeller hub 10
D4 at 63.6%, the angle of attack 4 of blade 20 are 15.39 ° ± 2.5 °；It is the radius of propeller 100 at the center apart from propeller hub 10
D5 at 72.7%, the angle of attack 5 of blade 20 are 13.78 ° ± 2.5 °；Therefore, the paddle for having specific shape is limited by above-mentioned parameter
Leaf 20 can reduce air drag using the propeller 100 of blade 20, improve pulling force and efficiency, increase aircraft 1000
The flying quality of aircraft 1000 is improved after boat distance.
In the description of this specification, reference term " certain embodiments ", " embodiment ", " some embodiment party
The description of formula ", " exemplary embodiment ", " example ", " specific example " or " some examples " means in conjunction with the embodiment
Or example particular features, structures, materials, or characteristics described are contained at least one embodiment of the utility model or show
In example.In the present specification, schematic expression of the above terms are not necessarily referring to identical embodiment or example.And
And particular features, structures, materials, or characteristics described can be in any one or more embodiments or example to close
Suitable mode combines.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include at least one described feature.The meaning of " plurality " is at least two, such as two in the description of the present invention,
It is a, three, unless otherwise specifically defined.
Although the embodiments of the present invention have been shown and described above, it is to be understood that above-described embodiment is
Illustratively, it should not be understood as limiting the present invention, those skilled in the art are in the scope of the utility model
It inside can make changes, modifications, alterations, and variations to the above described embodiments, the scope of the utility model is by claim and its is equal
Object limits.
Claims (12)
1. a kind of propeller, comprising: propeller hub and blade, the blade are connected on the propeller hub, it is characterised in that:
At the center apart from the propeller hub it is at the 45.5% of the radius of the propeller that the angle of attack of the blade is 18.16 ° ±
2.5°；
At the center apart from the propeller hub it is at the 54.5% of the radius of the propeller that the angle of attack of the blade is 16.80 ° ±
2.5°；
At the center apart from the propeller hub it is at the 63.6% of the radius of the propeller that the angle of attack of the blade is 15.39 ° ±
2.5°；
At the center apart from the propeller hub it is at the 72.7% of the radius of the propeller that the angle of attack of the blade is 13.78 ° ±
2.5°。
2. propeller according to claim 1, it is characterised in that:
At the center apart from the propeller hub it is at the 36.4% of the radius of the propeller that the angle of attack of the blade is 19.35 ° ±
2.5°；And/or
At the center apart from the propeller hub it is at the 81.8% of the radius of the propeller that the angle of attack of the blade is 11.97 ° ±
2.5°；And/or
At the center apart from the propeller hub it is at the 90.9% of the radius of the propeller that the angle of attack of the blade is 9.79 ° ±
2.5°；And/or
At the center apart from the propeller hub it is at the 100% of the radius of the propeller that the angle of attack of the blade is 7.91 ° ±
2.5°；And/or
At the center 40mm apart from the propeller hub, the angle of attack of the blade is 19.35 °；And/or
At the center 50mm apart from the propeller hub, the angle of attack of the blade is 18.16 °；And/or
At the center 60mm apart from the propeller hub, the angle of attack of the blade is 16.80 °；And/or
At the center 70mm apart from the propeller hub, the angle of attack of the blade is 15.39 °；And/or
At the center 80mm apart from the propeller hub, the angle of attack of the blade is 13.78 °；And/or
At the center 90mm apart from the propeller hub, the angle of attack of the blade is 11.97 °；And/or
At the center 100mm apart from the propeller hub, the angle of attack of the blade is 9.79 °；And/or
At the center 110mm apart from the propeller hub, the angle of attack of the blade is 7.91 °.
3. propeller according to claim 1, it is characterised in that:
It is at the 45.5% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 23.80mm
±5mm；And/or
It is at the 54.5% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 21.85mm
±5mm；And/or
It is at the 63.6% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 19.92mm
±5mm；And/or
It is at the 72.7% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 17.98mm
±5mm；And/or
At the center 50mm apart from the propeller hub, the chord length of the blade is 23.80mm；And/or
At the center 60mm apart from the propeller hub, the chord length of the blade is 21.85mm；And/or
At the center 70mm apart from the propeller hub, the chord length of the blade is 19.92mm；And/or
At the center 80mm apart from the propeller hub, the chord length of the blade is 17.98mm.
4. propeller according to claim 3, it is characterised in that:
It is at the 36.4% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 25.72mm
±5mm；And/or
It is at the 81.8% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 16.03mm
±5mm；And/or
It is at the 90.9% of the radius of the propeller at the center apart from the propeller hub, the chord length of the blade is 12.90mm
±5mm；And/or
Be at the center apart from the propeller hub at the 100% of the radius of the propeller, the chord length of the blade be 4.42mm ±
2mm；And/or
At the center 40mm apart from the propeller hub, the chord length of the blade is 25.72mm；And/or
At the center 90mm apart from the propeller hub, the chord length of the blade is 16.03mm；And/or
At the center 100mm apart from the propeller hub, the chord length of the blade is 12.90mm；And/or
At the center 110mm apart from the propeller hub, the chord length of the blade is 4.42mm.
5. propeller according to claim 1, it is characterised in that:
The diameter of the propeller is 220mm ± 22mm；And/or
The screw pitch of the blade is 5.10 ± 0.5 inches.
6. according to claim 1 to propeller described in 5 any one, it is characterised in that:
The blade includes blade root, the blade tip away from the blade root, opposite pressure face and suction surface, is connected to the pressure face
And described suction surface a side leading edge, be connected to the rear of the pressure face and another side of the suction surface and be formed in
The sweepback portion of the blade tip, the sweepback portion tilt extension from the leading edge to the rear；
Side where suction surface described in Zhan Xiangchao of the blade tip along the blade, which tilts, to be extended.
7. propeller according to claim 6, it is characterised in that:
The blade close to the blade tip position formed back bending at, the leading edge since at the back bending along the blade
Zhan Xiangchao described in side where suction surface tilt and extend, the sweepback portion is from the back bending from the leading edge to after described
Edge inclination extends, and the center at the back bending apart from the propeller hub is the 88% of the radius of the propeller.
8. propeller according to claim 6, it is characterised in that:
The leading edge that the leading edge evagination is formed with the shape in curved surface close to the blade root arches upward portion, and the rear evagination, which is formed with, to be leaned on
The rear of the shape in curved surface of the nearly blade root arches upward portion；And/or
The blade is at least two, and the center that at least two blades are connected on the propeller hub and about the propeller hub is in
Central symmetry；And/or
The blade has across the central axes at the center of the propeller hub, and the leading edge has the leading edge for being parallel to the central axes
Tangent line, the rear, which has, is parallel to the rear tangent lines of the central axes, the sweepback portion be located at the leading edge tangent line with it is described
Between rear tangent line；And/or
The suction surface and the pressure face are curved surface；And/or
The side of the free end of the blade tip is plane.
9. a kind of Power Component, including actuator and propeller of any of claims 1-8, which is characterized in that institute
Propeller is stated to connect by the propeller hub with the actuator.
10. Power Component according to claim 9, which is characterized in that the actuator is motor, the KV value of the motor
For 1040 ± 104 turns/(minute volt).
11. a kind of aircraft, which is characterized in that including Power Component described in fuselage and claim 9 or 10, the power packages
Part is connect with the fuselage.
12. aircraft according to claim 11, which is characterized in that the aircraft includes multiple Power Components, described
The rotation direction of multiple Power Components is different, and the aircraft is multi-rotor aerocraft.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820798000.4U CN208291465U (en) | 2018-05-25 | 2018-05-25 | Propeller, Power Component and aircraft |
| PCT/CN2018/105982 WO2019223193A1 (en) | 2018-05-25 | 2018-09-17 | Propeller, power assembly and air vehicle |
| CN201880016150.8A CN110896624A (en) | 2018-05-25 | 2018-09-17 | Screw, power component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820798000.4U CN208291465U (en) | 2018-05-25 | 2018-05-25 | Propeller, Power Component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208291465U true CN208291465U (en) | 2018-12-28 |
Family
ID=64727221
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820798000.4U Active CN208291465U (en) | 2018-05-25 | 2018-05-25 | Propeller, Power Component and aircraft |
| CN201880016150.8A Pending CN110896624A (en) | 2018-05-25 | 2018-09-17 | Screw, power component and aircraft |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201880016150.8A Pending CN110896624A (en) | 2018-05-25 | 2018-09-17 | Screw, power component and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN208291465U (en) |
| WO (1) | WO2019223193A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111056036A (en) * | 2019-12-27 | 2020-04-24 | 北京电子工程总体研究所 | Rapid iteration generation method for high-altitude propeller |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN212738487U (en) * | 2020-04-17 | 2021-03-19 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN213323651U (en) * | 2020-04-21 | 2021-06-01 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9140126B2 (en) * | 2011-07-26 | 2015-09-22 | Anthony V. Hins | Propeller with reactionary and vacuum faces |
| CN102963522B (en) * | 2012-10-31 | 2015-04-22 | 中国航天空气动力技术研究院 | Near space propeller |
| CN205366054U (en) * | 2016-01-28 | 2016-07-06 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205554565U (en) * | 2016-02-29 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN206243477U (en) * | 2016-11-10 | 2017-06-13 | 中强光电股份有限公司 | Aircraft and its rotor |
| CN206155775U (en) * | 2016-11-11 | 2017-05-10 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN206297727U (en) * | 2016-12-01 | 2017-07-04 | 重庆零度智控智能科技有限公司 | Propeller, Power Component and aircraft |
| CN206954494U (en) * | 2017-06-30 | 2018-02-02 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN206926806U (en) * | 2017-07-25 | 2018-01-26 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN207045700U (en) * | 2017-07-28 | 2018-02-27 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and unmanned plane for unmanned plane |
| CN207072430U (en) * | 2017-07-28 | 2018-03-06 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN208291465U (en) * | 2018-05-25 | 2018-12-28 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
-
2018
- 2018-05-25 CN CN201820798000.4U patent/CN208291465U/en active Active
- 2018-09-17 WO PCT/CN2018/105982 patent/WO2019223193A1/en active Application Filing
- 2018-09-17 CN CN201880016150.8A patent/CN110896624A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111056036A (en) * | 2019-12-27 | 2020-04-24 | 北京电子工程总体研究所 | Rapid iteration generation method for high-altitude propeller |
| CN111056036B (en) * | 2019-12-27 | 2021-08-13 | 北京电子工程总体研究所 | Rapid iteration generation method for high-altitude propeller |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110896624A (en) | 2020-03-20 |
| WO2019223193A1 (en) | 2019-11-28 |
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