CN207403925U - Propeller, Power Component and aircraft - Google Patents
Propeller, Power Component and aircraft Download PDFInfo
- Publication number
- CN207403925U CN207403925U CN201721008876.6U CN201721008876U CN207403925U CN 207403925 U CN207403925 U CN 207403925U CN 201721008876 U CN201721008876 U CN 201721008876U CN 207403925 U CN207403925 U CN 207403925U
- Authority
- CN
- China
- Prior art keywords
- blade
- propeller
- center
- attack
- apart
- 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
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
The utility model discloses a kind of propeller, Power Component and aircraft.Wherein, propeller includes propeller hub and blade, and the blade is connected on the propeller hub.At apart from the center of the propeller hub for the 40% of the radius of the propeller, the angle of attack of the blade is 20.37 ° ± 2.5 °, and the chord length of the blade is 16.95mm ± 5mm.At apart from the center of the propeller hub for the 60% of the radius of the propeller, the angle of attack of the blade is 14.79 ° ± 2.5 °, and the chord length of the blade is 13.1mm ± 5mm.At apart from the center of the propeller hub for the 80% of the radius of the propeller, the angle of attack of the blade is 9.44 ° ± 2.5 °, and the chord length of the blade is 9.3mm ± 5mm.The utility model can optimize the structure of propeller, improve the flying quality of aircraft.
Description
Technical field
The utility model is related to aircraft fields, more particularly to propeller, Power Component and aircraft.
Background technology
Carry-on propeller as the important Primary Component of aircraft, is used for shaft in motor or engine
Rotation be converted into thrust or lift.
Propeller of the prior art, outer shape is mostly rectangular, and resistance is big, efficiency is low, causes aircraft
Flying speed is small, after boat apart from short, seriously affected the flying quality of aircraft.
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：Propeller hub and blade, the blade are connected on the propeller hub,
It is at the 40% of the radius of the propeller apart from the center of the propeller hub, the angle of attack of the blade is 20.37 ° ± 2.5 °, institute
The chord length for stating blade is 16.95mm ± 5mm.At apart from the center of the propeller hub for the 60% of the radius of the propeller, institute
The angle of attack of blade is stated as 14.79 ° ± 2.5 °, the chord length of the blade is 13.1mm ± 5mm.It is being apart from the center of the propeller hub
At the 80% of the radius of the propeller, the angle of attack of the blade is 9.44 ° ± 2.5 °, the chord length of the blade for 9.3mm ±
5mm。
In some embodiments, a diameter of 136mm ± 13.6mm of the propeller.Apart from the center of the propeller hub
At 27.2mm, the angle of attack of the blade is 20.37 °, and the chord length of the blade is 16.95mm.Apart from the center of the propeller hub
At 40.8mm, the angle of attack of the blade is 14.79 °, and the chord length of the blade is 13.1mm.Apart from the center of the propeller hub
At 54.4mm, the angle of attack of the blade is 9.44 °, and the chord length of the blade is 9.3mm.
In some embodiments, it is described at apart from the center of the propeller hub for the 20% of the radius of the propeller
The angle of attack of blade is 20.06 ° ± 2.5 °, and the chord length of the blade is 15mm ± 5mm.
In some embodiments, a diameter of 136mm ± 13.6mm of the propeller.Apart from the center of the propeller hub
At 13.6mm, the angle of attack of the blade is 20.06 °, and the chord length of the blade is 15mm.
In some embodiments, it is described at apart from the center of the propeller hub for the 100% of the radius of the propeller
The angle of attack of blade is 4.42 ° ± 2.5 °, and the chord length of the blade is 7.25mm ± 5mm.
In some embodiments, a diameter of 136mm ± 13.6mm of the propeller.Apart from the center of the propeller hub
At 68mm, the angle of attack of the blade is 4.42 °, and the chord length of the blade is 7.25mm.
In some embodiments, the blade includes blade face directed downwardly, blade back upward, is connected to the blade back and institute
It states the first lateral margin of blade face one side and is connected to the second lateral margin of the blade back and the blade face opposite side.The blade face and
The cross section of the blade back is curved, and first lateral margin is located at below second lateral margin.
In some embodiments, the first lateral margin evagination of the blade is formed with protrusion.
In some embodiments, the blade includes the connecting pin being connected with the propeller hub and away from the end of the propeller hub
End, the thickness of the blade are gradually reduced by the connecting pin to the end.
In some embodiments, the protruding parts in the blade at the connecting pin.
In some embodiments, the blade is at least two, and at least two blade is in the propeller hub
The heart is centrosymmetric.
In some embodiments, the screw pitch of the blade is 34mm.
Spiral shell of the Power Component of the utility model embodiment described in including actuator and above-mentioned any one embodiment
Revolve paddle, which is characterized in that the propeller is connected by the propeller hub with the actuator.
In some embodiments, the actuator is motor, and the KV values of the motor are 2300 ± 100 turns/(minute
Volt).
Power packages of the aircraft of the utility model embodiment described in including fuselage and above-mentioned any one embodiment
Part, the Power Component are connected 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.
Propeller, Power Component and the aircraft that the utility model embodiment provides, due in the propeller hub
The heart is at the 40% of the radius of propeller, and the angle of attack of blade is 20.37 ° ± 2.5 °, and the chord length of blade is 16.95mm ± 5mm.
It is at the 60% of the radius of propeller apart from the center of propeller hub, the angle of attack of blade is 14.79 ° ± 2.5 °, and the chord length of blade is
13.1mm±5mm.At apart from the center of propeller hub for the 80% of the radius of propeller, the angle of attack of blade is 9.44 ° ± 2.5 °, paddle
The chord length of leaf is 9.3mm ± 5mm.The blade for possessing given shape is limited by above-mentioned parameter, using the propeller energy of the blade
Enough reduce air drag, improve pulling force and efficiency, add aircraft after boat distance and improve the flying quality of aircraft.
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
The practice for becoming embodiment that is apparent or passing through the utility model in following description is recognized.
Description of the drawings
In description of the above-mentioned and/or additional aspect and advantage of the utility model from combination accompanying drawings below to embodiment
It will be apparent and be readily appreciated that, wherein：Illustrating in newly-increased attached drawing modification, specification
Fig. 1 is a kind of floor map for propeller that the utility model embodiment provides.
Fig. 2 be embodiment illustrated in fig. 1 propeller in B-B sections at propeller hub center 27.2mm sectional view.
Fig. 3 be embodiment illustrated in fig. 1 propeller in C-C sections at center 40.8mm apart from propeller hub sectional view.
Fig. 4 be embodiment illustrated in fig. 1 propeller in D-D sections at center 54.4mm apart from propeller hub sectional view.
Fig. 5 be embodiment illustrated in fig. 1 propeller in A-A sections at center 13.6mm apart from propeller hub sectional view.
Fig. 6 be embodiment illustrated in fig. 1 propeller in E-E sections at center 68mm apart from propeller hub sectional view.
Fig. 7 is a kind of stereogram for propeller that the utility model embodiment provides.
Fig. 8 is a kind of floor map for propeller that the utility model embodiment provides.
Fig. 9 is a kind of floor map for propeller that the utility model embodiment provides.
Figure 10 is a kind of stereogram for propeller that the utility model embodiment provides.
Specific embodiment
Here exemplary embodiment will be illustrated in detail, example is illustrated in the accompanying drawings.Following description is related to
During attached drawing, unless otherwise indicated, the same numbers in different attached drawings represent the same or similar element.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 apparatus and method of some aspects be described in detail in the appended claims, the utility model.
It is only merely for the purpose of description specific embodiment in the term that the utility model uses, and is not intended to be limiting this reality
With new.In " one kind " 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 any or all may be combined comprising one or more associated list items purposes.
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 departing 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 linguistic context, word as used in this " if " can be construed to " ... when " or
" when ... " or " in response to determining ".
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 afterbody is seen to motor head direction, rotates 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 structure of the positive paddle and the knot of 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, Power Component and aircraft of the utility model are described in detail.It is not rushing
In the case of prominent, the feature in following embodiment and embodiment can be mutually combined.
Referring to shown in Fig. 1 to Fig. 4, the utility model embodiment provides a kind of propeller 100, and propeller 100 includes propeller hub
10 and blade 20.
Blade 20 is connected on propeller hub 10.Certainly, blade 20 can be integrally formed with propeller hub 10, can also respectively be processed again
It is fixedly mounted integral.The D4 at apart from the center of propeller hub 10 for the 40% of the radius of propeller 100, the angle of attack 1 of blade 20 are
20.37 ° ± 2.5 °, the chord length L1 of blade 20 is 16.95mm ± 5mm.It is being the radius of propeller 100 apart from the center of propeller hub 10
60% at D3, the angle of attack 2 of blade 20 is 14.79 ° ± 2.5 °, and the chord length L2 of blade 20 is 13.1mm ± 5mm.Apart from paddle
The center of hub 10 is D2 at the 80% of the radius of propeller 100, and the angle of attack 3 of blade 20 is 9.44 ° ± 2.5 °, the string of blade 20
Long L3 is 9.3mm ± 5mm.
In the present embodiment, due to apart from the center of propeller hub 10 for propeller 100 radius 40% at D4, blade 20
Angle of attack 1 is 20.37 ° ± 2.5 °, and the chord length L1 of blade 20 is 16.95mm ± 5mm；It is being propeller apart from the center of propeller hub 10
D3 at the 60% of 100 radius, the angle of attack 2 of blade 20 is 14.79 ° ± 2.5 °, and the chord length L2 of blade 20 is 13.1mm ± 5mm；
The D2 at apart from the center of propeller hub 10 for the 80% of the radius of propeller 100, the angle of attack 3 of blade 20 is 9.44 ° ± 2.5 °, paddle
The chord length L3 of leaf 20 is 9.3mm ± 5mm；Therefore, the blade for possessing given shape is limited by above-mentioned parameter, using the blade
Propeller 100 can reduce air drag, improve pulling force and efficiency, add aircraft after boat distance and improve aircraft
Flying quality.
Table 1 is referred to, the propeller 100 that the present embodiment is provided and the comparison of the test result of existing propeller, by
Can be seen that in table, under identical pulling force, the power for the propeller 100 that the present embodiment is provided it is lower namely：In smaller work(
Under the conditions of rate, there is the pulling force of bigger, so as to reduce kwh loss, increase endurance distance.Spiral provided in this embodiment as a result,
It, can be notable under the larger extreme case in High aititude region or low altitude area take-off weight that paddle 100 is reduced in density
Pulling force is improved, ensures that enough power extends cruising time simultaneously, improves flying quality.
Table 1
Wherein, the D4 at apart from the center of propeller hub 10 for the 40% of the radius of propeller 100, the angle of attack 1 of blade 20 can be with
For 17.87 ° or 20.37 ° or 22.87 ° or 18.37 °, 18.87 °, 19.37 °, 19.87 °, 20.87 °, 21.37 °,
Any one in 21.87 °, 22.37 ° etc. or above-mentioned any value arbitrarily therebetween, the chord length L1 of blade 20 can be
11.95mm or 16.95mm or 21.95mm or 12.95mm, 13.95mm, 14.95mm, 15.95mm, 17.95mm,
Any one in 18.95mm, 19.95mm, 20.95mm etc. or above-mentioned arbitrary numerical value therebetween.Apart from propeller hub 10
Center is D3 at the 60% of the radius of propeller 100, the angle of attack 2 of blade 20 can be 12.29 ° or 14.79 ° or 17.29 ° or
Person be in 12.79 °, 13.29 °, 13.79 °, 14.29 °, 15.29 °, 15.79 °, 16.29 °, 16.79 ° etc. any one or on
State arbitrary numerical value therebetween, the chord length L2 of blade 20 can be 8.1mm or 13.1mm or 18.1mm or 9.1mm,
Any one in 10.1mm, 11.1mm, 12.1mm, 14.1mm, 15.1mm, 16.1mm, 17.1mm etc. or above-mentioned arbitrary the two
Between numerical value.The D2 at apart from the center of propeller hub 10 for the 80% of the radius of propeller 100, the angle of attack 3 of blade 20 can be
6.94 ° or 9.44 ° or 11.94 ° or 7.44 °, 7.94 °, 8.44 °, 8.94 °, 9.94 °, 10.44 °, 10.94 °, 11.44 °
Any one in or above-mentioned arbitrary numerical value therebetween, the chord length L3 of blade 20 can be 4.3mm or 9.3mm or
It is any one in 14.3mm or 5.3mm, 6.3mm, 7.3mm, 8.3mm, 10.3mm, 11.3mm, 12.3mm, 13.3mm etc.
A or above-mentioned arbitrary numerical value therebetween.
Wherein, propeller hub 10 can be that cylindric or propeller hub 10 section can be the shapes such as ellipse, diamond shape.Propeller hub 10
Center is equipped with connecting hole, and connecting hole is used to be set in the output terminal of motor.Blade 20 can be in strip, blade 20 and propeller hub
10 connections, and radially extending along propeller hub 10.The angle of attack refers to the angle between the wing chord and speed of incoming flow of blade 20, and chord length refers to
The length of 20 cross section of blade.
It is shown in Figure 5, it is being the radius of propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment
D5 at 20%, the angle of attack 4 of blade 20 is 20.06 ° ± 2.5 °, and the chord length L4 of blade 20 is 15mm ± 5mm, to be further reduced
The air drag of propeller 100 improves pulling force and efficiency.Wherein, the angle of attack 4 of blade 20 can be 17.56 ° or 20.06 ° or
Appointing in 22.56 ° or 18.06 °, 18.56 °, 19.06 °, 19.56 °, 20.56 °, 21.06 °, 21.56 °, 22.06 ° etc.
Meaning one or above-mentioned arbitrary numerical value therebetween, the chord length L4 of blade 20 can be 10mm or 15mm or 20mm, either
Any one in 11mm, 12mm, 13mm, 14mm, 16mm, 17mm, 18mm, 19mm etc. or above-mentioned arbitrary number therebetween
Value.
It is shown in Figure 6, it is being the radius of propeller 100 apart from the center of propeller hub 10 optionally in the present embodiment
D1 at 100%, the angle of attack 5 of blade 20 is 4.42 ° ± 2.5 °, and the chord length L5 of blade 20 is 7.25mm ± 5mm.Further to subtract
The air drag of few propeller 100, improves pulling force and efficiency.Wherein, the angle of attack 5 of blade 20 can be 1.92 ° or 4.42 ° or
In 6.92 ° or 2.42 °, 2.92 °, 3.42 °, 3.92 °, 4.92 °, 5.42 °, 5.92 °, 6.42 ° etc. any one or on
Arbitrary numerical value therebetween is stated, the chord length L5 of blade 20 can be 2.25mm or 7.25mm or 12.25mm, either
In 3.25mm, 4.25mm, 5.25mm, 6.25mm, 8.25mm, 9.25mm, 10.25mm, 11.25mm etc. any one or it is above-mentioned
Arbitrarily therebetween numerical value.
Referring again to shown in Fig. 1 to Fig. 4, in the present embodiment, optionally, a diameter of 136mm of propeller 100 ±
13.6mm.The D4 at the center 27.2mm apart from propeller hub 10, the angle of attack 1 of blade 20 is 20.37 °, and the chord length L1 of blade 20 is
16.95mm.The D3 at the center 40.8mm apart from propeller hub 10, the angle of attack 2 of blade 20 is 14.79 °, and the chord length L2 of blade 20 is
13.1mm.The D2 at the center 54.4mm apart from propeller hub 10, the angle of attack 3 of blade 20 is 9.44 °, and the chord length L3 of blade 20 is
9.3mm.The air drag of propeller 100 can be further reduced as a result, improve pulling force and efficiency.Wherein, propeller 100 is straight
Footpath can be 122.4mm or 136mm or 149.6mm or 122.5mm, 125mm, 130mm, 135mm, 140mm, 145mm,
Any one in 149mm etc. or above-mentioned arbitrary numerical value therebetween.
Referring again to shown in Fig. 5, in the present embodiment, optionally, a diameter of 136mm ± 13.6mm of propeller 100.
D5 at center 13.6mm apart from propeller hub 10, the angle of attack 4 of blade 20 is 20.06 °, and the chord length L4 of blade 20 is 15mm.As a result,
The air drag of propeller 100 can be further reduced, improves pulling force and efficiency.Wherein, the diameter of propeller 100 can be
In 122.4mm or 136mm or 149.6mm or 122.5mm, 125mm, 130mm, 135mm, 140mm, 145mm, 149mm etc.
Any one or above-mentioned arbitrary numerical value therebetween.
Referring again to shown in Fig. 6, in the present embodiment, optionally, a diameter of 136mm ± 13.6mm of propeller 100.Away from
D1 at center 68mm from propeller hub 10, the angle of attack 5 of blade 20 is 4.42 °, and the chord length L5 of blade 20 is 7.25mm.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 be 122.4mm
It is or arbitrary in 136mm or 149.6mm or 122.5mm, 125mm, 130mm, 135mm, 140mm, 145mm, 149mm etc.
One or above-mentioned arbitrary numerical value therebetween.
It refers to shown in Fig. 6 to Fig. 9, in the present embodiment, optionally, blade 20 includes blade face 21 directed downwardly, leaf upward
The back of the body 22 is connected to the first edge 23 of 21 one side of blade back 22 and blade face and is connected to the of 21 opposite side of blade back 22 and blade face
Two edges 24.Blade face 21 and the cross section of blade back 22 are curved, and first edge 23 is located at 24 lower section of second edge.Due to leaf
Face 21 and the cross section of blade back 22 are curved, and first edge 23 is located at 24 lower section of second edge, therefore can reduce air
Resistance improves the pulling force of blade 20.
Refer to Figure 10, in the present embodiment, optionally, blade 20 includes the connecting pin being connected with propeller hub 10 and away from propeller hub
10 end, the thickness of blade 20 are gradually reduced by connecting pin to end.Due to, without drastically torsion part, being answered on blade 20
Power is more uniform, avoids the occurrence of that the stress of respective location is excessive, and structural strength is higher, is not easily broken, so as to improve propeller 100
Functional reliability.In addition, end of the blade 20 away from propeller hub 10 is the most thin part of blade 20, be conducive to reduce air resistance
Power.
In the present embodiment, optionally, 23 evagination of first edge of blade 20 is formed with protrusion 231.It thus can be further
Improve the pulling force of blade 20.Wherein, protrusion 231 can be located at blade 20 at connecting pin, and blade is further improved to play
The effect of 20 pulling force.
In the present embodiment, optionally, blade 20 is at least two, during at least two blades 20 are on the center of propeller hub 10
The heart is symmetrical.The balance of propeller 100 can be improved as a result,.
In the present embodiment, optionally, the screw pitch of blade 20 is 34mm.The resistance of air can be reduced as a result, improve blade 20
Pulling force.
To sum up, can be significantly improved in highlands using the propeller 100 of the blade of the utility model above-described embodiment
Pulling force ensures enough power redundancies.Meanwhile performance is taken into account to a certain extent, increase after boat distance, improve flying for aircraft
Row performance.Existing propeller 100 is compared on the market at present, using the propeller 100 of the blade in smaller power condition
Its lower pulling force with bigger so as to reduce kwh loss, increases endurance distance.Density reduce High aititude region or
Under the larger extreme case of low altitude area take-off weight, pulling force can be significantly improved, ensure enough power while is extended continuous
ETS estimated time of sailing improves flying quality.
Due to mirror symmetry between the structure of anti-paddle and the structure of positive paddle, the structure of anti-paddle is repeated no more.
The utility model embodiment provides a kind of Power Component, the spiral shell including actuator and the utility model any embodiment
Paddle 100 is revolved, propeller 100 is connected by propeller hub 10 with actuator.Wherein, the concrete structure and previous embodiment of propeller 100
Similar, details are not described herein again.I.e. the description as described in propeller 100 is equally applicable to this reality in embodiment above and embodiment
The Power Component provided with new embodiment.
In the present embodiment, due to apart from the center of propeller hub 10 for propeller 100 radius 40% at D4, blade 20
Angle of attack 1 is 20.37 ° ± 2.5 °, and the chord length L1 of blade 20 is 16.95mm ± 5mm.It is being propeller apart from the center of propeller hub 10
D3 at the 60% of 100 radius, the angle of attack 2 of blade 20 is 14.79 ° ± 2.5 °, and the chord length L2 of blade 20 is 13.1mm ± 5mm.
The D2 at apart from the center of propeller hub 10 for the 80% of the radius of propeller 100, the angle of attack 3 of blade 20 is 9.44 ° ± 2.5 °, paddle
The chord length L3 of leaf 20 is 9.3mm ± 5mm, therefore, the blade for possessing given shape is limited by above-mentioned parameter, using the blade
Propeller 100 can reduce air drag, improve pulling force and efficiency, add aircraft after boat distance and improve aircraft
Flying quality.
In the present embodiment, optionally, the KV values of motor for 2300 ± 100 turns/(minute volt).Thereby, it is possible to ensure
The power performance of Power Component.
The utility model embodiment provides a kind of aircraft, the power packages including fuselage and the utility model any embodiment
Part, Power Component are connected with fuselage.The concrete structure of wherein Power Component is similar with previous embodiment, and details are not described herein again.I.e.
The description as described in propeller 100 is equally applicable to flying for the utility model embodiment offer in embodiment above and embodiment
Row device.
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 present embodiment, due to apart from the center of propeller hub 10 for propeller 100 radius 40% at D4, blade 20
Angle of attack 1 is 20.37 ° ± 2.5 °, and the chord length L1 of blade 20 is 16.95mm ± 5mm.It is being propeller apart from the center of propeller hub 10
D3 at the 60% of 100 radius, the angle of attack 2 of blade 20 is 14.79 ° ± 2.5 °, and the chord length L2 of blade 20 is 13.1mm ± 5mm.
The D2 at apart from the center of propeller hub 10 for the 80% of the radius of propeller 100, the angle of attack 3 of blade 20 is 9.44 ° ± 2.5 °, paddle
The chord length L3 of leaf 20 is 9.3mm ± 5mm, therefore, the blade for possessing given shape is limited by above-mentioned parameter, using the blade
Propeller 100 can reduce air drag, improve pulling force and efficiency, add aircraft after boat distance and improve aircraft
Flying quality.
The above is only the preferred embodiment of the present utility model, and limit in any form is not done 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 technical solutions of the utility model are not departed from, 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 that foundation the technical essence of the utility model makees above example, still
Belong in the range of technical solutions of the utility model.
This patent document disclosure includes material protected by copyright.The copyright owns for copyright holder.Copyright
Owner does not oppose that anyone replicates the patent document in the presence of the proce's-verbal of Patent＆Trademark Office and archives or should
Patent discloses.
Claims (17)
1. a kind of propeller, including：Propeller hub and blade, the blade are connected on the propeller hub, it is characterised in that：
At apart from the center of the propeller hub for the 40% of the radius of the propeller, the angle of attack of the blade for 20.37 ° ±
2.5 °, the chord length of the blade is 16.95mm ± 5mm；
At apart from the center of the propeller hub for the 60% of the radius of the propeller, the angle of attack of the blade for 14.79 ° ±
2.5 °, the chord length of the blade is 13.1mm ± 5mm；
At apart from the center of the propeller hub for the 80% of the radius of the propeller, the angle of attack of the blade for 9.44 ° ±
2.5 °, the chord length of the blade is 9.3mm ± 5mm.
2. propeller according to claim 1, it is characterised in that：
A diameter of 136mm ± 13.6mm of the propeller；
At the center 27.2mm apart from the propeller hub, the angle of attack of the blade is 20.37 °, and the chord length of the blade is
16.95mm；
At the center 40.8mm apart from the propeller hub, the angle of attack of the blade is 14.79 °, and the chord length of the blade is
13.1mm；
At the center 54.4mm apart from the propeller hub, the angle of attack of the blade is 9.44 °, and the chord length of the blade is 9.3mm.
3. propeller according to claim 1, which is characterized in that be the propeller apart from the center of the propeller hub
At the 20% of radius, the angle of attack of the blade is 20.06 ° ± 2.5 °, and the chord length of the blade is 15mm ± 5mm.
4. propeller according to claim 3, it is characterised in that：
A diameter of 136mm ± 13.6mm of the propeller；
At the center 13.6mm apart from the propeller hub, the angle of attack of the blade is 20.06 °, and the chord length of the blade is 15mm.
5. propeller according to claim 1, which is characterized in that be the propeller apart from the center of the propeller hub
At the 100% of radius, the angle of attack of the blade is 4.42 ° ± 2.5 °, and the chord length of the blade is 7.25mm ± 5mm.
6. propeller according to claim 5, it is characterised in that：
A diameter of 136mm ± 13.6mm of the propeller；
At the center 68mm apart from the propeller hub, the angle of attack of the blade is 4.42 °, and the chord length of the blade is 7.25mm.
7. according to any propeller in claim 1-6, it is characterised in that：
The blade includes blade face directed downwardly, blade back upward, the first lateral margin for being connected to the blade back and the blade face one side,
And it is connected to the second lateral margin of the blade back and the blade face opposite side；
The blade face and the cross section of the blade back are curved, and first lateral margin is located at below second lateral margin.
8. propeller according to claim 7, which is characterized in that the first lateral margin evagination of the blade is formed with protrusion
Portion.
9. propeller according to claim 8, which is characterized in that the blade includes the connecting pin being connected with the propeller hub
It is gradually reduced with the thickness away from the end of the propeller hub, the blade by the connecting pin to the end.
10. propeller according to claim 9, which is characterized in that the protruding parts is in the blade close to the company
It connects at end.
11. according to the propeller any one of claim 1-6, which is characterized in that the blade is at least two, described
At least two blades are centrosymmetric on the center of the propeller hub.
12. according to the propeller any one of claim 1-6, which is characterized in that the screw pitch of the blade is 34mm.
13. a kind of Power Component, including the propeller any one of actuator and claim 1-12, which is characterized in that
The propeller is connected by the propeller hub with the actuator.
14. Power Component according to claim 13, which is characterized in that the actuator be motor, the KV of the motor
Be worth for 2300 ± 100 turns/(minute volt).
15. a kind of aircraft, which is characterized in that including the Power Component described in fuselage and claim 13 or 14, the power
Component is connected with the fuselage.
16. aircraft according to claim 15, which is characterized in that the aircraft includes multiple Power Components, described
The rotation direction of multiple Power Components is different.
17. aircraft according to claim 15, which is characterized in that the aircraft is multi-rotor aerocraft.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721008876.6U CN207403925U (en) | 2017-08-11 | 2017-08-11 | Propeller, Power Component and aircraft |
| PCT/CN2017/108494 WO2019029026A1 (en) | 2017-08-11 | 2017-10-31 | Propeller, power assembly, and aircraft |
| CN201780072033.9A CN109996723A (en) | 2017-08-11 | 2017-10-31 | Propeller, Power Component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721008876.6U CN207403925U (en) | 2017-08-11 | 2017-08-11 | Propeller, Power Component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207403925U true CN207403925U (en) | 2018-05-25 |
Family
ID=62322955
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721008876.6U Expired - Fee Related CN207403925U (en) | 2017-08-11 | 2017-08-11 | Propeller, Power Component and aircraft |
| CN201780072033.9A Pending CN109996723A (en) | 2017-08-11 | 2017-10-31 | Propeller, Power Component and aircraft |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780072033.9A Pending CN109996723A (en) | 2017-08-11 | 2017-10-31 | Propeller, Power Component and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN207403925U (en) |
| WO (1) | WO2019029026A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109178295A (en) * | 2018-10-24 | 2019-01-11 | 深圳市飞米机器人科技有限公司 | Blade, propeller and aircraft |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7600976B2 (en) * | 2005-05-31 | 2009-10-13 | Sikorsky Aircraft Corporation | Rotor blade twist distribution for a high speed rotary-wing aircraft |
| EP2253835A1 (en) * | 2009-05-18 | 2010-11-24 | Lm Glasfiber A/S | Wind turbine blade with base part having non-positive camber |
| JP5995200B2 (en) * | 2012-03-09 | 2016-09-21 | 国立研究開発法人宇宙航空研究開発機構 | Variable pitch propeller |
| JP6167051B2 (en) * | 2014-02-21 | 2017-07-19 | 三菱重工業株式会社 | Wind turbine blade, wind turbine rotor and wind power generator |
| CN105253295A (en) * | 2015-10-30 | 2016-01-20 | 深圳市道通智能航空技术有限公司 | Screw propeller and aerocraft |
| 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 |
| CN205469778U (en) * | 2016-02-29 | 2016-08-17 | 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 |
| CN205801500U (en) * | 2016-06-30 | 2016-12-14 | 深圳市大疆创新科技有限公司 | Propeller, power suit and unmanned vehicle |
| CN206202665U (en) * | 2016-11-09 | 2017-05-31 | 亿航智能设备（广州）有限公司 | Propeller, 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 |
| CN206344996U (en) * | 2016-12-06 | 2017-07-21 | 顺丰科技有限公司 | Propeller fin |
-
2017
- 2017-08-11 CN CN201721008876.6U patent/CN207403925U/en not_active Expired - Fee Related
- 2017-10-31 CN CN201780072033.9A patent/CN109996723A/en active Pending
- 2017-10-31 WO PCT/CN2017/108494 patent/WO2019029026A1/en active Application Filing
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109178295A (en) * | 2018-10-24 | 2019-01-11 | 深圳市飞米机器人科技有限公司 | Blade, propeller and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109996723A (en) | 2019-07-09 |
| WO2019029026A1 (en) | 2019-02-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205366054U (en) | Screw, power component and aircraft | |
| CN206155775U (en) | Screw, power component and aircraft | |
| CN207072430U (en) | Propeller, Power Component and aircraft | |
| US7281900B2 (en) | Cascade rotor blade for low noise | |
| WO2017148133A1 (en) | Propeller, power assembly and aircraft | |
| CN206926806U (en) | Propeller, Power Component and aircraft | |
| WO2017124781A1 (en) | Propeller, power assembly and unmanned aircraft | |
| CN205589457U (en) | Screw, power component and aircraft | |
| CN202642093U (en) | Propeller and aircraft with propeller | |
| CN205524939U (en) | Screw, power component and aircraft | |
| CN109071006B (en) | Screw, power component and aircraft | |
| CN109641648A (en) | Propeller, Power Component and aircraft | |
| US6527515B2 (en) | Rotor for rotary wing aircraft | |
| WO2019200941A1 (en) | Gradient pitch multi-section slotted propeller | |
| CN109071004A (en) | Propeller, power suit and unmanned vehicle | |
| CN207403925U (en) | Propeller, Power Component and aircraft | |
| CN207917131U (en) | Propeller, Power Component and aircraft | |
| CN207242018U (en) | Propeller, Power Component and aircraft | |
| JP2622670B2 (en) | Supersonic aircraft wing | |
| CN206954494U (en) | Propeller, Power Component and aircraft | |
| CN206968981U (en) | Propeller, power set and aircraft | |
| CN209905055U (en) | Rotor oar and unmanned aerial vehicle | |
| CN108750074A (en) | propeller | |
| CN207773438U (en) | Propeller, Power Component and aircraft | |
| CN206068155U (en) | Blade, propeller, power suit and unmanned vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180525 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |