CN206068155U - Blade, propeller, power suit and unmanned vehicle - Google Patents
Blade, propeller, power suit and unmanned vehicle Download PDFInfo
- Publication number
- CN206068155U CN206068155U CN201621083454.0U CN201621083454U CN206068155U CN 206068155 U CN206068155 U CN 206068155U CN 201621083454 U CN201621083454 U CN 201621083454U CN 206068155 U CN206068155 U CN 206068155U
- Authority
- CN
- China
- Prior art keywords
- blade
- propeller
- gyration
- millimeters
- centre
- 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
- 238000009434 installation Methods 0.000 claims description 19
- 210000003361 heart septum Anatomy 0.000 claims 1
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VIKNJXKGJWUCNN-XGXHKTLJSA-N norethisterone Chemical compound O=C1CC[C@@H]2[C@H]3CC[C@](C)([C@](CC4)(O)C#C)[C@@H]4[C@@H]3CCC2=C1 VIKNJXKGJWUCNN-XGXHKTLJSA-N 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 235000009566 rice Nutrition 0.000 description 1
- 230000000007 visual effect Effects 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
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Wind Motors (AREA)
Abstract
This 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 51.28% of the radius of gyration of the propeller, the angle of attack of the blade is 11.53 ± 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 9.87 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is that, at the 82.05% of the radius of gyration of the propeller, the angle of attack of the blade is 8.28 ± 2.5.This 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
This utility model is related to a kind of blade, the propeller with the blade, the suit of the power with the propeller
And the aircraft with power suit.
Background technology
Propeller on unmanned vehicle for unmanned vehicle key element, the propeller for by it is described nobody fly
The rotation of rotating shaft in the motor or electromotor of row device is converted into motive force, so as to provide the dynamic of flight for the unmanned vehicle
Power., due to the restriction of appearance profile and structure, its work efficiency is relatively low for propeller of the prior art, 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 using the propeller power be set with and unmanned vehicle.
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 51.28% of the radius of gyration of rotation oar, the angle of attack of the blade is 11.53 ± 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 9.87 ± 2.5
Degree；The distance of the centre of gyration on the blade away from the propeller is at the 82.05% of the radius of gyration of the propeller,
The angle of attack of the blade is 8.28 ± 2.5.
Further, the distance of the centre of gyration on the blade away from the propeller is the revolution half of the propeller
At the 35.90% of footpath, the angle of attack of the blade is 15.40 ± 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
97.44% at, the angle of attack of the blade is 7.03 ± 2.5 degree.
Further, the tactical diameter of the propeller is 195 millimeters, in 35 milli of the centre of gyration apart from the propeller
At rice, the angle of attack of the blade is 15.40 ± 2.5 degree；
And/or, at 50 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 11.53 ± 2.5
Degree；
And/or, at 65 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 9.87 ± 2.5 degree；
And/or, at 80 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 8.28 ± 2.5 degree；
And/or, at 95 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 7.03 ± 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 51.28% of footpath, the chord length of the blade is 17.52 ± 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 15.27 ± 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
82.05% at, the chord length of the blade is 13.03 ± 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 35.90% of footpath, the chord length of the blade is 20.05 ± 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
97.44% at, the chord length of the blade is 10.63 ± 5 millimeters.
Further, a diameter of 195 ± 50 millimeters of the revolution of the propeller.
Further, the blade includes mutually away from the blade face and blade back for arranging, 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
Include curved outwardly second 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 include oar seat and at least one blade as above, set on the blade
Installation portion is equipped with, the installation portion is connected with the oar seat.Further, the propeller also includes oar seat, on the blade
Installation portion is provided with, the installation portion is connected with the oar seat.
Further, connecting hole is provided with the installation portion, the connecting hole is for being engaged with securing member, so that institute
State installation portion and the oar seat can be connected to by the securing member；
And/or, the center of the oar seat is the centre of gyration of the propeller, is provided with connecting hole on the installation portion,
The installation portion can be connected with the oar seat by the connecting hole, the center of the center of the connecting hole and the 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 2 ± 0.5 inches.
Further, the power suit includes at least one propeller as 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, which includes fuselage, multiple horns and multiple power suits as above, the plurality of machine
Arm is connected with the fuselage, and the plurality of power suit is separately mounted on the plurality of horn.
The design of the angle of attack of the propeller that this utility model is provided by the different parts to blade, reduces air resistance
Power, improves efficiency, and motive force is relatively large.
Description of the drawings
Fig. 1 is the structural representation of the power suit that this utility model embodiment 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 this utility model with reference to above-mentioned accompanying drawing.
Specific embodiment
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only this utility model a part of embodiment, rather than whole
Embodiment.Based on the embodiment in this 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 this 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 technology used herein and scientific terminology are 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.In term used in the description of the present utility model it is simply herein
The purpose of description specific embodiment, it is not intended that in limiting this utility model.Term as used herein " and/or " include
The arbitrary and all of combination of one or more related Listed Items.
During this 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, for this purpose, shape and knot of the inventor in propeller
It is made that in terms of structure that emphasis is improved.
（2）Especially, the efficiency of propeller is subject in the middle part of propeller（40% ~ 90% region）The angle of attack and chord length affect,
For this purpose, inventor makes improvement in the middle part emphasis of propeller.
（3）The shape and structure of propeller directly influences the promotion force direction which produces when rotated and motive force is big
It is little, for this purpose, inventor is made that some improvement in this regard.
This utility model embodiment provides a kind of propeller, and which includes blade.Away from the propeller on the blade
The distance of the centre of gyration is that, at the 51.28% of the radius of gyration of the propeller, the angle of attack of the blade is 11.53 ± 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 9.87 ± 2.5 degree；The distance of the centre of gyration on the blade away from the propeller is the propeller
The radius of gyration 82.05% at, the angle of attack of the blade is 8.28 ± 2.5 degree.
This 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 9.87 ± 2.5 degree；In the oar
The distance of the centre of gyration on leaf away from the propeller is at the 82.05% of the radius of gyration of the propeller, and the blade is attacked
Angle is 8.28 ± 2.5 degree.The propeller can provide larger motive force.
This utility model embodiment also provides a kind of unmanned vehicle, and which includes fuselage, multiple horns and multiple power
Suit, the plurality of horn are connected with the fuselage, and the plurality of power suit is separately mounted on the plurality of 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, the KV values of the motor for 1400 turns/（Minute volt）.The propeller includes 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
9.87 ± 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 82.05%, the angle of attack of the blade is 8.28 ± 2.5 degree.
Below in conjunction with the accompanying drawings, some embodiments of the present utility model are elaborated.In the case where not conflicting, under
Feature in the embodiment stated and embodiment can be mutually combined.
The unmanned vehicle that one embodiment of this utility model is provided, which includes fuselage, horn, propeller and is used to drive
The actuator of the propeller rotational, the horn are 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 be one, two or
It is multiple.In present embodiment, the actuator is motor, the KV values of the motor for 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 electromotor etc..
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 this utility model embodiment.Specifically at this
In embodiment, 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 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 this utility model embodiment 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, and does not answer institute
State and think restrictive.
Please refer to Fig. 2 to Fig. 4, the blade of the propeller 300 that this utility model embodiment is provided in figure, is shown
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, two blades 100 are centrosymmetric setting with regard to the center of the oar seat.Two blades 100 and the oar
Seat rotates to form an oar disk.In the present embodiment, the center of the oar seat is essentially coincided 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 with the oar seat by the connecting hole 103, 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 securing members such as screw are provided with, the installation portion 101 is connected with the oar seat by the securing member.In one embodiment,
Substantially 4.25 millimeters of the distance between the center of the connecting hole 103 and center O of the oar seat.It is appreciated that at other
In some embodiments, the distance between the center of the connecting hole 103 and center of the oar seat can be according to actual needs
Arrange, it is not limited to described by this 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 the oar seat
Structure, or, in some embodiments, the blade 100 is detachably mounted on the oar seat, not by connector
It is confined to described in this 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 etc..Specifically such as, in another embodiment party
In formula, the quantity of the blade 100 is three, the center of the relatively described oar seat of three blades 100 in a circumferential direction between
Every being uniformly distributed.
In the present embodiment, a diameter of 195 ± 5 millimeters of the oar disk.Specifically, the diameter of the oar disk can be
190 millimeters, 192.5 millimeters, 195 millimeters, 197.5 millimeters, 200 millimeters, or, the diameter of the oar disk can be above-mentioned any
The arbitrary value in numerical range defined by two values.Preferably, a diameter of 195 millimeters of the oar disk.Due to the oar
Disk is the effect that formed by the blade 100 and oar seat rotation, 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 rotational.Reinforcement pad can be embedded with the oar seat, the reinforced sheet can adopt aluminum
The light-weight high-strength materials such as alloy are made, to improve the intensity of the propeller.
Please refer to Fig. 5, in the present embodiment, the oar seat is substantially cylindrical.During two blades 100 are in
Heart symmetry shape is arranged on the connection between the both sides of the oar seat, and each described blade 100 and the oar seat and connects in screw-like
Connect.In the present embodiment, the geometrical pitch of the propeller 300 is 2 ± 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 1.5 English
It is very little, 1.6 inches, 1.7 inches, 1.8 inches, 1.9 inches, 2.0 inches, 2.1 inches, 2.2 inches, 2.3 inches, 2.4 inches,
2.5 inches, or, the arbitrary value in numerical range that the geometrical pitch can be defined by above-mentioned any two numerical value.It is excellent
Selection of land, the geometrical pitch are 2 inches.
The blade 100 includes mutually away from the blade face 10 and blade back 20 for arranging, 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
When stating propeller 300 and being installed on the actuator 400 of the unmanned plane, the blade face 10 towards the actuator 400, that is,
The blade face 10 is arranged down；And the blade back 20 deviates from the actuator 400, that is, the blade back 20 is arranged upward.At this
In embodiment, 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 portion 31 that arches upward is arranged adjacent to the oar seat.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 portion 41 that arches upward is arranged adjacent to the oar seat.
In the propeller 300 provided by this utility model embodiment, without drastically torsion part on the blade 100,
Stress is less, and structural strength is higher, is not easily broken, and reliability is high.The blade 100 is the oar away from one end of the oar seat
The most thin part of leaf 100, is conducive to reducing air drag.That is, thickness of the described blade 100 away from the one end at the center of the oar disk
Thickness of the degree less than 100 other parts of the blade.
In present embodiment, the length of the blade 100 is 88.5 ± 5 millimeters.The length of the blade 100 can be
Arbitrary value between 83.5 millimeters to 93.5 millimeters, such as 83.5 millimeters, 86 millimeters, 88.5 millimeters, 91 millimeters, 93.5 millimeters,
Or, the arbitrary value in numerical range that the length of the blade 100 can be defined by above-mentioned any two numerical value.It is preferred that
Ground, the length of the blade 100 is 84 millimeters.
The angle of attack referred to herein, refers to the angle between the wing chord and speed of incoming flow of the blade 100.
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 35.90% of footpath, the angle of attack 1 of the blade 100 is 15.40 ± 2.5 degree.Specifically, the angle of attack 1 of blade described herein 100
Can be 12.90 degree, 13.90 degree, 14.40 degree, 15.40 degree, 16.40 degree, 16.90 degree, 17.90 degree, or, oar described herein
The arbitrary value in numerical range that the angle of attack 1 of leaf 100 can be defined by above-mentioned wantonly 65 meaning two values, in present embodiment
In, the angle of attack 1 is 15.40 degree.The distance of the center O on the blade 100 away from the oar disk is the oar disk radius
At 35.90%, chord length L1 of the blade 100 is 20.05 ± 5 millimeters.Specifically, chord length L1 of blade described herein 100 can be with
For 15.05 millimeters, 16.05 millimeters, 18.05 millimeters, 20.05 millimeters, 22.05 millimeters, 24.05 millimeters, 25.05 millimeters, or,
The numerical value in numerical range that chord length L1 of blade described herein 100 can be defined by above-mentioned any two numerical value, in this reality
Apply in mode, chord length L1 is 20.05 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 51.28% of footpath, the angle of attack 2 of the blade 100 is 11.53 ± 2.5 degree.Specifically, the angle of attack 2 of blade described herein 100
Can be 9.03 degree, 10.03 degree, 10.53 degree, 11.53 degree, 12.53 degree, 13.03 degree, 14.03 degree, or, oar described herein
The arbitrary value in numerical 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 11.53 degree.The distance of the center O on the blade 100 away from the oar disk is the oar disk radius
At 51.28%, chord length L2 of the blade 100 is 17.52 ± 5 millimeters.Specifically, chord length L2 of blade described herein 100 can be with
For 12.52 millimeters, 13.52 millimeters, 15.52 millimeters, 17.52 millimeters, 19.52 millimeters, 21.52 millimeters, 22.52 millimeters, or,
Specifically, it is any in the numerical range that chord length L2 of blade described herein 100 can be defined by above-mentioned any two numerical value
Value, in the present embodiment, chord length L2 is 17.52 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 9.87 ± 2.5 degree.Specifically, the angle of attack 3 of blade described herein 100
Can be 7.37 degree, 8.37 degree, 8.87 degree, 9.87 degree, 10.87 degree, 11.37 degree, 12.37 degree, or, blade described herein
The arbitrary value in numerical 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 9.87 degree.The distance of the center O on the blade 100 away from the oar disk is the 66.67% of the oar disk radius
Place, chord length L3 of the blade 100 is 15.27 ± 5 millimeters.Specifically, chord length L3 of blade described herein 100 can be
10.27 millimeters, 11.27 millimeters, 13.27 millimeters, 15.27 millimeters, 17.27 millimeters, 19.27 millimeters, 20.27 millimeters, or, this
Locate the arbitrary value in the numerical range that chord length L3 of the blade 100 can be defined by above-mentioned any two numerical value, in this reality
Apply in mode, chord length L3 is 15.27 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 82.05% of radius, the angle of attack 4 of the blade 100 is 8.28 ± 2.5 degree.Specifically, the angle of attack of blade described herein 100
4 can be 5.78 degree, 6.78 degree, 7.28 degree, 8.28 degree, 9.28 degree, 9.78 degree, 10.78 degree, or, blade described herein 100
The numerical range that can be defined by above-mentioned any two numerical value of angle of attack 4 in arbitrary value, it is in the present embodiment, described
Angle of attack 4 is 8.28 degree.The distance of the center O on the blade 100 away from the oar disk is the 82.05% of the oar disk radius
Place, chord length L4 of the blade 100 is 13.03 ± 5 millimeters.Specifically, chord length L4 of blade described herein 100 can be 8.03
Millimeter, 9.03 millimeters, 11.03 millimeters, 13.03 millimeters, 15.03 millimeters, 17.03 millimeters, 18.03 millimeters, or, it is described herein
The arbitrary value in numerical range that chord length L4 of blade 100 can be defined by above-mentioned any two numerical value, in present embodiment
In, chord length L4 is 13.03 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 97.44% of radius, the angle of attack 5 of the blade 100 is 7.03 ± 2.5 degree.Specifically, the angle of attack of blade described herein 100
5 can be 4.53 degree, 5.53 degree, 6.03 degree, 7.03 degree, 8.03 degree, 8.53 degree, 9.53 degree, or, blade described herein 100
The numerical range that can be defined by above-mentioned any two numerical value of angle of attack 5 in arbitrary value, it is in the present embodiment, described
Angle of attack 5 is 7.03 degree.The distance of the center O on the blade 100 away from the oar disk is the 97.44% of the oar disk radius
Place, chord length L5 of the blade 100 is 10.63 ± 5 millimeters.Specifically, chord length L5 of blade described herein 100 can be 5.63
Millimeter, 6.63 millimeters, 8.63 millimeters, 10.63 millimeters, 12.63 millimeters, 14.63 millimeters, 15.63 millimeters, or, it is described herein
The arbitrary value in numerical range that chord length L5 of blade 100 can be defined by above-mentioned any two numerical value, in present embodiment
In, chord length L5 is 10.63 millimeters.
Referring to Fig. 6 to Figure 11, in the present embodiment, a diameter of 195 millimeters of the oar disk.In the blade
On 100 at 35 millimeters of oar disk center described in distance, the angle of attack 1 of the blade 100 is 15.40 degree, the chord length of the blade 100
L1 is 20.05 millimeters；At 50 millimeters of the center of the oar disk, the angle of attack 2 of the blade 100 is 11.53 degree, described
Chord length L2 of blade 100 is 17.52 millimeters；At 65 millimeters of the center of the oar disk, the angle of attack 3 of the blade 100 is
9.87 degree, chord length L3 of the blade 100 is 15.27 millimeters；At 80 millimeters of the center of the oar disk, the blade
100 angle of attack 4 is 8.28 degree, and chord length L4 of the blade 100 is 13.03 millimeters；Apart from 95 millimeters of the center of the oar disk
Place, the angle of attack 5 of the blade 100 is 7.03 degree, and chord length L5 of the blade 100 is 10.63 millimeters.
Table 1 is referred to, table 1 show promotion force value of the propeller of present embodiment offer under different rotating speeds.
1 propeller pulling force of table-performance number
By the propeller of embodiment offer of the present utility model is can be seen that in table under identical pulling force size, need
The power wanted is less 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 of the propeller that this utility model is provided by 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 embodiment 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 made by above example all falls within the scope of this utility model is claimed.
Claims (17)
1. a kind of blade, for propeller, it is characterised in that：The distance of the centre of gyration on the blade away from the propeller
For the propeller the radius of gyration 51.28% at, the angle of attack of the blade is 11.53 ± 2.5 degree；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
9.87 ± 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 82.05%, the angle of attack of the blade is 8.28 ± 2.5.
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 35.90% of the radius of gyration for the propeller, the angle of attack of the blade is 15.40 ± 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 97.44%, the angle of attack of the blade is 7.03 ± 2.5 degree.
3. blade as claimed in claim 1, it is characterised in that：The tactical diameter of the propeller is 195 millimeters, apart from institute
State at 35 millimeters of the centre of gyration of propeller, the angle of attack of the blade is 15.40 ± 2.5 degree；
And/or, at 50 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 11.53 ± 2.5 degree；
And/or, at 65 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 9.87 ± 2.5 degree；
And/or, at 80 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 8.28 ± 2.5 degree；
And/or, at 95 millimeters of the centre of gyration of the propeller, the angle of attack of the blade is 7.03 ± 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 51.28% of the radius of gyration for the propeller, the chord length of the blade is 17.52 ± 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 15.27 ± 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 82.05%, the chord length of the blade is 13.03 ± 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 35.90% of the radius of gyration for the propeller, the chord length of the blade is 20.05 ± 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 97.44%, the chord length of the blade is 10.63 ± 5 millimeters.
6. blade as claimed in claim 1, it is characterised in that：A diameter of 195 ± 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 arranging,
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 arbitrary
Blade described in, is provided with installation portion on the blade, the installation portion is connected with the 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 for being engaged with securing member, so that the installation portion can be connected to the oar seat by the securing member；
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 with the oar seat by the connecting hole, the middle heart septum of the center of the connecting hole and the 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
For 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 2 ± 0.5 inches.
A kind of power suit of 15. unmanned vehicles, it is characterised in that：The power suit is included described in claim 11
The actuator of at least one propeller and the driving propeller rotational.
16. power suits as claimed in claim 15, it is characterised in that：The actuator is motor, the propeller connection
On the motor, the KV values of the motor are 1400 turns/（Minute volt）.
A kind of 17. unmanned vehicles, which includes the multiple power suits described in fuselage, multiple horns and claim 15 or 16,
The plurality of horn is connected with the fuselage, and the plurality of power suit is separately mounted on the plurality of horn.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621083454.0U CN206068155U (en) | 2016-09-27 | 2016-09-27 | Blade, propeller, power suit and unmanned vehicle |
| PCT/CN2016/106549 WO2018058768A1 (en) | 2016-09-27 | 2016-11-21 | Blade, airscrew, power package and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621083454.0U CN206068155U (en) | 2016-09-27 | 2016-09-27 | Blade, propeller, power suit and unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206068155U true CN206068155U (en) | 2017-04-05 |
Family
ID=58441118
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621083454.0U Expired - Fee Related CN206068155U (en) | 2016-09-27 | 2016-09-27 | Blade, propeller, power suit and unmanned vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN206068155U (en) |
| WO (1) | WO2018058768A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109789921A (en) * | 2017-04-07 | 2019-05-21 | 深圳市大疆创新科技有限公司 | Blade, propeller, power suit and unmanned vehicle |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2253835A1 (en) * | 2009-05-18 | 2010-11-24 | Lm Glasfiber A/S | Wind turbine blade with base part having non-positive camber |
| 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 |
| 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 CN201621083454.0U patent/CN206068155U/en not_active Expired - Fee Related
- 2016-11-21 WO PCT/CN2016/106549 patent/WO2018058768A1/en active Application Filing
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109789921A (en) * | 2017-04-07 | 2019-05-21 | 深圳市大疆创新科技有限公司 | Blade, propeller, power suit and unmanned vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018058768A1 (en) | 2018-04-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205554565U (en) | Screw, power component and aircraft | |
| CN206141830U (en) | Screw, power suit and unmanned vehicles | |
| CN205345321U (en) | Screw, power suit and unmanned vehicles | |
| CN205891216U (en) | Screw, power suit and unmanned vehicles | |
| CN205801500U (en) | Propeller, power suit and unmanned vehicle | |
| CN202642093U (en) | Propeller and aircraft with propeller | |
| CN205345320U (en) | Screw, power component and aircraft | |
| CN206202665U (en) | Propeller, Power Component and aircraft | |
| US11554854B2 (en) | Adhesive panels of microvane arrays for reducing effects of wingtip vortices | |
| CN205524939U (en) | Screw, power component and aircraft | |
| JP2016222242A (en) | propeller | |
| WO2017148135A1 (en) | Propeller, power assembly and aircraft | |
| CN205589457U (en) | Screw, power component and aircraft | |
| CN206691356U (en) | Propeller, Power Component and aircraft | |
| CN206155775U (en) | Screw, power component and aircraft | |
| CN207000809U (en) | Blade, propeller, power suit and unmanned vehicle | |
| WO2019200941A1 (en) | Gradient pitch multi-section slotted propeller | |
| CN205418072U (en) | Screw, power component and aircraft | |
| CN207072430U (en) | Propeller, Power Component and aircraft | |
| CN206926806U (en) | Propeller, Power Component and aircraft | |
| CN208993923U (en) | Propeller, Power Component and unmanned vehicle | |
| CN206068155U (en) | Blade, propeller, power suit and unmanned vehicle | |
| CN206202682U (en) | Blade, propeller, power suit and unmanned vehicle | |
| CN206394870U (en) | Propeller, Power Component and aircraft | |
| CN205837193U (en) | Propeller, power suit and unmanned vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190717 Address after: 518005 Baiwang Creative Factory, 1051 Songbai Road, Xili Street, Nanshan District, Shenzhen City, Guangdong Province, 7 101, 102-1 and 201/9 buildings Patentee after: DJI BAIWANG TECHNOLOGY Co.,Ltd. Address before: 518057 Guangdong province Shenzhen city Nanshan District high tech Zone South Hing a No. 9 Hongkong, Shenzhen building 6 floor Patentee before: SZ DJI TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170405 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |