CN206691356U - Propeller, Power Component and aircraft - Google Patents
Propeller, Power Component and aircraft Download PDFInfo
- Publication number
- CN206691356U CN206691356U CN201720191484.1U CN201720191484U CN206691356U CN 206691356 U CN206691356 U CN 206691356U CN 201720191484 U CN201720191484 U CN 201720191484U CN 206691356 U CN206691356 U CN 206691356U
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- Prior art keywords
- blade
- propeller
- oar
- attack
- oar disk
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- 230000000630 rising effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
Abstract
The utility model provides a kind of propeller, Power Component and aircraft, and wherein propeller includes oar seat and the blade being connected on the oar seat；The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 59.32% of oar disk radius is 14.05 ° ± 2.5 °, chord length is 11.94mm ± 5mm；The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 76.27% of oar disk radius is 11.44 ° ± 2.5 °, chord length is 10.25mm ± 5mm；The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 93.22% of oar disk radius is 9.99 ° ± 2.5 °, chord length is 8.64mm ± 5mm.Propeller, Power Component and aircraft provided by the utility model, resistance of the propeller in rotation process can be reduced, improve the flying quality of aircraft.
Description
Technical field
It the utility model is related to propeller arrangement technology, more particularly to a kind of propeller, Power Component and aircraft.
Background technology
Carry-on propeller, as the important Primary Component of aircraft, it is used for rotating shaft in motor or engine
Rotation be converted into thrust or lift.
Propeller of the prior art, its blade outer shape is mostly rectangular, and resistance is big when causing its flight, efficiency
It is low, cause that the flying speed of aircraft is small, endurance distance is short, had a strong impact on the flying quality of aircraft.
Utility model content
The utility model provides a kind of propeller, Power Component and aircraft, of the prior art above-mentioned scarce to solve
Fall into, reduce the flight resistance of propeller, improve the flight efficiency of propeller, improve the flying quality of aircraft.
On the one hand the utility model provides a kind of propeller, including blade, the blade rotates to form oar disk；
The blade with the propeller shape into oar disk center at a distance of for oar disk radius 59.32% at the angle of attack
For 14.05 ° ± 2.5 °, chord length is 11.94mm ± 5mm；
The blade with the propeller shape into oar disk center at a distance of for oar disk radius 76.27% at the angle of attack
For 11.44 ° ± 2.5 °, chord length is 10.25mm ± 5mm；
The blade with the propeller shape into oar disk center at a distance of for oar disk radius 93.22% at the angle of attack
For 9.99 ° ± 2.5 °, chord length is 8.64mm ± 5mm.
Propeller as described above, the propeller shape into a diameter of 118mm of oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 35mm is 14.05 °, chord length
For 11.94mm；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 45mm is 11.44 °, string
A length of 10.25mm；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 55mm is 9.99 °, chord length
For 8.64mm.
Propeller as described above,
The blade with the propeller shape into oar disk center at a distance of for oar disk radius 42.37% at the angle of attack
For 16.61 ° ± 2.5 °, chord length is 13.48mm ± 5mm.
Propeller as described above, the propeller shape into a diameter of 118mm of oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 25mm is 16.61 °, string
A length of 13.48mm.13.48mm
Propeller as described above,
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 100% of oar disk radius is
9.61 ° ± 2.5 °, chord length is 8.34mm ± 5mm.
Propeller as described above, the propeller shape into a diameter of 118mm of oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 59mm is 9.61 °, chord length
For 8.34mm.
Propeller as described above, the propeller also include oar seat, and the blade is detachably connected with the oar seat.
Propeller as described above, the quantity of the blade are at least two, and at least two blade is along the oar seat
Circumferentially it is uniformly distributed.
Propeller as described above, from the blade close to one end of the oar disk center to the blade away from the oar
One end of disk center, the thickness of the blade are gradually reduced.
Propeller as described above, the blade includes blade back upward, blade face directed downwardly, and is connected to the blade back
And the first lateral margin between the side on the blade face and be connected between the blade back and the opposite side on the blade face second
Lateral margin, first lateral margin are located at below second lateral margin；The blade back and the blade face are curved surface；The propeller
Also include oar seat, the blade is detachably connected with the oar seat.
Propeller as described above, first lateral margin include one curved outwardly first portion that arches upward, institute
Stating the second lateral margin includes one curved outwardly second portion that arches upward；Described first, which arches upward, portion and described second arches upward portion
It is close to one end that the blade is connected with the oar seat；And described first the protrusion degree for arching upward portion arched upward more than described second
The protrusion degree in portion.
Propeller as described above, the pitch of the propeller is 30 inches.
On the other hand the utility model also provides a kind of Power Component, including actuator and the spiral described in any of the above-described
Oar, the propeller are connected by oar seat with the actuator.
Power Component as described above, the actuator are motor, and the KV values of the motor are 2100 turns/(minute volt
It is special).
The another aspect of the utility model also provides a kind of aircraft, including fuselage, in addition at least one as above any one
Described Power Component, the Power Component are connected with the fuselage.
The aircraft includes multiple Power Components, and the rotation direction of the multiple Power Component is different.
Propeller, Power Component and aircraft provided by the utility model, due to blade with propeller shape into oar disk
Center at a distance of being that the angle of attack at the 59.32% of oar disk radius is 14.05 ° ± 2.5 °, chord length is 11.94mm ± 5mm；It is described
Blade with the propeller shape into oar disk center at a distance of be the angle of attack at the 76.27% of oar disk radius be 11.44 ° ±
2.5 °, chord length is 10.25mm ± 5mm；The blade with the propeller shape into oar disk center at a distance of being oar disk radius
93.22% at the angle of attack be 9.99 ° ± 2.5 °, chord length is 8.64mm ± 5mm.Therefore propeller can be reduced rotating
Resistance in journey, reduce the flight resistance during aircraft flight, improve flight efficiency, increase endurance distance, improve flight
The flying quality of device.
Brief description of the drawings
Fig. 1 is the stereogram of blade in the propeller that the utility model embodiment one provides；
Fig. 2 is the front view of blade shown in Fig. 1；
Fig. 3 is the left view of blade shown in Fig. 1；
Fig. 4 is the right view of blade shown in Fig. 1；
Fig. 5 is the upward view of blade shown in Fig. 1；
Fig. 6 is the top view of blade shown in Fig. 1；
Fig. 7 is diagrammatic cross-section of the blade along line A-A in Fig. 2；
Fig. 8 is diagrammatic cross-section of the blade along line B-B in Fig. 2；
Fig. 9 is diagrammatic cross-section of the blade along line C-C in Fig. 2；
Figure 10 is diagrammatic cross-section of the blade along line D-D in Fig. 2；
Figure 11 is diagrammatic cross-section of the blade along E-E lines in Fig. 2.
Reference：
1- blades；2- connecting holes；3- blade faces
4- blade backs；The lateral margins of 5- first；The lateral margins of 6- second；
501- first arches upward portion；601- second arches upward portion.
Embodiment
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, the technical scheme in the embodiment of the utility model is clearly and completely described, it is clear that is retouched
The embodiment stated is the utility model part of the embodiment, rather than whole embodiments.Based on the implementation in the utility model
Example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made, is belonged 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.
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.
Embodiment one
The utility model embodiment one provides a kind of propeller.Propeller in the present embodiment, can apply to aircraft,
Propeller can include：Oar seat and the blade being connected on oar seat.
In the present embodiment, propeller can be positive oar or anti-oar, so-called positive oar, refer to from the angle for overlooking aircraft
See, dextrorotation transfers to produce the propeller of lift；So-called anti-oar, refer to from the point of view of aircraft is overlooked, counterclockwise rotation
Then produce the propeller of lift.It is symmetrical for minute surface just between the structure of oar and the structure of anti-oar, only with positive oar in the present embodiment
Structure exemplified by the structure of propeller is illustrated, the mode that those skilled in the art can be provided according to the present embodiment is entered
Row extends and obtains the structure of anti-oar.
In the propeller that the present embodiment provides, blade and oar seat can be formed in one structure, or can also pass through it
Its mode realizes interconnection, such as can be fixed by the form of welding, or can be fixed by dismountable connector
Connection, such as the fixation that is spirally connected, or realize connection etc. by other connectors.The number of blade can be one or more, multiple
Blade can arrange that the present embodiment is preferable along the circumferential uniform intervals of oar seat, and the quantity of blade is at least two, at least two
Circumference of the blade along oar seat is uniformly distributed.Can be formed in one structure between multiple blades, or, can also be each independent,
The utility model is not limited specifically this.
Fig. 1 is the stereogram of blade in the propeller that the utility model embodiment one provides；Fig. 2 is blade shown in Fig. 1
Front view；Fig. 3 is the left view of blade shown in Fig. 1；Fig. 4 is the right view of blade shown in Fig. 1；Fig. 5 is facing upward for blade shown in Fig. 1
View；Fig. 6 is the top view of blade shown in Fig. 1.As shown in Figures 1 to 6, the blade of the propeller in the present embodiment, can wrap
Include blade back 4 upward, blade face directed downwardly 3, and be connected between the side on blade back 4 and blade face 3 the first lateral margin 5, Yi Jilian
The second lateral margin 6 being connected between blade back 4 and the opposite side on blade face 3, the first lateral margin 5 are located at the lower section of the second lateral margin 6；Blade back 4 and
Blade face 3 is curved surface.
Wherein, blade back 4 be aircraft in flight course, the one side of blade 1 upward；Blade face 3 is that aircraft was flying
Cheng Zhong, 1 one side directed downwardly of blade.As shown in Figure 3 and Figure 4, blade back 4 and blade face 3 are curved surface, and the trend bent is：Work as oar
When leaf 1 is generally in horizontality, the location of first lateral margin 5 is lower than the location of the second lateral margin 6.
First lateral margin 5 can include curved outwardly first and arch upward portion 501, and first arches upward portion 501 and first
The remainder of lateral margin 5 is to be connected smoothly.On the length direction of whole blade 1, relative to one of blade 1 away from oar seat
End, first arches upward one end that portion 501 is connected closer to blade 1 with oar seat.First arches upward portion 501 not only towards the side arch of blade 1
Rise, while can also arch upward downwards, i.e., arched upward towards the direction where blade face 3, and the company of seamlessly transitting can be formed with blade face 3
Connect.
Second lateral margin 6 can include one curved outwardly second portion 601 that arches upward, second arch upward portion 601 with
The remainder of second lateral margin 6 is to be connected smoothly.On the length direction of whole blade 1, relative to blade 1 away from oar seat
One end, second arches upward one end that portion 601 is connected closer to blade 1 with oar seat.
In the present embodiment, the first protrusion degree for arching upward portion 501 can be more than the second protrusion degree that arch upward portion 601.
First arches upward the summit in portion 501 and the second summit for arching upward portion 601 is located substantially on the same cross section of blade 1.Also,
The each opening position in surface of blade 1 is to seamlessly transit, and without part is drastically reversed, therefore has less stress, and intensity compared with
Height is not easily broken, and whole propeller has higher reliability.
Circle of the propeller that the present embodiment is provided formed in rotary course, referred to as oar disk, the center of the circle are referred to as
The center of oar disk, the diameter of a circle are referred to as the diameter of oar disk.For split type blade 1, the radius of oar disk can be more than
The length of blade 1.
From blade 1 close to one end of oar disk center to the one end of blade 1 away from oar disk center, the thickness of blade 1 can be by
It is decrescence small.Thus, the end in blade 1 from oar disk center farthest is part most thin in blade 1, thus is advantageously reduced winged
Air drag during row, improve flight efficiency.
Fig. 7 is diagrammatic cross-section of the blade along line A-A in Fig. 2；Fig. 8 is diagrammatic cross-section of the blade along line B-B in Fig. 2；
Fig. 9 is diagrammatic cross-section of the blade along line C-C in Fig. 2；Figure 10 is diagrammatic cross-section of the blade along line D-D in Fig. 2；Figure 11 is figure
Diagrammatic cross-section of the blade along E-E lines in 2.
As shown in Fig. 7 to Figure 11, the present embodiment can be improved to the size at five sections of blade, wherein, it is right
The improvement that size at section B-B, C-C sections and D-D sections is carried out is mostly important.
Specifically, as shown in Figure 2 and Figure 8, blade 1 with propeller shape into oar disk center at a distance of for oar disk radius
At 59.32%, i.e.,：It is as shown in Figure 2 at oar disk center L2 section B-B, at this angle of attack A2 of blade 1 be 14.05 ° ±
2.5 °, chord length D2 is 11.94mm ± 5mm；Wherein, chord length is the length that the section of blade 1 in this place projects in the horizontal direction,
The angle of attack is the string wing and the angle of gas direction of flow.
As shown in Figure 2 and Figure 9, blade 1 with propeller shape into oar disk center at a distance of be oar disk radius 76.27%
Place, i.e.,：It is as shown in Figure 2 at oar disk center L3 C-C sections, angle of attack A3 of blade 1 is 11.44 ° ± 2.5 ° at this, string
Long D3 is 10.25mm ± 5mm.
As shown in figs. 2 and 10, blade 1 with propeller shape into oar disk center at a distance of for oar disk radius
At 93.22%, i.e.,：It is as shown in Figure 2 at oar disk center L4 D-D sections, angle of attack of blade 1 is that A4 is 9.99 ° at this
± 2.5 °, chord length D4 is 8.64mm ± 5mm.
The present embodiment is by that to the chord length in above three section in blade 1 and the setting of the angle of attack, can reduce propeller and exist
Resistance in rotation process, improve the flying speed and flight efficiency of aircraft, under certain power conditions supply increase after
Boat distance, improve the flying quality of aircraft.
, can also be to Section A-A in blade 1 and the angle of attack chord progress in E-E sections on the basis of above-mentioned technical proposal
Row optimization, further to reduce air drag of the propeller in rotation process.
As shown in Figure 2 and Figure 7, blade 1 with propeller shape into oar disk center at a distance of be oar disk radius 42.37%
Place, i.e.,：It is as shown in Figure 2 at oar disk center L1 Section A-A, angle of attack of blade 1 is 16.61 ° ± 2.5 ° at this, chord length
For 13.48mm ± 5mm.
As shown in figs. 2 and 11, blade 1 with propeller shape into oar disk center at a distance of be oar disk radius 100%
Place, i.e.,：It is as shown in Figure 2 at oar disk center L5 E-E sections, angle of attack of blade 1 is 9.61 ° ± 2.5 ° at this, chord length
For 8.34mm ± 5mm.
Certainly, it will be appreciated by persons skilled in the art that above-mentioned Section A-A, section B-B, C-C sections, D-D sections
Can slightly it be changed with the position in E-E sections.
For above-mentioned technical proposal, the present embodiment provides a kind of specific propeller, and the oar disk that the propeller is formed is straight
Footpath is 118mm, and the distance of oar disk center to the end of blade 1 is the half of oar disk diameter, Ji Jiang disk center to the end of blade 1 away from
From for 59mm.
By taking oar disk diameter 118mm as an example, blade 1 with propeller shape into oar disk center at a distance of at 35mm (i.e.
The 59mm angle of attack 59.32%) is 14.05 °, chord length 11.94mm；Blade 1 with propeller shape into oar disk center phase
It is 11.44 ° away from the angle of attack for (i.e. the 76.27% of 59mm) at 45mm, chord length 10.25mm；Blade 1 with propeller shape into
The center of oar disk is apart that the angle of attack of (i.e. the 93.22% of 59mm) at 55mm is 9.99 °, chord length 8.64mm.
Further, it is 16.61 ° in the angle of attack with oar disk center distance 35mm (i.e. the 38.9% of 59mm) place, blade 1,
Chord length is 13.48mm.It is 9.61 ° in the angle of attack with oar disk center distance 59mm (i.e. the 100% of 59mm) place, blade 1, chord length
For 8.34mm.
It is understood that because Section A-A, section B-B, C-C sections, D-D sections and the position in E-E sections can slightly become
It is dynamic, therefore correspondingly, the angle of attack chord long value obtained at Section A-A, section B-B, C-C sections, D-D sections and E-E sections can
It is corresponding to change.
The setting of the chord length in above-mentioned each section and the angle of attack can be set with the size of oar disk.In the present embodiment, oar
Connecting hole 2 can be provided with leaf 1.Blade 1 can realize the connection with oar seat by connecting hole 2, simple in construction, be easy to grasp
Make.
In addition, the propeller provided according to the present embodiment, the pitch of blade 1 can be 30 inches, i.e.,：Blade 1 rotates
One week, the distance that theory rises was 30 inches.
It is appreciated that the propeller can also be integrated oar, the length of whole oar is 118mm.
The above-mentioned propeller that the present embodiment is provided, by carrying out contrast test, reference with propeller of the prior art
Table one understands that under identical pulling force, the power for the propeller that the present embodiment is provided is lower, namely：In less power bar
Under part, there is bigger pulling force, so as to reduce kwh loss, increase endurance distance.
The propeller and the reduced parameter of prior art that the present embodiment of table one is provided
Embodiment two
The utility model embodiment two provides a kind of Power Component, including actuator and the spiral described in above-described embodiment
Oar, the propeller are connected by oar seat with the actuator.
After oar seat is connected with actuator, actuator can drive oar seat to rotate, and then oar seat drives blade to rotate.And blade
Quantity can be set according to being actually needed.Wherein, actuator is specifically as follows motor, the KV values of motor for 2100 turns/(point
Clock volt), wherein, KV values are used to weigh motor speed to the increased susceptibility of voltage, the voltage of the motor in the present embodiment
Often increase by 1 volt, motor rotating speed per minute just improves 2100 turns.
The Power Component that the present embodiment provides, by that to three section chord lengths in blade and the setting of the angle of attack, can drop
Resistance of the low propeller in rotation process, the flying speed of aircraft is improved, extend boat under certain power conditions supply
Row distance, improve flying quality.
Embodiment three
The utility model embodiment three provides a kind of aircraft.Aircraft in the present embodiment, can include fuselage and
At least one Power Component as described in above-mentioned embodiment two, the Power Component are connected with the fuselage.Power in aircraft
The number of component can be one, or multiple, Power Component in the present embodiment is multiple, and multiple Power Components
Rotation direction is different.Aircraft in the present embodiment may include the Power Component of the numbers such as three, four, five, six, eight, therefore can be pair
Answer the rotor craft of number.
The aircraft that the present embodiment provides, employs above-mentioned Power Component, by least three section strings in blade
Long and the angle of attack setting, can reduce resistance of the propeller in rotation process, the flying speed of aircraft be improved, certain
Power conditions supply is lower to extend distance to go, improves flying quality.
Finally it should be noted that：Above example is only to illustrate the technical solution of the utility model, rather than its limitations；
Although the utility model is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：
It can still modify to the technical scheme described in foregoing embodiments, or which part technical characteristic is carried out etc.
With replacement；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model technology
The spirit and scope of scheme.
Claims (16)
1. a kind of propeller, including blade, it is characterised in that the blade rotates to form oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 59.32% of oar disk radius is
14.05 ° ± 2.5 °, chord length is 11.94mm ± 5mm；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 76.27% of oar disk radius is
11.44 ° ± 2.5 °, chord length is 10.25mm ± 5mm；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 93.22% of oar disk radius is
9.99 ° ± 2.5 °, chord length is 8.64mm ± 5mm.
2. propeller according to claim 1, it is characterised in that the propeller shape into a diameter of 118mm of oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 35mm is 14.05 °, chord length is
11.94mm；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 45mm is 11.44 °, chord length is
10.25mm；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 55mm is 9.99 °, chord length is
8.64mm。
3. propeller according to claim 1 or 2, it is characterised in that
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 42.37% of oar disk radius is
16.61 ° ± 2.5 °, chord length is 13.48mm ± 5mm.
4. propeller according to claim 3, it is characterised in that the propeller shape into a diameter of 118mm of oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 25mm is 16.61 °, chord length is
13.48mm。
5. propeller according to claim 1 or 2, it is characterised in that
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at the 100% of oar disk radius is
9.61 ° ± 2.5 °, chord length is 8.34mm ± 5mm.
6. propeller according to claim 5, it is characterised in that the propeller shape into a diameter of 118mm of oar disk；
The blade with the propeller shape into oar disk center at a distance of being that the angle of attack at 59mm is 9.61 °, chord length is
8.34mm。
7. propeller according to claim 1, it is characterised in that the propeller also includes oar seat, the blade and institute
Oar seat is stated to be detachably connected.
8. propeller according to claim 7, it is characterised in that the quantity of the blade be at least two, it is described at least
Two blades are circumferentially uniformly distributed along the oar seat.
9. propeller according to claim 1, it is characterised in that from the blade close to one end of the oar disk center to
The one end of the blade away from the oar disk center, the thickness of the blade are gradually reduced.
10. according to the propeller any one of claim 1,2,4,6 and 9, it is characterised in that the blade is included upward
Blade back, blade face directed downwardly, and the first lateral margin for being connected between the side on the blade back and the blade face and be connected to
The second lateral margin between the blade back and the opposite side on the blade face, first lateral margin are located at below second lateral margin；Institute
It is curved surface to state blade back and the blade face；The propeller also includes oar seat, and the blade is detachably connected with the oar seat.
11. propeller according to claim 10, it is characterised in that first lateral margin is curved outside including one
The first of protrusion is arched upward portion, and second lateral margin includes one curved outwardly second portion that arches upward；First arch
The portion of rising and second portion of arching upward are close to one end that the blade is connected with the oar seat；And described first protrusion for arching upward portion
Degree is more than the described second protrusion degree for arching upward portion.
12. according to the propeller described in claim 1,2,4 and 6~9 any one, it is characterised in that the pitch of the propeller
For 30 inches.
A kind of 13. Power Component, it is characterised in that the propeller including actuator and as described in any one of claim 1~12,
The propeller is connected by oar seat with the actuator.
14. Power Component according to claim 13, it is characterised in that the actuator is motor, the KV of the motor
Be worth for 2100 turns/(minute volt).
15. a kind of aircraft, including fuselage, it is characterised in that also including at least one dynamic as described in claim 13 or 14
Power component, the Power Component are connected with the fuselage.
16. aircraft according to claim 15, it is characterised in that the aircraft includes multiple Power Components, described
The rotation direction of multiple Power Components is different.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720191484.1U CN206691356U (en) | 2017-02-28 | 2017-02-28 | Propeller, Power Component and aircraft |
| PCT/CN2017/078258 WO2018157426A1 (en) | 2017-02-28 | 2017-03-27 | Propeller, power assembly and aircraft |
| CN201780052530.2A CN109641648A (en) | 2017-02-28 | 2017-03-27 | Propeller, Power Component and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720191484.1U CN206691356U (en) | 2017-02-28 | 2017-02-28 | Propeller, Power Component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206691356U true CN206691356U (en) | 2017-12-01 |
Family
ID=60439753
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720191484.1U Expired - Fee Related CN206691356U (en) | 2017-02-28 | 2017-02-28 | Propeller, Power Component and aircraft |
| CN201780052530.2A Pending CN109641648A (en) | 2017-02-28 | 2017-03-27 | Propeller, Power Component and aircraft |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780052530.2A Pending CN109641648A (en) | 2017-02-28 | 2017-03-27 | Propeller, Power Component and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN206691356U (en) |
| WO (1) | WO2018157426A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108545173A (en) * | 2018-06-25 | 2018-09-18 | 北京小米移动软件有限公司 | Blade, propeller and aircraft |
| CN108820187A (en) * | 2018-03-30 | 2018-11-16 | 中山市朗宇模型有限公司 | Propeller, Power Component and aircraft |
| CN108945396A (en) * | 2018-03-30 | 2018-12-07 | 中山市朗宇模型有限公司 | propeller |
| CN109229364A (en) * | 2018-10-23 | 2019-01-18 | 西北工业大学 | Class ellipse aerofoil profile applied to high-speed helicopter rotor reversed flow region |
| CN109641648A (en) * | 2017-02-28 | 2019-04-16 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN109896009A (en) * | 2019-02-20 | 2019-06-18 | 顺丰科技有限公司 | Propeller and unmanned plane |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2374331A (en) * | 2000-12-15 | 2002-10-16 | Robert Andrew Ledingham | Aerofoil with protruding aerodynamic surface |
| US7861967B2 (en) * | 2008-04-25 | 2011-01-04 | Abe Karem | Aircraft with integrated lift and propulsion system |
| US9688395B2 (en) * | 2013-12-04 | 2017-06-27 | Sikorsky Aircraft Corporation | Boundary layer ingesting blade |
| CN205345321U (en) * | 2016-01-19 | 2016-06-29 | 深圳市大疆创新科技有限公司 | Screw, power suit and unmanned vehicles |
| CN205345320U (en) * | 2016-01-27 | 2016-06-29 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205524939U (en) * | 2016-01-27 | 2016-08-31 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205469778U (en) * | 2016-02-29 | 2016-08-17 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205524940U (en) * | 2016-02-29 | 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 |
| CN205589457U (en) * | 2016-02-29 | 2016-09-21 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN205801500U (en) * | 2016-06-30 | 2016-12-14 | 深圳市大疆创新科技有限公司 | Propeller, power suit and unmanned vehicle |
| 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 |
| CN206691356U (en) * | 2017-02-28 | 2017-12-01 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
-
2017
- 2017-02-28 CN CN201720191484.1U patent/CN206691356U/en not_active Expired - Fee Related
- 2017-03-27 WO PCT/CN2017/078258 patent/WO2018157426A1/en active Application Filing
- 2017-03-27 CN CN201780052530.2A patent/CN109641648A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109641648A (en) * | 2017-02-28 | 2019-04-16 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| CN108820187A (en) * | 2018-03-30 | 2018-11-16 | 中山市朗宇模型有限公司 | Propeller, Power Component and aircraft |
| CN108945396A (en) * | 2018-03-30 | 2018-12-07 | 中山市朗宇模型有限公司 | propeller |
| CN108545173A (en) * | 2018-06-25 | 2018-09-18 | 北京小米移动软件有限公司 | Blade, propeller and aircraft |
| CN109229364A (en) * | 2018-10-23 | 2019-01-18 | 西北工业大学 | Class ellipse aerofoil profile applied to high-speed helicopter rotor reversed flow region |
| CN109896009A (en) * | 2019-02-20 | 2019-06-18 | 顺丰科技有限公司 | Propeller and unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109641648A (en) | 2019-04-16 |
| WO2018157426A1 (en) | 2018-09-07 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
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| CF01 | Termination of patent right due to non-payment of annual fee |