CN207000809U - Blade, propeller, power suit and unmanned vehicle - Google Patents
Blade, propeller, power suit and unmanned vehicle Download PDFInfo
- Publication number
- CN207000809U CN207000809U CN201720364541.1U CN201720364541U CN207000809U CN 207000809 U CN207000809 U CN 207000809U CN 201720364541 U CN201720364541 U CN 201720364541U CN 207000809 U CN207000809 U CN 207000809U
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- Prior art keywords
- blade
- propeller
- gyration
- millimeters
- centre
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- 238000009434 installation Methods 0.000 claims description 19
- 210000003361 heart septum Anatomy 0.000 claims 1
- 238000005516 engineering process Methods 0.000 description 3
- 229910000838 Al alloy 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
- 230000002787 reinforcement Effects 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
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- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/04—Blade mountings
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
The utility model provides a kind of blade, for propeller, it is characterised in that：The distance of the centre of gyration away from the propeller on the blade is at the 58.33% of the radius of gyration of the propeller, and the angle of attack of the blade is 11.48 ± 2.5 degree；The distance of the centre of gyration away from the propeller on the blade is at the 77.38% of the radius of gyration of the propeller, and the angle of attack of the blade is 8.02 ± 2.5 degree；The distance of the centre of gyration away from the propeller on the blade is at the 96.43% of the radius of gyration of the propeller, and the angle of attack of the blade is 6.31 ± 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
It the utility model is related to a kind of blade, the propeller with the blade, the power suit with the propeller
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 as to provide the dynamic of flight for the unmanned vehicle
Power.For propeller of the prior art due to the limitation of appearance profile and structure, its operating efficiency is relatively low, can not meet at work
The demand of expected motive force.
Utility model content
In view of this, it is necessary to a kind of blade with greater efficiency is provided, it is a kind of using the oar to there is a need to offer
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 away from the propeller on the blade is the spiral shell
At revolve the radius of gyration of oar 58.33%, the angle of attack of the blade is 11.48 ± 2.5 degree；Away from the spiral on the blade
The distance of the centre of gyration of oar is at the 77.38% of the radius of gyration of the propeller, and the angle of attack of the blade is 8.02 ± 2.5
Degree；The distance of the centre of gyration away from the propeller on the blade for the propeller the radius of gyration 96.43% at,
The angle of attack of the blade is 6.31 ± 2.5 degree.
Further, the distance of the centre of gyration away from the propeller on the blade is the revolution half of the propeller
At the 39.29% of footpath, the angle of attack of the blade is 17.65 ± 2.5 degree；
And/or the radius of gyration that the distance of the centre of gyration away from the propeller on the blade is the propeller
97.62% at, the angle of attack of the blade is 6.58 ± 2.5 degree.
Further, the tactical diameter of the propeller is 840 millimeters, in the centre of gyration 165 apart from the propeller
At millimeter, the angle of attack of the blade is 17.65 ± 2.5 degree；
And/or at 245 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 11.48 ± 2.5
Degree；
And/or at 325 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 8.02 ± 2.5
Degree；
And/or at 405 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 6.31 ± 2.5
Degree；
And/or at 410 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 6.58 ± 2.5
Degree.
Further, the distance of the centre of gyration away from the propeller on the blade is the revolution half of the propeller
At the 58.33% of footpath, the chord length of the blade is 54.14 ± 5 millimeters；
And/or the radius of gyration that the distance of the centre of gyration away from the propeller on the blade is the propeller
77.38% at, the chord length of the blade is 42.99 ± 5 millimeters；
And/or the radius of gyration that the distance of the centre of gyration away from the propeller on the blade is the propeller
96.43% at, the chord length of the blade is 31.63 ± 5 millimeters.
Further, the distance of the centre of gyration away from the propeller on the blade is the revolution half of the propeller
At the 39.29% of footpath, the chord length of the blade is 68.20 ± 5 millimeters；
And/or the radius of gyration that the distance of the centre of gyration away from the propeller on the blade is the propeller
97.62% at, the chord length of the blade is 30.94 ± 5 millimeters.
Further, the length of the blade is 395 ± 50 millimeters.
Further, the blade is included mutually away from the blade face and blade back set, and the connection blade back and described
First lateral margin of the side on blade face, the second lateral margin for connecting the blade back and the opposite side on the 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 curved outwardly first and arched 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 40 millimeters.
A kind of propeller, the propeller include oar seat and at least one blade as described 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, is provided with installation portion on the blade, the installation portion with it is described
Oar seat connects.
Further, connecting hole is provided with the installation portion, the connecting hole is used to be engaged with fastener, so that institute
The oar seat can be connected to by the fastener by stating installation portion；
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 with the oar seat, the center of the connecting hole and the center of the oar seat
It is spaced pre-determined distance.
Further, the propeller is folds oar, and the quantity of the blade is at least two, and each blade can
It is rotationally connected with the oar seat；
Or the propeller includes the propeller hub being fixedly connected with the blade, the quantity of the blade is at least two.
Further, the geometrical pitch of the propeller is 9 ± 0.5 inches.
Further, the power suit includes at least one propeller as described above and the driving propeller rotational
Actuator.
Further, the actuator is motor, and the propeller is connected on the motor, and the KV values of the motor are
118 turns/(minute volt).
A kind of unmanned vehicle, it includes fuselage, multiple horns and multiple power suits as described above, the multiple machine
Arm is connected with the fuselage, and the multiple power suit is separately mounted on the multiple horn.
Propeller provided by the utility model reduces air resistance by the design of the angle of attack of the different parts to blade
Power, efficiency is improved, and motive force is relatively large.
Brief description of the drawings
Fig. 1 is the structural representation for the power suit that the utility model embodiment provides.
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 embodiment will further illustrate the utility model with reference to above-mentioned accompanying drawing.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describing, it is clear that described embodiment is only the utility model part of the embodiment, 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 obtained, belong 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 be directly on another component
Or there may also be component placed in the middle.When a component is considered as " connection " another component, it can be directly connected to
To another component or it 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 belonging to technology of the present utility model
The implication that the technical staff in domain is generally understood that is identical.It is simply in term used in the description of the present utility model herein
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 combination of one or more related Listed Items.
During the utility model is realized, inventor is found that following problem：
(1) efficiency of propeller is relevant with the angle of attack chord length of propeller, therefore, shape and knot of the inventor in propeller
It is made that emphasis improves in terms of structure.
(2) especially, the angle of attack and chord length shadow of the efficiency of propeller by (40%~90% region) in the middle part of propeller
Ring, therefore, inventor makes improvement in the middle part emphasis of propeller.
(3) shape of propeller and structure directly influence its when rotated it is caused promotion force direction and motive force it is big
It is small, therefore, inventor is made that some improvement 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 at the 58.33% of the radius of gyration of the propeller, and the angle of attack of the blade is 11.48 ± 2.5 degree；
The distance of the centre of gyration away from the propeller on the blade is institute at the 77.38% of the radius of gyration of the propeller
The angle of attack for stating blade is 8.02 ± 2.5 degree；The distance of the centre of gyration away from the propeller on the blade is the spiral
At the 96.43% of the radius of gyration of oar, the angle of attack of the blade is 6.31 ± 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 are connected on the motor, the motor is used to drive the propeller rotational, the motor
KV values be 118 turns/(minute volt).The propeller includes blade, in the revolution away from the propeller on the blade
The distance of the heart is at the 77.38% of the radius of gyration of the propeller, and the angle of attack of the blade is 8.02 ± 2.5 degree；Described
The distance of the centre of gyration away from the propeller on blade is the blade at the 96.43% of the radius of gyration of the propeller
The angle of attack be 6.31 ± 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 are 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
Oar to be revolved to rotate, the KV values of the motor are 118 turns/(minute volt).The propeller includes blade, on the blade away from
The distance of the centre of gyration of the propeller is that the angle of attack of the blade is at the 77.38% of the radius of gyration of the propeller
8.02 ± 2.5 degree；The distance of the centre of gyration away from the propeller on the blade is the radius of gyration of the propeller
At 96.43%, the angle of attack of the blade is 6.31 ± 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 and embodiment stated can be mutually combined.
The unmanned vehicle that the embodiment of the utility model one provides, it includes fuselage, horn, propeller and for driving
The actuator of the propeller rotational, the horn are connected with the fuselage.It is appreciated that in some embodiments, institute
It can be to fold oar to state propeller.The quantity of the propeller can according to be actually needed selection, can be one, two or
It is multiple.In present embodiment, the actuator is motor, the KV values of the motor for 118 turns/(minute volt)；It can manage
Solution, in other embodiments, the KV values of the motor can need to choose according to the flight of reality；The actuator can be
Other forms, such as engine.
The propeller can be positive oar or anti-oar.So-called positive oar, refer to from the afterbody of actuator such as motor to motor head
Portion sees in direction, and rotate counterclockwise is to produce the propeller of lift；So-called anti-oar, refer in terms of from motor afterbody to motor head direction,
Turn clockwise to produce the propeller of lift.The positive specular between the structure of oar and the structure of the anti-oar, therefore under
Text only illustrates the structure of the propeller by taking positive oar as an example.
Referring to Fig. 1, the structural representation for the power suit that Fig. 1, which is the utility model embodiment, to be provided.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
Oar 300 and actuator 400 are revolved, the propeller 300 and the actuator 400 are multiple, and each actuator 400 drives
Move a propeller 300 to rotate, form 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) propellers 300.
In addition, the orientation term such as upper and lower occurred in the description of the utility model embodiment is with the propeller 300
The normal operational attitude of the propeller 300 and the aircraft is reference after being installed on the aircraft, without answering
State and think restrictive.
Please refer to Fig. 2 to Fig. 4, the blade for the propeller 300 that the utility model embodiment provides is shown in figure
100 structural representation.The propeller 300 includes oar seat (not shown) and is arranged at two oars of the oar seat both sides
Leaf 100, two blades 100 are centrosymmetric setting on 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 and the center of the oar disk essentially coincide.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 the 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 the oar seat.In one embodiment,
Substantially 40 millimeters of the distance between center O of the center of the connecting hole 103 and the oar seat.It is appreciated that other one
In a little embodiments, the distance between the center of the connecting hole 103 and center of the oar seat can be set according to being actually needed
Put, it is not limited to described by the utility model embodiment.Even, in certain embodiments, the installation portion 101 and the company
Connecing hole 103 can omit.
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 by connector, not
It is confined to described in the utility model embodiment.It can also be appreciated that according to being actually needed, each 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, 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 840 ± 5 millimeters of the oar disk.Specifically, the diameter of the oar disk can be
835 millimeters, 837.5 millimeters, 840 millimeters, 842.5 millimeters, 845 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 840 millimeters of the oar disk.Due to the oar
Disk is the effect for being rotated by the blade 100 and the oar seat and being formed, it is above and be hereinafter previously mentioned " 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 of the unmanned vehicle 400, 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
Heart symmetry shape is arranged on the both sides of the oar seat, and each connection between the blade 100 and the oar seat connects in shape of threads
Connect.In the present embodiment, the geometrical pitch of the propeller 300 is 9 ± 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 8.5 English
It is very little, 8.6 inches, 8.7 inches, 8.8 inches, 8.9 inches, 9.0 inches, 9.1 inches, 9.2 inches, 9.3 inches, 9.4 inches,
9.5 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 are 9 inches.
The blade 100 is included mutually away from the blade face 10 and blade back 20 set, and the connection blade back 20 and described
First lateral margin 30 of the side on blade face 10, the second lateral margin 40 for connecting the blade back 20 and the opposite side on the 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 (referring 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 set down；And the blade back 20 deviates from the actuator 400, that is, the blade back 20 is set 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 other parts for arching upward portion 31 and first lateral margin 30 are connected smoothly.In this reality
Apply in mode, described first portion 31 that arches upward is set adjacent to the oar seat.Second lateral margin 40 includes curved outwardly
Second arch upward portion 41, the described second other parts for arching upward portion 41 and second lateral margin 40 are connected smoothly.In this reality
Apply in mode, described second portion 41 that arches upward is set adjacent to the oar seat.
In the propeller 300 that the utility model embodiment is provided, nothing drastically reverses part on the blade 100,
Stress is smaller, and structural strength is higher, is not easily broken, and reliability is high.The one end of the blade 100 away from the oar seat is the oar
The most thin part of leaf 100, be advantageous to reduce air drag.That is, the thickness of the one end at described center of the blade 100 away from the oar disk
Thickness of the degree less than the other parts of blade 100.
In present embodiment, the length of the blade 100 is 395 ± 5 millimeters.The length of the blade 100 can be 390
Millimeter to the arbitrary value between 400 millimeters, such as 390 millimeters, 392.5 millimeters, 395 millimeters, 397.5 millimeters, 400 millimeters, or
Person, the arbitrary value in number range that the length of the blade 100 can be defined by above-mentioned any two numerical value.Preferably,
The length of the blade 100 is 395 millimeters.
The angle of attack referred to herein, refer 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 away from the oar disk on the blade 100 is the oar disk half
At the 39.29% of footpath, the angle of attack 1 of the blade 100 is 17.65 ± 2.5 degree.Specifically, the angle of attack of blade 100 described herein
1 can be 15.15 degree, 16.15 degree, 17.40 degree, 17.65 degree, 17.90 degree, 19.15 degree, 20.15 degree, or, it is described herein
The arbitrary value in number range that the angle of attack 1 of blade 100 can be defined by above-mentioned any two numerical value, in present embodiment
In, the angle of attack 1 is 17.65 degree.The distance of center O away from the oar disk on the blade 100 is the oar disk radius
At 39.29%, the chord length L1 of the blade 100 is 68.20 ± 5 millimeters.Specifically, the chord length L1 of blade 100 described herein can
Think 63.20 millimeters, 64.20 millimeters, 67.20 millimeters, 68.20 millimeters, 69.20 millimeters, 71.20 millimeters, 73.20 millimeters, or
Person, the numerical value in number range that the chord length L1 of blade 100 described herein can be defined by above-mentioned any two numerical value, at this
In embodiment, the chord length L1 is 68.20 millimeters.
Please refer to Fig. 6 and Fig. 8, the distance of the center O away from the oar disk on the blade 100 is the oar disk half
At the 58.33% of footpath, the angle of attack 2 of the blade 100 is 11.48 ± 2.5 degree.Specifically, the angle of attack of blade 100 described herein
2 can be 8.02 degree, 9.02 degree, 10.02 degree, 11.48 degree, 11.98 degree, 12.98 degree, 13.98 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 11.48 degree.The distance of center O away from the oar disk on the blade 100 is the oar disk radius
At 58.33%, the chord length L2 of the blade 100 is 54.14 ± 5 millimeters.Specifically, the chord length L2 of blade 100 described herein can
Think 49.14 millimeters, 50.14 millimeters, 52.14 millimeters, 54.14 millimeters, 55.14 millimeters, 57.14 millimeters, 59.14 millimeters, or
Person, specifically, appointing in the number range that the chord length L2 of blade 100 described herein can be defined by above-mentioned any two numerical value
Meaning value, in the present embodiment, the chord length L2 are 54.14 millimeters.
Please refer to Fig. 6 and Fig. 9, the distance of the center O away from the oar disk on the blade 100 is the oar disk half
At the 77.38% of footpath, the angle of attack 3 of the blade 100 is 8.02 ± 2.5 degree.Specifically, the angle of attack 3 of blade 100 described herein
Can be 5.52 degree, 6.52 degree, 7.52 degree, 8.02 degree, 9.02 degree, 10.02 degree, 10.52 degree, or, blade 100 described herein
The number range that can be defined by above-mentioned any two numerical value of angle of attack 3 in arbitrary value, it is in the present embodiment, described
Angle of attack 3 is 8.02 degree.The distance of center O away from the oar disk on the blade 100 is the 77.38% of the oar disk radius
Place, the chord length L3 of the blade 100 is 42.99 ± 5 millimeters.Specifically, the chord length L3 of blade 100 described herein can be
37.99 millimeters, 38.99 millimeters, 40.99 millimeters, 42.99 millimeters, 43.99 millimeters, 45.99 millimeters, 47.99 millimeters, or, this
Locate the arbitrary value in the number range that the chord length L3 of the blade 100 can be defined by above-mentioned any two numerical value, in this reality
Apply in mode, the chord length L3 is 42.99 millimeters.
Please refer to Fig. 6 and Figure 10, the distance of the center O away from the oar disk on the blade 100 is the oar disk
At the 96.43% of radius, the angle of attack 4 of the blade 100 is 6.31 ± 2.5 degree.Specifically, the angle of attack of blade 100 described herein
α 4 can be 3.81 degree, 4.81 degree, 5.81 degree, 6.31 degree, 6.81 degree, 7.81 degree, 8.81 degree, or, blade 100 described herein
The number 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 6.31 degree.The distance of center O away from the oar disk on the blade 100 is the 96.43% of the oar disk radius
Place, the chord length L4 of the blade 100 is 31.63 ± 5 millimeters.Specifically, the chord length L4 of blade 100 described herein can be
26.63 millimeters, 27.63 millimeters, 29.63 millimeters, 31.63 millimeters, 32.63 millimeters, 34.63 millimeters, 36.63 millimeters, or, this
Locate the arbitrary value in the number range that the chord length L4 of the blade 100 can be defined by above-mentioned any two numerical value, in this reality
Apply in mode, the chord length L4 is 31.63 millimeters.
Please refer to Fig. 6 and Figure 11, the distance of the center O away from the oar disk on the blade 100 is the oar disk
At the 97.62% of radius, the angle of attack 5 of the blade 100 is 6.58 ± 2.5 degree.Specifically, the angle of attack of blade 100 described herein
α 5 can be 4.08 degree, 5.08 degree, 6.08 degree, 6.58 degree, 6.08 degree, 7.08 degree, 9.08 degree, or, blade 100 described herein
The number 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 6.58 degree.The distance of center O away from the oar disk on the blade 100 is the 97.62% of the oar disk radius
Place, the chord length L5 of the blade 100 is 30.94 ± 5 millimeters.Specifically, the chord length L5 of blade 100 described herein can be
25.94 millimeters, 26.94 millimeters, 28.94 millimeters, 30.94 millimeters, 31.94 millimeters, 33.94 millimeters, 35.94 millimeters, or, this
Locate the arbitrary value in the number range that the chord length L5 of the blade 100 can be defined by above-mentioned any two numerical value, in this reality
Apply in mode, the chord length L5 is 30.94 millimeters.
Referring to Fig. 6 to Figure 11, in the present embodiment, a diameter of 840 millimeters of the oar disk.In the blade
On 100 at 165 millimeters of oar disk center described in distance, the angle of attack 1 of the blade 100 is 17.65 degree, the chord length of the blade 100
L1 is 68.20 millimeters；At 245 millimeters of the center apart from the oar disk, the angle of attack 2 of the blade 100 is 11.48 degree, described
The chord length L2 of blade 100 is 54.14 millimeters；At 325 millimeters of the center apart from the oar disk, the angle of attack 3 of the blade 100
For 8.02 degree, the chord length L3 of the blade 100 is 42.99 millimeters；At 405 millimeters of the center apart from the oar disk, the oar
The angle of attack 4 of leaf 100 is 6.31 degree, and the chord length L4 of the blade 100 is 31.63 millimeters；Apart from the center 410 of the oar disk
At millimeter, the angle of attack 5 of the blade 100 is 6.58 degree, and the chord length L5 of the blade 100 is 30.94 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
The propeller that embodiment of the present utility model provides it can be seen from table needs under identical pulling force size
The power wanted is smaller, so as to save electric quantity consumption, adds the endurance distance of unmanned vehicle, improves efficiency.
Propeller provided by the utility model reduces air resistance by the design of the angle of attack of the different parts to blade
Power, efficiency is improved, add the endurance distance of aircraft and improve 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 to restriction of the present utility model, as long as 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 requires of the utility model protection.
Claims (17)
- A kind of 1. blade, in propeller, it is characterised in that：The centre of gyration away from the propeller on the blade away from At 58.33% of the radius of gyration for the propeller, the angle of attack of the blade is 11.48 ± 2.5 degree；On the blade The distance of the centre of gyration away from the propeller is the angle of attack of the blade at the 77.38% of the radius of gyration of the propeller For 8.02 ± 2.5 degree；The distance of the centre of gyration away from the propeller on the blade is the radius of gyration of the propeller 96.43% at, the angle of attack of the blade is 6.31 ± 2.5 degree.
- 2. blade as claimed in claim 1, it is characterised in that：The centre of gyration away from the propeller on the blade away from At 39.29% of the radius of gyration for the propeller, the angle of attack of the blade is 17.65 ± 2.5 degree；And/or the distance of the centre of gyration away from the propeller on the blade is the radius of gyration of the propeller At 97.62%, the angle of attack of the blade is 6.58 ± 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 840 Millimeter, at 165 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 17.65 ± 2.5 degree；And/or at 245 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 11.48 ± 2.5 degree；And/or at 325 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 8.02 ± 2.5 degree；And/or at 405 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 6.31 ± 2.5 degree；And/or at 410 millimeters of the centre of gyration apart from the propeller, the angle of attack of the blade is 6.58 ± 2.5 degree.
- 4. blade as claimed in claim 1, it is characterised in that：The centre of gyration away from the propeller on the blade away from At 58.33% of the radius of gyration for the propeller, the chord length of the blade is 54.14 ± 5 millimeters；And/or the distance of the centre of gyration away from the propeller on the blade is the radius of gyration of the propeller At 77.38%, the chord length of the blade is 42.99 ± 5 millimeters；And/or the distance of the centre of gyration away from the propeller on the blade is the radius of gyration of the propeller At 96.43%, the chord length of the blade is 31.63 ± 5 millimeters.
- 5. blade as claimed in claim 4, it is characterised in that：The centre of gyration away from the propeller on the blade away from At 39.29% of the radius of gyration for the propeller, the chord length of the blade is 68.20 ± 5 millimeters；And/or the distance of the centre of gyration away from the propeller on the blade is the radius of gyration of the propeller At 97.62%, the chord length of the blade is 30.94 ± 5 millimeters.
- 6. blade as claimed in claim 1, it is characterised in that：The length of the blade is 395 ± 50 millimeters.
- 7. blade as claimed in claim 1, it is characterised in that：The blade includes mutually deviating from the blade face set and blade back, And connect the first lateral margin of the side on the blade back and the blade face, connect the blade back and the opposite side on the blade face 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 curved outwardly second and arched 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 40 millimeters.
- A kind of 11. propeller, it is characterised in that：The propeller includes appointing in oar seat and at least one such as claim 1-10 Blade described in one, installation portion is provided with the blade, the installation portion is connected with the oar seat.
- 12. propeller 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；It is described 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 Installation portion can be connected by the connecting hole with the oar seat, the center of the connecting hole and the middle heart septum of the oar seat Pre-determined distance.
- 13. propeller as claimed in claim 11, it is characterised in that：The propeller is to fold oar, the quantity of the blade For at least two, each blade can be rotationally connected with the oar seat；Or the propeller includes the propeller hub being fixedly connected with the blade, the quantity of the blade is at least two.
- 14. propeller as claimed in claim 11, it is characterised in that：The geometrical pitch of the propeller is 9 ± 0.5 inches.
- A kind of 15. power suit of unmanned vehicle, 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 suit 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 118 turns/(minute volt).
- 17. a kind of unmanned vehicle, it includes 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 |
|---|---|---|---|
| CN201720364541.1U CN207000809U (en) | 2017-04-07 | 2017-04-07 | Blade, propeller, power suit and unmanned vehicle |
| CN201780060396.0A CN109789921A (en) | 2017-04-07 | 2017-06-14 | Blade, propeller, power suit and unmanned vehicle |
| PCT/CN2017/088335 WO2018184291A1 (en) | 2017-04-07 | 2017-06-14 | Blade, propeller, power kit, and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720364541.1U CN207000809U (en) | 2017-04-07 | 2017-04-07 | Blade, propeller, power suit and unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207000809U true CN207000809U (en) | 2018-02-13 |
Family
ID=61442222
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720364541.1U Expired - Fee Related CN207000809U (en) | 2017-04-07 | 2017-04-07 | Blade, propeller, power suit and unmanned vehicle |
| CN201780060396.0A Pending CN109789921A (en) | 2017-04-07 | 2017-06-14 | Blade, propeller, power suit and unmanned vehicle |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780060396.0A Pending CN109789921A (en) | 2017-04-07 | 2017-06-14 | Blade, propeller, power suit and unmanned vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN207000809U (en) |
| WO (1) | WO2018184291A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750074A (en) * | 2018-03-30 | 2018-11-06 | 中山市朗宇模型有限公司 | propeller |
| CN112572766A (en) * | 2020-12-17 | 2021-03-30 | 重庆工程职业技术学院 | Water vapor propeller of unmanned aerial vehicle on water and processing technology thereof |
| CN113022849A (en) * | 2021-05-28 | 2021-06-25 | 北京三快在线科技有限公司 | Propeller and rotor craft |
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| DE3328116A1 (en) * | 1983-08-04 | 1985-02-14 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Rotor, especially of a rotary-wing aircraft |
| FR2689852B1 (en) * | 1992-04-09 | 1994-06-17 | Eurocopter France | BLADE FOR AIRCRAFT TURNING WING, AT THE ARROW END. |
| DE19528155C1 (en) * | 1995-08-02 | 1996-06-27 | Deutsche Forsch Luft Raumfahrt | Helicopter rotor blade of glass fibre reinforced synthetic resin |
| US6641365B2 (en) * | 1998-02-20 | 2003-11-04 | Abraham E. Karem | Optimum speed tilt rotor |
| CN101157380A (en) * | 2007-11-14 | 2008-04-09 | 吴官举 | Vane wheel oar |
| US8646721B2 (en) * | 2008-05-07 | 2014-02-11 | Entecho Pty Ltd. | Fluid dynamic device with thrust control shroud |
| EP2519439B1 (en) * | 2009-12-28 | 2018-01-24 | GKN Aerospace Sweden AB | Air propeller arrangement and aircraft |
| GB2486021B (en) * | 2010-12-02 | 2017-07-19 | Agustawestland Ltd | Aerofoil |
| US9446843B2 (en) * | 2012-03-27 | 2016-09-20 | The Boeing Company | Enhanced performance rotorcraft rotor blade |
| CN102963522B (en) * | 2012-10-31 | 2015-04-22 | 中国航天空气动力技术研究院 | Near space propeller |
| ITPD20120369A1 (en) * | 2012-12-06 | 2014-06-07 | Vortex Energy S R L | WIND TURBINE WITH VERTICAL AXIS AND SHOVEL FOR WIND TURBINE WITH VERTICAL AXIS |
| CN204173156U (en) * | 2014-08-25 | 2015-02-25 | 深圳市兴天翼科技有限公司 | Screw propeller |
| CN205418068U (en) * | 2015-10-13 | 2016-08-03 | 河南卓尔航空科技有限公司 | Screw device |
| 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 |
| 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 |
| 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 |
| CN205837193U (en) * | 2016-07-28 | 2016-12-28 | 深圳市大疆创新科技有限公司 | Propeller, power suit and unmanned vehicle |
| CN205891216U (en) * | 2016-08-04 | 2017-01-18 | 深圳市大疆创新科技有限公司 | Screw, power suit and unmanned vehicles |
| CN206068155U (en) * | 2016-09-27 | 2017-04-05 | 深圳市大疆创新科技有限公司 | Blade, propeller, power suit and unmanned vehicle |
-
2017
- 2017-04-07 CN CN201720364541.1U patent/CN207000809U/en not_active Expired - Fee Related
- 2017-06-14 CN CN201780060396.0A patent/CN109789921A/en active Pending
- 2017-06-14 WO PCT/CN2017/088335 patent/WO2018184291A1/en active Application Filing
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750074A (en) * | 2018-03-30 | 2018-11-06 | 中山市朗宇模型有限公司 | propeller |
| CN112572766A (en) * | 2020-12-17 | 2021-03-30 | 重庆工程职业技术学院 | Water vapor propeller of unmanned aerial vehicle on water and processing technology thereof |
| CN113022849A (en) * | 2021-05-28 | 2021-06-25 | 北京三快在线科技有限公司 | Propeller and rotor craft |
| CN113022849B (en) * | 2021-05-28 | 2024-02-06 | 北京三快在线科技有限公司 | Propeller and rotary wing aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109789921A (en) | 2019-05-21 |
| WO2018184291A1 (en) | 2018-10-11 |
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| 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: 20180213 |