CN206202682U - Blade, propeller, power suit and unmanned vehicle - Google Patents
Blade, propeller, power suit and unmanned vehicle Download PDFInfo
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- CN206202682U CN206202682U CN201621083453.6U CN201621083453U CN206202682U CN 206202682 U CN206202682 U CN 206202682U CN 201621083453 U CN201621083453 U CN 201621083453U CN 206202682 U CN206202682 U CN 206202682U
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- blade
- propeller
- gyration
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Wind Motors (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a kind of blade, and for propeller, the distance of the centre of gyration on the blade away from the propeller is that at the 52.38% of the radius of gyration of the propeller, the angle of attack of the blade is 13.59 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is that at the 66.67% of the radius of gyration of the propeller, the angle of attack of the blade is 11.09 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is that at the 80.95% of the radius of gyration of the propeller, the angle of attack of the blade is 9.76 ± 2.5 degree.The utility model also provides a kind of propeller using above-mentioned blade, using the power suit and unmanned vehicle of the propeller.
Description
Technical field
The utility model is related to a kind of blade, the propeller with the blade, the power with the propeller to be set with
And the aircraft with power suit.
Background technology
Propeller on unmanned vehicle is the key element of unmanned vehicle, the propeller be used for by it is described nobody fly
The rotation of rotating shaft is converted into motive force in the motor or engine of row device, so that for the unmanned vehicle provides the dynamic of flight
Power.Propeller of the prior art is due to the limitation of appearance profile and structure, and its operating efficiency is relatively low, cannot operationally meet
The demand of expected motive force.
Utility model content
In view of this, it is necessary to which a kind of blade with greater efficiency is provided, there is a need to offer a kind of using the oar
The propeller of leaf and the power suit and unmanned vehicle using the propeller.
A kind of blade, for propeller, the distance of the centre of gyration on the blade away from the propeller is the spiral shell
At the 52.38% of the radius of gyration of rotation oar, the angle of attack of the blade is 13.59 ± 2.5 degree；Away from the spiral on the blade
The distance of the centre of gyration of oar is that at the 66.67% of the radius of gyration of the propeller, the angle of attack of the blade is 11.09 ± 2.5
Degree；The distance of the centre of gyration on the blade away from the propeller is at the 80.95% of the radius of gyration of the propeller,
The angle of attack of the blade is 9.76 ± 2.5 degree.
Further, the distance of the centre of gyration on the blade away from the propeller is the revolution half of the propeller
At the 38.10% of footpath, the angle of attack of the blade is 16.68 ± 2.5 degree；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
95.24% at, the angle of attack of the blade is 8.60 ± 2.5 degree.
Further, the tactical diameter of the propeller is 210 millimeters, in the milli of the centre of gyration 40 apart from the propeller
At rice, the angle of attack of the blade is 16.68 ± 2.5 degree；
And/or, at 55 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 13.59 ± 2.5
Degree；
And/or, at 70 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 11.09 ± 2.5
Degree；
And/or, at 85 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 9.76 ± 2.5 degree；
And/or, at 100 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 8.60 ± 2.5
Degree.
Further, the distance of the centre of gyration on the blade away from the propeller is the revolution half of the propeller
At the 52.38% of footpath, the chord length of the blade is 18.44 ± 5 millimeters；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
66.67% at, the chord length of the blade is 16.08 ± 5 millimeters；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
80.95% at, the chord length of the blade is 13.75 ± 5 millimeters.
Further, the distance of the centre of gyration on the blade away from the propeller is the revolution half of the propeller
At the 38.10% of footpath, the chord length of the blade is 20.66 ± 5 millimeters；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
95.24% at, the chord length of the blade is 11.26 ± 5 millimeters.
Further, a diameter of 210 ± 50 millimeters of the revolution of the propeller.
Further, the blade includes mutually away from the blade face and blade back for setting, and connects the blade back and described
Second lateral margin of the opposite side of first lateral margin, the connection blade back and the blade face of the side on blade face.
Further, the cross-sectional profiles of the cross-sectional profiles on the blade face and the blade back are warp architecture.
Further, first lateral margin includes that curved outwardly first arches upward portion；The second lateral margin bag
Curved outwardly second is included to arch upward portion.
Further, the oar hole of the blade to oar head distance be 4.25 millimeters.
A kind of propeller, the propeller includes oar seat and at least one blade as described above, is set on the blade
Installation portion is equipped with, the installation portion is connected with oar seat.
Further, the propeller also includes oar seat, is provided with installation portion on the blade, the installation portion with it is described
Oar seat connection.
Further, connecting hole is provided with the installation portion, the connecting hole is used to be engaged with fastener, so that institute
Stating installation portion can be connected to the oar seat by the fastener；
And/or, the center of the oar seat is the centre of gyration of the propeller, and connecting hole is provided with the installation portion,
The installation portion can be connected by the connecting hole and the oar seat, the center of the center of the connecting hole and oar seat
Interval predeterminable range.
Further, to fold oar, the quantity of the blade is at least two to the propeller, and each described blade can
It is rotationally connected with the oar seat；
Or, the propeller includes the propeller hub being fixedly connected with the blade, and the quantity of the blade is at least two.
Further, the geometrical pitch of the propeller is 3 ± 0.5 inches.
Further, the power suit includes at least one propeller as described above and drives the propeller rotational
Actuator.
Further, the actuator is motor, and the propeller is connected on the motor, and the KV values of the motor are
1400 turns/（Minute volt）.
A kind of unmanned vehicle, it includes fuselage, multiple horns and multiple power suit as described above, the multiple machine
Arm is connected with the fuselage, and the multiple power suit is separately mounted on the multiple horn.
The design of the angle of attack that the propeller that the utility model is provided passes through the different parts to blade, reduces air resistance
Power, improves efficiency, and motive force is relatively large.
Brief description of the drawings
Fig. 1 is the structural representation of the power suit that the utility model implementation method is provided.
Fig. 2 is the paddle blade structure schematic diagram of the propeller of the power suit in Fig. 1.
Fig. 3 is the front view of the blade in Fig. 2.
Fig. 4 is the side view of the blade in Fig. 2.
Fig. 5 is the side view at another visual angle of the blade in Fig. 2.
Fig. 6 is the front schematic view of the blade in Fig. 3.
Fig. 7 is the sectional view of the A-A sections of the blade in Fig. 6.
Fig. 8 is the sectional view of the B-B sections of the blade in Fig. 6.
Fig. 9 is the sectional view of the C-C sections of the blade in Fig. 6.
Figure 10 is the sectional view of the D-D sections of the blade in Fig. 6.
Figure 11 is the sectional view of the E-E sections of the blade in Fig. 6.
Main element symbol description
| Blade | 100 |
| Installation portion | 101 |
| Connecting hole | 103 |
| Blade face | 10 |
| Blade back | 20 |
| First lateral margin | 30 |
| First arches upward portion | 31 |
| Second lateral margin | 40 |
| Second arches upward portion | 41 |
Following specific embodiment will further illustrate the utility model with reference to above-mentioned accompanying drawing.
Specific embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment for being obtained, belongs to the scope of the utility model protection.
It should be noted that when component is referred to as " being fixed on " another component, it can directly on another component
Or can also there is component placed in the middle.When a component is considered as " connection " another component, it can be directly connected to
To another component or may be simultaneously present component placed in the middle.When a component is considered as " being arranged at " another component, it
Can be set directly on another component or may be simultaneously present component placed in the middle.
Unless otherwise defined, all of technologies and scientific terms used here by the article is led with technology of the present utility model is belonged to
The implication that the technical staff in domain is generally understood that is identical.It is herein to be in term used in the description of the present utility model
The purpose of description specific embodiment, it is not intended that in limitation the utility model.Term as used herein " and/or " include
The arbitrary and all of combination of one or more related Listed Items.
During the utility model is realized, inventor is found that following problem：
（1）The efficiency of propeller is relevant with the angle of attack of propeller and chord length, therefore, shape and knot of the inventor in propeller
Structure aspect is made that emphasis is improved.
（2）Especially, the efficiency of propeller is subject to propeller middle part（40% ~ 90% region）The angle of attack and chord length influence,
Therefore, inventor makes improvement in the middle part emphasis of propeller.
（3）The shape and structure of propeller directly influence the promotion force direction that it produces when rotated and motive force is big
It is small, therefore, inventor is made that some are improved in this regard.
The utility model embodiment provides a kind of propeller, and it includes blade.Away from the propeller on the blade
The distance of the centre of gyration is that at the 52.38% of the radius of gyration of the propeller, the angle of attack of the blade is 13.59 ± 2.5 degree；
The distance of the centre of gyration on the blade away from the propeller is at the 66.67% of the radius of gyration of the propeller, described
The angle of attack of blade is 11.09 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is the propeller
The radius of gyration 80.95% at, the angle of attack of the blade is 9.76 ± 2.5 degree.
The utility model embodiment also provides a kind of power suit of unmanned vehicle, and the power suit includes propeller
And motor, the propeller is connected on the motor, and the motor is used to drive the propeller rotational, the motor
KV values be 1400 turns/（Minute volt）.The propeller includes blade, in the revolution on the blade away from the propeller
The distance of the heart is that at the 66.67% of the radius of gyration of the propeller, the angle of attack of the blade is 11.09 ± 2.5 degree；Described
The distance of the centre of gyration on blade away from the propeller is at the 80.95% of the radius of gyration of the propeller, the blade
The angle of attack is 9.76 ± 2.5 degree.The propeller can provide larger motive force.
The utility model embodiment also provides a kind of unmanned vehicle, and it includes fuselage, multiple horns and multiple power
Suit, the multiple horn is connected with the fuselage, and the multiple power suit is separately mounted on the multiple horn.It is described
Power suit includes propeller and motor, and the propeller is connected on the motor, and the motor is used to drive the spiral shell
Rotation oar is rotated, and the KV values of the motor are 1400 turns/（Minute volt）.The propeller include blade, on the blade away from
The distance of the centre of gyration of the propeller is that at the 66.67% of the radius of gyration of the propeller, the angle of attack of the blade is
11.09 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
At 80.95%, the angle of attack of the blade is 9.76 ± 2.5 degree.
Below in conjunction with the accompanying drawings, some implementation methods of the present utility model are elaborated.In the case where not conflicting, under
Feature in the embodiment and embodiment stated can be mutually combined.
The unmanned vehicle that the implementation method of the utility model one is provided, it includes fuselage, horn, propeller and for driving
The actuator of the propeller rotational, the horn is connected with the fuselage.It is appreciated that in some embodiments, institute
Stating propeller can be to fold oar.The quantity of the propeller can be selected according to actual needs, can for one, two or
It is multiple.In present embodiment, the actuator is motor, the KV values of the motor are 1400 turns/（Minute volt）；Can manage
Solution, in other embodiments, the KV values of the motor can need to choose according to actual flight；The actuator can be
Other forms, such as engine.
The propeller can be positive oar or anti-oar.So-called positive oar, refers to from the afterbody of actuator such as motor to motor head
Portion sees in direction, and rotate counterclockwise is producing the propeller of lift；So-called anti-oar, refers in terms of from motor afterbody to motor head direction,
Turn clockwise to produce the propeller of lift.Specular between the structure of the structure of the positive oar and the anti-oar, therefore under
Text only illustrates the structure of the propeller by taking positive oar as an example.
Refer to Fig. 1, the structural representation of the power suit that Fig. 1 is provided for the utility model implementation method.Specifically at this
In implementation method, the power suit 200 is connected with the horn, and the horn is multiple, and the power suit 200 includes spiral shell
Rotation oar 300 and actuator 400, the propeller 300 and the actuator 400 are multiple, and each actuator 400 drives
Move a propeller 300 to rotate, constitute a set of power suit 200.Each horn is provided with least a set of power set
Fill 200.
It is appreciated that the power suit 200 may also comprise an actuator 400 and multiple（Such as two）Propeller 300.
In addition, the orientation term such as upper and lower occurred in the description of the utility model implementation method is with the propeller 300
The normal operational attitude for being installed on the later propeller 300 of the aircraft and the aircraft is reference, without answering
State and think restrictive.
Please refer to Fig. 2 to Fig. 4, the blade of the propeller 300 that the utility model implementation method is provided is shown in figure
100 structural representation.The propeller 300 includes oar seat（Not shown in figure）And it is arranged at two oars of the oar seat both sides
Leaf 100, center of two blades 100 on oar seat is centrosymmetric setting.Two blades 100 and the oar
Seat rotates to form an oar disk.In the present embodiment, the center of the oar seat essentially coincides with the center of the oar disk.When
So, in other embodiments, the propeller 300 can be straight oar, the propeller 300 can include propeller hub and with it is described
Two or more blades 100 that propeller hub is fixedly connected.
In the present embodiment, the propeller 300 is fixed propeller, and two blades 100 regularly connect
It is connected on the oar seat.Specifically in the illustrated embodiment, one end of the blade 100 is provided with installation portion 101, the peace
Connecting hole 103 is provided with dress portion 101, the installation portion 101 is connected by the connecting hole 103 with oar seat, so that
The blade 100 is connected on the oar seat.In the present embodiment, the connecting hole 103 is screwed hole, in the screwed hole
The fasteners such as screw are provided with, the installation portion 101 is connected by the fastener with oar seat.In one embodiment,
Substantially 4.25 millimeters of the distance between center O of the center of the connecting hole 103 and the oar seat.It is appreciated that at other
In some implementation methods, the distance between center of the center of the connecting hole 103 and the oar seat can be according to actual needs
Set, it is not limited to described by the utility model embodiment.Even, in certain embodiments, the installation portion 101 and described
Connecting hole 103 can be omitted.
It is appreciated that in other implementations, the propeller 300 can be foldable oar, and the blade 100 can
It is rotationally connected with the oar seat.Or, in some embodiments, the blade 100 is formed in one with oar seat
Structure, or, in some embodiments, the blade 100 is detachably mounted on the oar seat by connector, not
It is confined to described in the utility model embodiment.It can also be appreciated that according to actual needs, each described propeller
The quantity of blade 100 described in 300 can be other quantity, such as three, four.Specifically such as, in another embodiment party
In formula, the quantity of the blade 100 is three, three centers of the relatively described oar seat of the blade 100 in a circumferential direction between
Every being uniformly distributed.
In the present embodiment, a diameter of 210 ± 5 millimeters of the oar disk.Specifically, the diameter of the oar disk can be
205 millimeters, 207.5 millimeters, 210 millimeters, 212.5 millimeters, 215 millimeters, or, the diameter of the oar disk can be above-mentioned any
The arbitrary value in number range that two values are defined.Preferably, a diameter of 210 millimeters of the oar disk.Due to the oar
Disk is the effect that is formed by the blade 100 and the rotation of oar seat, be previously mentioned above and hereinafter " in oar disk
The heart " and " oar disk center ", it should be understood that " centre of gyration of propeller ", similarly, " the oar being previously mentioned above and hereinafter
The diameter of disk " and " oar disk diameter " should be understood to " tactical diameter of propeller ", and " radius of oar disk " and " oar disk radius " should
When being interpreted as " radius of gyration of propeller ".
The oar seat can be used for being connected with the rotating shaft of the actuator 400 of the unmanned vehicle, so that the driving
Part 400 can drive the propeller 300 to rotate.Reinforcement pad can be embedded with the oar seat, the reinforced sheet can be adopted
It is made of light-weight high-strength materials such as aluminium alloys, to improve the intensity of the propeller 300.
Please refer to Fig. 5, in the present embodiment, the oar seat is substantially cylindrical.During two blades 100 are in
The connection that heart symmetry shape is arranged between the both sides of the oar, and each described blade 100 and oar seat connects in shape of threads
Connect.In the present embodiment, the geometrical pitch of the propeller 300 is 3 ± 0.5 inches, and the geometrical pitch is propeller-blade section
When the angle of attack is zero, blade rotates a circle advanced distance.Specifically, the geometrical pitch of the propeller 300 can be 2.5 English
It is very little, 2.6 inches, 2.7 inches, 2.8 inches, 2.9 inches, 3.0 inches, 3.1 inches, 3.2 inches, 3.3 inches, 3.4 inches,
3.5 inches, or, the arbitrary value in number range that the geometrical pitch can be defined by above-mentioned any two numerical value.It is excellent
Selection of land, the geometrical pitch is 3 inches.
The blade 100 includes mutually away from the blade face 10 and blade back 20 for setting, and connects the blade back 20 and described
Second lateral margin 40 of the opposite side of first lateral margin 30, the connection blade back 20 and the blade face 10 of the side on blade face 10.It is described
The cross-sectional profiles of the cross-sectional profiles on blade face 10 and the blade back 20 are warp architecture（Refer to Fig. 7 to Figure 11）.Work as institute
Propeller 300 is stated to be installed in when on the actuator 400 of the unmanned plane, the blade face 10 towards the actuator 400, that is,
The blade face 10 is set down；And the blade back 20 deviates from the actuator 400, that is, the blade back 20 is set upward.At this
In implementation method, the blade face 10 and the blade back 20 are curved surface.First lateral margin 30 includes curved outwardly
First arch upward portion 31.Described first portion 31 that arches upward is connected smoothly with the other parts of first lateral margin 30.In this reality
Apply in mode, described first arches upward portion 31 adjacent to oar seat setting.Second lateral margin 40 includes curved outwardly
Second arch upward portion 41, described second portion 41 that arches upward is connected smoothly with the other parts of second lateral margin 40.In this reality
Apply in mode, described second arches upward portion 41 adjacent to oar seat setting.
In the propeller 300 that the utility model implementation method is provided, without drastically torsion part on the blade 100,
Stress is smaller, and structural strength is higher, is not easily broken, and reliability is high.The blade 100 is the oar away from one end of oar seat
The most thin part of leaf 100, is conducive to reducing air drag.That is, the thickness of the one end at center of the described blade 100 away from the oar disk
Thickness of the degree less than the other parts of the blade 100.
In present embodiment, the length of the blade 100 is 96 ± 5 millimeters.The length of the blade 100 can be 91 millis
Rice to the arbitrary value between 101 millimeters, such as 91 millimeters, 93.5 millimeters, 96 millimeters, 98.5 millimeters, 101 millimeters, or, it is described
The arbitrary value in number range that the length of blade 100 can be defined by above-mentioned any two numerical value.Preferably, the blade
100 length is 96 millimeters.
The angle of attack referred to herein, refer to the blade 100 wing chord and speed of incoming flow between angle.
Please refer to Fig. 6 and Fig. 7, the distance of the center O on the blade 100 away from the oar disk is the oar disk half
At the 38.10% of footpath, the angle of attack 1 of the blade 100 is 16.68 ± 2.5 degree.Specifically, the angle of attack 1 of blade described herein 100
Can be 14.18 degree, 15.18 degree, 15.68 degree, 16.68 degree, 17.68 degree, 18.18 degree, 19.18 degree, or, oar described herein
The arbitrary value in number range that the angle of attack 1 of leaf 100 can be defined by above-mentioned any two numerical value, in the present embodiment,
The angle of attack 1 is 16.68 degree.The distance of the center O on the blade 100 away from the oar disk is the oar disk radius
At 38.10%, the chord length L1 of the blade 100 is 20.66 ± 5 millimeters.Specifically, the chord length L1 of blade described herein 100 can be with
It is 15.66 millimeters, 16.66 millimeters, 18.66 millimeters, 20.66 millimeters, 22.66 millimeters, 24.66 millimeters, 25.66 millimeters, or,
The numerical value in number range that the chord length L1 of blade described herein 100 can be defined by above-mentioned any two numerical value, in this reality
Apply in mode, the chord length L1 is 20.66 millimeters.
Please refer to Fig. 6 and Fig. 8, the distance of the center O on the blade 100 away from the oar disk is the oar disk half
At the 52.38% of footpath, the angle of attack 2 of the blade 100 is 13.59 ± 2.5 degree.Specifically, the angle of attack 2 of blade described herein 100
Can be 11.09 degree, 12.09 degree, 12.59 degree, 13.59 degree, 14.59 degree, 15.09 degree, 16.09 degree, or, oar described herein
The arbitrary value in number range that the angle of attack 2 of leaf 100 can be defined by above-mentioned any two numerical value, in the present embodiment,
The angle of attack 2 is 13.59 degree.The distance of the center O on the blade 100 away from the oar disk is the oar disk radius
At 52.38%, the chord length L2 of the blade 100 is 18.44 ± 5 millimeters.Specifically, the chord length L2 of blade described herein 100 can be with
It is 13.44 millimeters, 14.44 millimeters, 16.44 millimeters, 18.44 millimeters, 20.44 millimeters, 22.44 millimeters, 23.44 millimeters, or,
Specifically, it is any in the number range that the chord length L2 of blade described herein 100 can be defined by above-mentioned any two numerical value
Value, in the present embodiment, the chord length L2 is 18.44 millimeters.
Please refer to Fig. 6 and Fig. 9, the distance of the center O on the blade 100 away from the oar disk is the oar disk half
At the 66.67% of footpath, the angle of attack 3 of the blade 100 is 11.09 ± 2.5 degree.Specifically, the angle of attack 3 of blade described herein 100
Can be 8.59 degree, 9.59 degree, 10.09 degree, 11.09 degree, 12.09 degree, 12.59 degree, 13.59 degree, or, blade described herein
The arbitrary value in number range that 100 angle of attack 3 can be defined by above-mentioned any two numerical value, in the present embodiment, institute
Angle of attack 3 is stated for 11.09 degree.The distance of the center O on the blade 100 away from the oar disk is the oar disk radius
At 66.67%, the chord length L3 of the blade 100 is 16.08 ± 5 millimeters.Specifically, the chord length L3 of blade described herein 100 can be with
It is 11.08 millimeters, 12.08 millimeters, 14.08 millimeters, 16.08 millimeters, 18.08 millimeters, 20.08 millimeters, 21.08 millimeters, or,
The arbitrary value in number range that the chord length L3 of blade described herein 100 can be defined by above-mentioned any two numerical value, at this
In implementation method, the chord length L3 is 16.08 millimeters.
Please refer to Fig. 6 and Figure 10, the distance of the center O on the blade 100 away from the oar disk is the oar disk
At the 80.95% of radius, the angle of attack 4 of the blade 100 is 9.76 ± 2.5 degree.Specifically, the angle of attack of blade described herein 100
4 can be 7.26 degree, 8.26 degree, 8.76 degree, 9.76 degree, 10.76 degree, 11.26 degree, 12.26 degree, or, blade described herein
The arbitrary value in number range that 100 angle of attack 4 can be defined by above-mentioned any two numerical value, in the present embodiment, institute
Angle of attack 4 is stated for 9.76 degree.The distance of the center O on the blade 100 away from the oar disk is the 80.95% of the oar disk radius
Place, the chord length L4 of the blade 100 is 13.75 ± 5 millimeters.Specifically, the chord length L4 of blade described herein 100 can be 8.75
Millimeter, 9.75 millimeters, 11.75 millimeters, 13.75 millimeters, 15.75 millimeters, 17.75 millimeters, 18.75 millimeters, or, it is described herein
The arbitrary value in number range that the chord length L4 of blade 100 can be defined by above-mentioned any two numerical value, in present embodiment
In, the chord length L4 is 13.75 millimeters.
Please refer to Fig. 6 and Figure 11, the distance of the center O on the blade 100 away from the oar disk is the oar disk
At the 95.24% of radius, the angle of attack 5 of the blade 100 is 8.60 ± 2.5 degree.Specifically, the angle of attack of blade described herein 100
5 can be 6.10 degree, 7.10 degree, 7.60 degree, 8.60 degree, 9.60 degree, 10.10 degree, 11.10 degree, or, blade described herein
The arbitrary value in number range that 100 angle of attack 5 can be defined by above-mentioned any two numerical value, in the present embodiment, institute
Angle of attack 5 is stated for 8.60 degree.The distance of the center O on the blade 100 away from the oar disk is the 95.24% of the oar disk radius
Place, the chord length L5 of the blade 100 is 11.26 ± 5 millimeters.Specifically, the chord length L5 of blade described herein 100 can be 6.26
Millimeter, 7.26 millimeters, 9.26 millimeters, 11.26 millimeters, 13.26 millimeters, 15.26 millimeters, 16.26 millimeters, or, it is described herein
The arbitrary value in number range that the chord length L5 of blade 100 can be defined by above-mentioned any two numerical value, in present embodiment
In, the chord length L5 is 11.26 millimeters.
Referring to Fig. 6 to Figure 11, in the present embodiment, a diameter of 210 millimeters of the oar disk.In the blade
On 100 at 40 millimeters of oar disk center described in distance, the angle of attack 1 of the blade 100 is 16.68 degree, the chord length of the blade 100
L1 is 20.66 millimeters；At 55 millimeters of the center of the oar disk, the angle of attack 2 of the blade 100 is 13.59 degree, described
The chord length L2 of blade 100 is 18.44 millimeters；At 70 millimeters of the center of the oar disk, the angle of attack 3 of the blade 100 is
11.09 degree, the chord length L3 of the blade 100 is 16.08 millimeters；At 85 millimeters of the center of the oar disk, the blade
100 angle of attack 4 is 9.76 degree, and the chord length L4 of the blade 100 is 13.75 millimeters；In the milli of center 100 apart from the oar disk
At rice, the angle of attack 5 of the blade 100 is 8.60 degree, and the chord length L5 of the blade 100 is 11.26 millimeters.
Table 1 is referred to, table 1 show promotion force value of the propeller of present embodiment offer under different rotating speeds.
The propeller pulling force of table 1-performance number
By can be seen that the propeller of implementation method offer of the present utility model in table under identical pulling force size, need
The power wanted is smaller such that it is able to save electric quantity consumption, increased the endurance distance of unmanned vehicle, improves efficiency.
The design of the angle of attack that the propeller that the utility model is provided passes through the different parts to blade, reduces air resistance
Power, improves efficiency, increased the endurance distance of aircraft and improves the flying quality of aircraft.
In addition, those skilled in the art are it should be appreciated that the implementation method of the above is intended merely to explanation originally
Utility model, and be not used as be to restriction of the present utility model, if within spirit of the present utility model, it is right
The appropriate change and change that above example is made all fall within the scope of the utility model is claimed.
Claims (17)
1. a kind of blade, for propeller in, it is characterised in that：The centre of gyration on the blade away from the propeller away from
Away from 52.38% of the radius of gyration for the propeller, the angle of attack of the blade is 13.59 ± 2.5 degree；On the blade
The distance of the centre of gyration away from the propeller is that at the 66.67% of the radius of gyration of the propeller, the angle of attack of the blade is
11.09 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
At 80.95%, the angle of attack of the blade is 9.76 ± 2.5 degree.
2. blade as claimed in claim 1, it is characterised in that：The centre of gyration on the blade away from the propeller away from
Away from 38.10% of the radius of gyration for the propeller, the angle of attack of the blade is 16.68 ± 2.5 degree；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
At 95.24%, the angle of attack of the blade is 8.60 ± 2.5 degree.
3. blade as claimed in claim 1, it is characterised in that：The tactical diameter of the propeller using the blade is 210
Millimeter, at 40 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 16.68 ± 2.5 degree；
And/or, at 55 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 13.59 ± 2.5 degree；
And/or, at 70 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 11.09 ± 2.5 degree；
And/or, at 85 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 9.76 ± 2.5 degree；
And/or, at 100 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 8.60 ± 2.5 degree.
4. blade as claimed in claim 1, it is characterised in that：The centre of gyration on the blade away from the propeller away from
Away from 52.38% of the radius of gyration for the propeller, the chord length of the blade is 18.44 ± 5 millimeters；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
At 66.67%, the chord length of the blade is 16.08 ± 5 millimeters；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
At 80.95%, the chord length of the blade is 13.75 ± 5 millimeters.
5. blade as claimed in claim 4, it is characterised in that：The centre of gyration on the blade away from the propeller away from
Away from 38.10% of the radius of gyration for the propeller, the chord length of the blade is 20.66 ± 5 millimeters；
And/or, the distance of the centre of gyration on the blade away from the propeller is the radius of gyration of the propeller
At 95.24%, the chord length of the blade is 11.26 ± 5 millimeters.
6. blade as claimed in claim 1, it is characterised in that：A diameter of 210 ± 50 millimeters of the revolution of the propeller.
7. blade as claimed in claim 1, it is characterised in that：The blade includes mutually deviating from blade face and the blade back for setting,
And connect the side on the blade back and the blade face the first lateral margin, connect the blade back and the blade face opposite side the
Two lateral margins.
8. blade as claimed in claim 7, it is characterised in that：The cross section of the cross-sectional profiles on the blade face and the blade back
Profile is warp architecture.
9. blade as claimed in claim 7, it is characterised in that：First lateral margin includes curved outwardly first
Arch upward portion；Second lateral margin includes that curved outwardly second arches upward portion.
10. blade as claimed in claim 1, it is characterised in that：The oar hole of the blade to oar head distance be 4.25 millimeters.
A kind of 11. propellers, it is characterised in that：The propeller includes that oar seat and at least one such as claim 1-10 are any
Blade described in, is provided with installation portion on the blade, the installation portion is connected with oar seat.
12. propellers as claimed in claim 11, it is characterised in that：Connecting hole, the connection are provided with the installation portion
Hole is used to be engaged with fastener, so that the installation portion can be connected to the oar seat by the fastener；
And/or, the center of the oar seat is the centre of gyration of the propeller, and connecting hole is provided with the installation portion, described
Installation portion can be connected by the connecting hole and the oar seat, the middle heart septum of the center of the connecting hole and oar seat
Predeterminable range.
13. propellers as claimed in claim 11, it is characterised in that：The propeller is folding oar, the quantity of the blade
It is at least two, each described blade can be rotationally connected with the oar seat；
Or, the propeller includes the propeller hub being fixedly connected with the blade, and the quantity of the blade is at least two.
14. propellers as claimed in claim 11, it is characterised in that：The geometrical pitch of the propeller is 3 ± 0.5 inches.
A kind of power suit of 15. unmanned vehicles, it is characterised in that：The power suit includes any one of claim 11
At least one described propeller and the actuator of the driving propeller rotational.
16. power suits as claimed in claim 15, it is characterised in that：The actuator is motor, the propeller connection
In on the motor, the KV values of the motor for 1400 turns/（Minute volt）.
A kind of 17. unmanned vehicles, it includes the multiple power suit described in fuselage, multiple horns and claim 15 or 16,
The multiple horn is connected with the fuselage, and the multiple power suit is separately mounted on the multiple horn.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621083453.6U CN206202682U (en) | 2016-09-27 | 2016-09-27 | Blade, propeller, power suit and unmanned vehicle |
| PCT/CN2016/106550 WO2018058769A1 (en) | 2016-09-27 | 2016-11-21 | Blade, airscrew, power package and unmanned aerial vehicle |
| CN201680088644.8A CN109641654A (en) | 2016-09-27 | 2016-11-21 | Blade, propeller, power suit and unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621083453.6U CN206202682U (en) | 2016-09-27 | 2016-09-27 | Blade, propeller, power suit and unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206202682U true CN206202682U (en) | 2017-05-31 |
Family
ID=58761485
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621083453.6U Expired - Fee Related CN206202682U (en) | 2016-09-27 | 2016-09-27 | Blade, propeller, power suit and unmanned vehicle |
| CN201680088644.8A Pending CN109641654A (en) | 2016-09-27 | 2016-11-21 | Blade, propeller, power suit and unmanned vehicle |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680088644.8A Pending CN109641654A (en) | 2016-09-27 | 2016-11-21 | Blade, propeller, power suit and unmanned vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN206202682U (en) |
| WO (1) | WO2018058769A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019223205A1 (en) * | 2018-05-25 | 2019-11-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU567757B2 (en) * | 1983-09-05 | 1987-12-03 | Sims, M.L. | Improved hydrofoil keel. |
| US6932296B2 (en) * | 2003-10-21 | 2005-08-23 | Information Systems Laboratories, Inc. | Cycloidal VTOL UAV |
| EP2253835A1 (en) * | 2009-05-18 | 2010-11-24 | Lm Glasfiber A/S | Wind turbine blade with base part having non-positive camber |
| CN203996873U (en) * | 2014-07-30 | 2014-12-10 | 深圳市大疆创新科技有限公司 | Aircraft and screw propeller thereof |
| 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 |
| CN205345321U (en) * | 2016-01-19 | 2016-06-29 | 深圳市大疆创新科技有限公司 | Screw, power suit and unmanned vehicles |
| CN205345320U (en) * | 2016-01-27 | 2016-06-29 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205524939U (en) * | 2016-01-27 | 2016-08-31 | 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 |
| CN205396538U (en) * | 2016-03-02 | 2016-07-27 | 深圳市道通智能航空技术有限公司 | Screw and aircraft |
-
2016
- 2016-09-27 CN CN201621083453.6U patent/CN206202682U/en not_active Expired - Fee Related
- 2016-11-21 CN CN201680088644.8A patent/CN109641654A/en active Pending
- 2016-11-21 WO PCT/CN2016/106550 patent/WO2018058769A1/en active Application Filing
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019223205A1 (en) * | 2018-05-25 | 2019-11-28 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109641654A (en) | 2019-04-16 |
| WO2018058769A1 (en) | 2018-04-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170531 |