CN205589457U - Screw, power component and aircraft - Google Patents
Screw, power component and aircraft Download PDFInfo
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- CN205589457U CN205589457U CN201620156286.7U CN201620156286U CN205589457U CN 205589457 U CN205589457 U CN 205589457U CN 201620156286 U CN201620156286 U CN 201620156286U CN 205589457 U CN205589457 U CN 205589457U
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- 238000000034 method Methods 0.000 abstract description 9
- 238000005516 engineering process Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- 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
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- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The utility model provides a screw, power component and aircraft, wherein the screw includes the oar seat and connects paddle on the oar seat, the paddle with the center of the oar dish that the screw formed is 15.1 2.5 at a distance of the angle of attack that coils 55.6% radial department for the oar, and the chord length is 16.5mm 5mm, the paddle with the center of the oar dish that the screw formed is 12.7 2.5 at a distance of the angle of attack that coils 72.2% radial department for the oar, and the chord length is 14mm 5mm, the paddle with the center of the oar dish that the screw formed is 11.2 2.5 at a distance of the angle of attack that coils 88.9% radial department for the oar, and the chord length is 11.5mm 5mm. The utility model provides a screw, power component and aircraft can subtract the small coil oar and rotate the resistance of in -process, improves the flight performance of aircraft.
Description
Technical field
This utility model relates to propeller arrangement technology, particularly relates to a kind of propeller, Power Component and flies
Row device.
Background technology
Carry-on propeller, as the important Primary Component of aircraft, it is used for motor or starts
The rotation of machine shaft is converted into thrust or lift.
Propeller of the prior art, its blade outer shape is the most rectangular, resistance when causing its flight
Greatly, efficiency low, the flight speed causing aircraft is little, endurance distance is short, has had a strong impact on aircraft
Flying quality.
Utility model content
This utility model provides a kind of propeller, Power Component and aircraft, in order to solve prior art
In drawbacks described above, reduce propeller flight resistance, improve propeller flight efficiency, raising flies
The flying quality of row device.
On the one hand this utility model provides a kind of propeller, and including blade, described blade rotates and forms oar
Dish；
Described blade at the center of the oar dish formed with described propeller at 55.6% for oar dish radius
The angle of attack be 15.1 ° ± 2.5 °, chord length is 16.5mm ± 5mm；
Described blade at the center of the oar dish formed with described propeller at 72.2% for oar dish radius
The angle of attack be 12.7 ° ± 2.5 °, chord length is 14mm ± 5mm；
Described blade at the center of the oar dish formed with described propeller at 88.9% for oar dish radius
The angle of attack be 11.2 ° ± 2.5 °, chord length is 11.5mm ± 5mm.
Propeller as above, a diameter of 180mm of oar dish that described propeller is formed；
Described blade at the center of the oar dish formed with described propeller at a distance of for the angle of attack at 50mm being
15.1 °, chord length is 16.5mm；
Described blade at the center of the oar dish formed with described propeller at a distance of for the angle of attack at 65mm being
12.7 °, chord length is 14mm；
Described blade at the center of the oar dish formed with described propeller at a distance of for the angle of attack at 80mm being
11.2 °, chord length is 11.5mm.
Propeller as above,
Described blade at the center of the oar dish formed with described propeller at 38.9% for oar dish radius
The angle of attack be 19.4 ° ± 2.5 °, chord length is 18.9mm ± 5mm.
Propeller as above, a diameter of 180mm of oar dish that described propeller is formed；
Described blade at the center of the oar dish formed with described propeller at a distance of for the angle of attack at 35mm being
19.4 °, chord length is 18.9mm.
Propeller as above,
Described blade at the center of the oar dish formed with described propeller at 100% for oar dish radius
The angle of attack be 10.5 ° ± 2.5 °, chord length is 10.1mm ± 5mm.
Propeller as above, a diameter of 180mm of oar dish that described propeller is formed；
Described blade at the center of the oar dish formed with described propeller at a distance of for the angle of attack at 90mm being
10.5 °, chord length is 10.1mm.
Propeller as above, described propeller also includes oar seat, and described blade is removable with described oar seat
Unloading connection, described blade offers the connecting hole for being connected with oar seat, described connecting hole is to oar dish
The distance at center is 14.5mm.
Propeller as above, the quantity of described blade is at least two, described at least two blade edge
Described oar seat circumference is uniformly distributed.
Propeller as above, remote to described blade near one end of described oar disk center from described blade
From one end of described oar disk center, the thickness of described blade is gradually reduced.
Propeller as above, described blade includes blade back upward, blade face down, and connects
The first lateral margin between the side on described blade back and described blade face and be connected to described blade back and described
The second lateral margin between the opposite side on blade face, described first lateral margin is positioned at below described second lateral margin；Described
Blade back and described blade face are curved surface.
Propeller as above, described first lateral margin includes a curved first outwardly arch
The portion of rising, described second lateral margin includes one curved outwardly second portion that arches upward；Described first arch
The portion of rising and described second portion of arching upward are close to one end that described blade is connected with described oar seat；And described first
The protrusion degree that the protrusion degree in portion that arches upward arches upward portion more than described second.
Propeller as above, the pitch of described propeller is 29mm.
On the other hand this utility model also provides for a kind of Power Component, including actuator and any of the above-described institute
The propeller stated, described propeller is connected with described actuator by oar seat.
Power Component as above, described actuator is motor, the KV value of described motor be 1000～
1200 turns/(minute volt).
The another aspect of this utility model also provides for a kind of aircraft, including fuselage, also includes at least one such as
Power Component described in upper any one, described Power Component is connected with described fuselage.
Described aircraft includes multiple Power Component, and the rotation direction of the plurality of Power Component is different.
This utility model provide propeller, Power Component and aircraft, due to blade with propeller shape
The center of the oar dish the become angle of attack at for the 55.6% of oar dish radius is 15.1 ° ± 2.5 °, and chord length is
16.5mm±5mm；Blade at the center of the oar dish formed with propeller at a distance of for oar dish radius
The angle of attack at 72.2% is 12.7 ° ± 2.5 °, and chord length is 14mm ± 5mm；Blade with propeller shape
The center of the oar dish the become angle of attack at for the 88.9% of oar dish radius is 11.2 ° ± 2.5 °, and chord length is
11.5mm±5mm.Therefore, it is possible to reduce propeller resistance in rotation process, reduce aircraft and fly
Flight resistance during row, improves flight efficiency, increases endurance distance, improves the flight of aircraft
Energy.
Accompanying drawing explanation
The axonometric chart of blade in the propeller that Fig. 1 provides for this utility model embodiment one；
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 be in Fig. 2 blade along the generalized section of line A-A；
Fig. 8 be in Fig. 2 blade along the generalized section of line B-B；
Fig. 9 be in Fig. 2 blade along the generalized section of line C-C；
Figure 10 be in Fig. 2 blade along the generalized section of line D-D；
Figure 11 be in Fig. 2 blade along the generalized section of E-E line.
Reference:
1-blade；2-connecting hole；3-blade face
4-blade back；5-the first lateral margin；6-the second lateral margin；
501-first arches upward portion；601-second arches upward portion.
Detailed description of the invention
For making the purpose of this utility model embodiment, technical scheme and advantage clearer, below in conjunction with
Accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out clear,
It is fully described by, it is clear that described embodiment is a part of embodiment of this utility model rather than complete
The embodiment in portion.Based on the embodiment in this utility model, those of ordinary skill in the art are not making
The every other embodiment obtained under creative work premise, broadly falls into the model of this utility model protection
Enclose.
It should be noted that when assembly is referred to as " being fixed on " another assembly, and it can be directly separately
On one assembly or assembly placed in the middle can also be there is.When assembly be considered as " connection " another
Individual assembly, it can be directly to another assembly or may be simultaneously present assembly placed in the middle.
Unless otherwise defined, all of technology used herein and scientific terminology with belong to this utility model
The implication that is generally understood that of those skilled in the art identical.Herein in description of the present utility model
Used in term be intended merely to describe specific embodiment purpose, it is not intended that in limiting this practicality
Novel.Term as used herein " and/or " include any of one or more relevant Listed Items
And all of combination.
Embodiment one
This utility model embodiment one provides a kind of propeller.Propeller in the present embodiment, can apply
In aircraft, propeller may include that 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, refers to fly from vertical view
From the point of view of row device, dextrorotation transfers to produce the propeller of lift；So-called anti-oar, refers to from vertical view
From the point of view of aircraft, rotate counterclockwise and produce the propeller of lift.The structure of positive oar and the knot of anti-oar
It is that minute surface is symmetrical between structure, the structure of propeller is only said as a example by the structure of positive oar by the present embodiment
Bright, those skilled in the art can be extended according to the mode that the present embodiment is provided and obtain anti-oar
Structure.
In the propeller that the present embodiment provides, blade and oar seat can be formed in one structure, or also may be used
To realize otherwise being connected with each other, such as, can be fixed by the form of welding, or can lead to
Cross the fixing connection of dismountable connector, such as, be spirally connected fixing, or realize connection etc. by other connector.
The number of blade can be one or more, and multiple blades can be arranged along the circumferential uniform intervals of oar seat,
The present embodiment is preferred, and the quantity of blade is at least two, and at least two blade is uniform along the circumference of oar seat
Distribution.Can be formed in one between multiple blades structure, or, it is also possible to each independent, this practicality
Novel this is the most specifically limited.
The axonometric chart of blade in the propeller that Fig. 1 provides for this utility model embodiment one；Fig. 2 is Fig. 1
The front view of shown blade；Fig. 3 is the left view of blade shown in Fig. 1；Fig. 4 is blade shown in Fig. 1
Right view；Fig. 5 is the upward view of blade shown in Fig. 1；Fig. 6 is the top view of blade shown in Fig. 1.As
Shown in Fig. 1 to Fig. 6, the blade of the propeller in the present embodiment, blade back 4 upward, court can be included
Under blade face 3, and the first lateral margin 5 of being connected between the side on blade back 4 and blade face 3 and connecting
The second lateral margin 6 between the opposite side on blade back 4 and blade face 3, the first lateral margin 5 is positioned at the second lateral margin 6
Lower section；Blade back 4 and blade face 3 are curved surface.
Wherein, blade back 4 be aircraft in flight course, blade 1 one side upward；Blade face 3 is for flying
Row device in flight course, blade 1 one side down.As shown in Figure 3 and Figure 4, blade back 4 and blade face
3 are curved surface, and the trend of bending is: when blade 1 is generally in level, the first lateral margin 5
Location is lower than the second lateral margin 6 location.
First lateral margin 5 can include that curved outwardly first arches upward portion 501, and first arches upward portion
501 with the remainder of the first lateral margin 5 for being connected smoothly.On the length direction of whole blade 1,
Relative to blade 1 away from one end of oar seat, first arches upward what portion 501 was connected closer to blade 1 with oar seat
One end.First portion 501 that arches upward not only arches upward towards the side of blade 1, can also arch upward downwards, i.e. simultaneously
Arch upward towards the direction at place, blade face 3, and can be connected smoothly with blade face 3 formation.
Second lateral margin 6 can include one curved outwardly second portion 601 that arches upward, the second arch
Play the portion 601 remainder with the second lateral margin 6 for being connected smoothly.Length side at whole blade 1
Upwards, relative to blade 1 away from one end of oar seat, second arches upward portion 601 closer to blade 1 and oar seat
The one end being connected.
In the present embodiment, the first protrusion degree arching upward portion 501 can arch upward portion 601 more than second
Protrusion degree.First summit arching upward portion 501 is located substantially at blade 1 with the second summit arching upward portion 601
Same cross section on.Further, each position, the surface of blade 1 is and seamlessly transits, without drastically
In place of torsion, therefore having less stress, and intensity is higher is not easily broken, whole propeller has relatively
High reliability.
The propeller that the present embodiment is provided circle formed in the rotary course, referred to as oar dish, this circle
Center is referred to as the center of oar dish, and this diameter of a circle is referred to as the diameter of oar dish.For split type blade 1
Speech, the radius of oar dish can be more than the length of blade 1.
From blade 1 near one end of oar disk center to blade 1 away from one end of oar disk center, blade 1
Thickness can be gradually reduced.Thus, in blade 1 end from oar disk center farthest be in blade 1
Thin part, thus air drag when advantageously reducing flight, improve flight efficiency.
Fig. 7 be in Fig. 2 blade along the generalized section of line A-A；Fig. 8 be in Fig. 2 blade along B-B
The generalized section of line；Fig. 9 be in Fig. 2 blade along the generalized section of line C-C；Figure 10 is Fig. 2
Middle blade is along the generalized section of line D-D；Figure 11 be in Fig. 2 blade along the generalized section of E-E line.
As shown in Fig. 7 to Figure 11, the size of the five of blade section can be improved by the present embodiment,
Wherein, the improvement carried out the size of section B-B, C-C cross section and D-D section is mostly important.
Concrete, as shown in Figure 2 and Figure 8, blade 1 is at the center of the oar dish formed with propeller apart
At the 55.6% of oar dish radius, it may be assumed that at the section B-B of distance oar disk center L2 as shown in Figure 2,
At this, the angle of attack A2 of blade 1 is 15.1 ° ± 2.5 °, and chord length D2 is 16.5mm ± 5mm；Wherein,
Chord length is the length that blade 1 cross section in this place projects in the horizontal direction, and the angle of attack is that the string wing comes with gas
The angle of flow path direction.
As shown in Figure 2 and Figure 9, blade 1 at the center of the oar dish formed with propeller at a distance of for oar dish half
At the 72.2% of footpath, it may be assumed that the C-C section of distance oar disk center L3 as shown in Figure 2, oar at this
The angle of attack A3 of leaf 1 is 12.7 ° ± 2.5 °, and chord length D3 is 14mm ± 5mm.
As shown in figs. 2 and 10, blade 1 at the center of the oar dish formed with propeller at a distance of for oar dish half
At the 88.9% of footpath, it may be assumed that the D-D section of distance oar disk center L4 as shown in Figure 2, oar at this
The angle of attack of leaf 1 be A4 be 11.2 ° ± 2.5 °, chord length D4 is 11.5mm ± 5mm.
The present embodiment is by the chord length in above three cross section in blade 1 and the setting of the angle of attack, it is possible to reduce
Propeller resistance in rotation process, improves flight speed and the flight efficiency of aircraft, certain
The lower increase of power conditions supply continues boat distance, improves the flying quality of aircraft.
On the basis of technique scheme, it is also possible to Section A-A in blade 1 and E-E cross section are attacked
Angle chord length is optimized, to reduce propeller air drag in rotation process further.
As shown in Figure 2 and Figure 7, blade 1 at the center of the oar dish formed with propeller at a distance of for oar dish half
At the 38.9% of footpath, it may be assumed that at the Section A-A of distance oar disk center L1 as shown in Figure 2, oar at this
The angle of attack of leaf 1 is 19.4 ° ± 2.5 °, and chord length is 18.9mm ± 5mm.
As shown in figs. 2 and 11, blade 1 at the center of the oar dish formed with propeller at a distance of for oar dish half
At the 100% of footpath, it may be assumed that the E-E section of distance oar disk center L5 as shown in Figure 2, blade at this
The angle of attack of 1 is 10.5 ° ± 2.5 °, and chord length is 10.1mm ± 5mm.
Certainly, it will be appreciated by persons skilled in the art that above-mentioned Section A-A, section B-B, C-C
The position in cross section, D-D cross section and E-E cross section can slightly change.
For technique scheme, the present embodiment provides a kind of concrete propeller, and this propeller is formed
The a diameter of 180mm of oar dish, the half that distance is oar dish diameter of oar disk center to blade 1 end, i.e.
Oar disk center is 90mm to the distance of blade 1 end.
As a example by oar dish diameter 180mm, blade 1 at the center of the oar dish formed with propeller is apart
At 50mm, the angle of attack of (i.e. the 55.6% of 90mm) is 15.1 °, and chord length is 16.5mm；Blade 1 exists
With the center of the oar dish of propeller formation for the angle of attack of (i.e. the 72.2% of 90mm) at 65mm it is apart
12.7 °, chord length is 14mm；Blade 1 at the center of the oar dish formed with propeller at for 80mm
The angle of attack of (i.e. the 88.9% of 90mm) is 11.2 °, and chord length is 11.5mm.
Further, with oar disk center distance 35mm (i.e. the 38.9% of 90mm) place, blade 1
The angle of attack be 19.4 °, chord length is 18.9mm.With oar disk center distance 90mm (i.e. the 100% of 90mm)
Place, the angle of attack of blade 1 is 10.5 °, and chord length is 10.1mm.
It is understood that because of Section A-A, section B-B, C-C cross section, D-D cross section and E-E
The position in cross section can slightly change, therefore correspondingly, Section A-A, section B-B, C-C cross section,
The angle of attack chord long value of D-D cross section and E-E section gained can change accordingly.
The chord length in above-mentioned each cross section and the setting of the angle of attack all can be set with the size of oar dish.This enforcement
In example, blade 1 can be provided with connecting hole 2, distance L6 of connecting hole 2 to oar disk center can be
14.5mm.Blade 1 can realize the connection with oar seat, simple in construction by connecting hole 2, it is simple to operation.
It addition, the propeller provided according to the present embodiment, the pitch of blade 1 can be 29mm, it may be assumed that
Blade 1 rotates a circle, and the theoretical distance risen is 29mm.
The above-mentioned propeller that the present embodiment is provided, surveys by carrying out contrast with propeller of the prior art
Examination, understands with reference to table one, and under identical pulling force, the power of the propeller that the present embodiment is provided is more
Low, namely: under less power condition, there is bigger pulling force, thus reduce kwh loss, increase
Add endurance distance.
The propeller that table one the present embodiment is provided and the reduced parameter of prior art
Embodiment two
This utility model embodiment two provides a kind of Power Component, including described in actuator and above-described embodiment
Propeller, described propeller is connected with described actuator by oar seat.
After oar seat is connected with actuator, actuator can drive oar seat to rotate, and then oar seat drives blade to turn
Dynamic.And the quantity of blade can be arranged according to actual needs.Wherein, actuator is specifically as follows motor,
The KV value of motor is 1000～1200 turns/(minute volt), and wherein, KV value is used for weighing motor
The sensitivity that voltage is increased by rotating speed, the voltage of the motor in the present embodiment often increases by 1 volt, every point of motor
Clock rotating speed just improves 1000～1200 turns.
The Power Component that the present embodiment provides, by setting three cross section chord lengths in blade and the angle of attack
Fixed, it is possible to reduce propeller resistance in rotation process, improve the flight speed of aircraft, necessarily
Power conditions supply under extend distance to go, improve flying quality.
Embodiment three
This 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-described embodiment two, described Power Component and described machine
Body connects.The number of aircraft medium power assembly can be one, it is also possible to for multiple, in the present embodiment
Power Component be multiple, and the rotation direction of multiple Power Component is different.Aircraft in the present embodiment
The Power Component of the numbers such as three, four, five, six, eight can be included, therefore can be the rotor flying of corresponding number
Device.
The aircraft that the present embodiment provides, have employed above-mentioned Power Component, by least three in blade
Individual cross section chord length and the setting of the angle of attack, it is possible to reduce propeller resistance in rotation process, improve flight
The flight speed of device, extends distance to go under certain power conditions supply, improves flying quality.
Last it is noted that above example is only in order to illustrate the technical solution of the utility model, rather than
It is limited；Although this utility model being described in detail with reference to previous embodiment, this area
Those of ordinary skill is it is understood that the technical scheme described in foregoing embodiments still can be carried out by it
Amendment, or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, not
The essence making appropriate technical solution departs from the spirit and scope of this utility model each embodiment technical scheme.
Claims (17)
1. a propeller, including blade, it is characterised in that described blade rotates and forms oar dish；
At the center of the oar dish formed with described propeller, the angle of attack at 55.6% for oar dish radius is 15.1 ° ± 2.5 ° to described blade, and chord length is 16.5mm ± 5mm；
At the center of the oar dish formed with described propeller, the angle of attack at 72.2% for oar dish radius is 12.7 ° ± 2.5 ° to described blade, and chord length is 14mm ± 5mm；
At the center of the oar dish formed with described propeller, the angle of attack at 88.9% for oar dish radius is 11.2 ° ± 2.5 ° to described blade, and chord length is 11.5mm ± 5mm.
Propeller the most according to claim 1, it is characterised in that a diameter of 180mm of oar dish that described propeller is formed；
Described blade is at the center of the oar dish formed with described propeller at a distance of being 15.1 ° for the angle of attack at 50mm, and chord length is 16.5mm；
Described blade is at the center of the oar dish formed with described propeller at a distance of being 12.7 ° for the angle of attack at 65mm, and chord length is 14mm；
Described blade is at the center of the oar dish formed with described propeller at a distance of being 11.2 ° for the angle of attack at 80mm, and chord length is 11.5mm.
Propeller the most according to claim 1, it is characterised in that
At the center of the oar dish formed with described propeller, the angle of attack at 38.9% for oar dish radius is 19.4 ° ± 2.5 ° to described blade, and chord length is 18.9mm ± 5mm.
Propeller the most according to claim 3, it is characterised in that a diameter of 180mm of oar dish that described propeller is formed；
Described blade is at the center of the oar dish formed with described propeller at a distance of being 19.4 ° for the angle of attack at 35mm, and chord length is 18.9mm.
Propeller the most according to claim 1, it is characterised in that
At the center of the oar dish formed with described propeller, the angle of attack at 100% for oar dish radius is 10.5 ° ± 2.5 ° to described blade, and chord length is 10.1mm ± 5mm.
Propeller the most according to claim 5, it is characterised in that a diameter of 180mm of oar dish that described propeller is formed；
Described blade is at the center of the oar dish formed with described propeller at a distance of being 10.5 ° for the angle of attack at 90mm, and chord length is 10.1mm.
Propeller the most according to claim 1, it is characterized in that, described propeller also includes that oar seat, described blade removably connect with described oar seat, offering the connecting hole for being connected with oar seat on described blade, the distance of described connecting hole to the center of oar dish is 14.5mm.
Propeller the most according to claim 7, it is characterised in that the quantity of described blade is at least two, described at least two blade is uniformly distributed along described oar seat circumference.
Propeller the most according to claim 1, it is characterised in that from described blade near one end of described oar disk center to described blade the one end away from described oar disk center, the thickness of described blade is gradually reduced.
10. according to the propeller described in any one of claim 1,2,3,4,5,6,9, it is characterized in that, described blade includes blade back upward, blade face down, and the second lateral margin between the first lateral margin of being connected between the side on described blade back and described blade face and the opposite side being connected to described blade back and described blade face, described first lateral margin is positioned at below described second lateral margin；Described blade back and described blade face are curved surface.
11. according to the propeller described in claim 7 or 8, it is characterized in that, described blade includes blade back upward, blade face down, and the second lateral margin between the first lateral margin of being connected between the side on described blade back and described blade face and the opposite side being connected to described blade back and described blade face, described first lateral margin is positioned at below described second lateral margin；Described blade back and described blade face are curved surface.
12. propellers according to claim 11, it is characterised in that described first lateral margin includes one curved outwardly first portion that arches upward, described second lateral margin includes one curved outwardly second portion that arches upward；Described first arches upward portion and described second portion of arching upward is close to one end that described blade is connected with described oar seat；And the described first protrusion degree the arching upward portion protrusion degree that arch upward portion more than described second.
13. according to the propeller described in any one of claim 1～9, it is characterised in that the pitch of described propeller is 29mm.
14. 1 kinds of Power Components, it is characterised in that include actuator and the propeller as described in any one of claim 1～13, described propeller is connected with described actuator by oar seat.
15. Power Components according to claim 14, it is characterised in that described actuator is motor, the KV value of described motor is 1000～1200 turns/(minute volt).
16. 1 kinds of aircraft, including fuselage, it is characterised in that also include at least one Power Component as described in claims 14 or 15, and described Power Component is connected with described fuselage.
17. aircraft according to claim 16, it is characterised in that described aircraft includes multiple Power Component, the rotation direction of the plurality of Power Component is different.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620156286.7U CN205589457U (en) | 2016-02-29 | 2016-02-29 | Screw, power component and aircraft |
| PCT/CN2016/098967 WO2017148128A1 (en) | 2016-02-29 | 2016-09-14 | Propeller, power assembly and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620156286.7U CN205589457U (en) | 2016-02-29 | 2016-02-29 | Screw, power component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205589457U true CN205589457U (en) | 2016-09-21 |
Family
ID=56927036
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620156286.7U Expired - Fee Related CN205589457U (en) | 2016-02-29 | 2016-02-29 | Screw, power component and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN205589457U (en) |
| WO (1) | WO2017148128A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018157426A1 (en) * | 2017-02-28 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Propeller, power assembly 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 |
| CN109071004A (en) * | 2016-10-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, power suit and unmanned vehicle |
| WO2019000560A1 (en) * | 2017-06-30 | 2019-01-03 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
| CN110015417A (en) * | 2019-04-03 | 2019-07-16 | 中南大学 | A kind of small propeller |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4454161B2 (en) * | 2001-01-23 | 2010-04-21 | ユニバーサル造船株式会社 | Duct for improving ship propulsion efficiency |
| CN102963522B (en) * | 2012-10-31 | 2015-04-22 | 中国航天空气动力技术研究院 | Near space propeller |
| CN203374428U (en) * | 2013-06-14 | 2014-01-01 | 中国科学院工程热物理研究所 | Family of wind-power airfoil profiles with large thickness and blunt trailing edges |
| CN203593160U (en) * | 2013-12-13 | 2014-05-14 | 吉林大学 | Wing structure |
| CN203996873U (en) * | 2014-07-30 | 2014-12-10 | 深圳市大疆创新科技有限公司 | Aircraft and screw propeller thereof |
| CN105253295A (en) * | 2015-10-30 | 2016-01-20 | 深圳市道通智能航空技术有限公司 | Screw propeller and aerocraft |
-
2016
- 2016-02-29 CN CN201620156286.7U patent/CN205589457U/en not_active Expired - Fee Related
- 2016-09-14 WO PCT/CN2016/098967 patent/WO2017148128A1/en active Application Filing
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109071004A (en) * | 2016-10-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Propeller, power suit and unmanned vehicle |
| WO2018157426A1 (en) * | 2017-02-28 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| 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 |
| WO2019000560A1 (en) * | 2017-06-30 | 2019-01-03 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, 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 |
| CN110015417A (en) * | 2019-04-03 | 2019-07-16 | 中南大学 | A kind of small propeller |
| CN110015417B (en) * | 2019-04-03 | 2024-02-02 | 中南大学 | Small-sized propeller |
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| Publication number | Publication date |
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| WO2017148128A1 (en) | 2017-09-08 |
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