CN205524939U - Screw, power component and aircraft - Google Patents
Screw, power component and aircraft Download PDFInfo
- Publication number
- CN205524939U CN205524939U CN201620083468.6U CN201620083468U CN205524939U CN 205524939 U CN205524939 U CN 205524939U CN 201620083468 U CN201620083468 U CN 201620083468U CN 205524939 U CN205524939 U CN 205524939U
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- China
- Prior art keywords
- blade
- screw
- oar
- center
- oar dish
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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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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Wind Motors (AREA)
Abstract
The utility model provides a screw, power component and aircraft, wherein, the screw presss from both sides and connects including the oar the paddle that the oar pressed from both sides, with the center of the oar dish that the screw formed is at a distance of coiling 55% radial department for the oar, the chord length of paddle is 16.7mm 5mm, and the angle of attack is 14 2.5, with the center of oar dish is at a distance of coiling 70% radial department for the oar, the chord length of paddle is 14.4mm 5mm, and the angle of attack is 11.7 2.5, with the center of oar dish is at a distance of coiling 85% radial department for the oar, the chord length of paddle is 12.2mm 5mm, and the angle of attack is 9.3 2.5. The utility model provides a screw, power component and aircraft can effectively subtract the small coil oar at the resistance that rotates the in -process to improve power conversion efficiency.
Description
Technical field
The utility model relates to propeller arrangement technology, particularly relates to a kind of screw, Power Component and flies
Row device.
Background technology
Carry-on screw, as the important devices of aircraft, is used for driving motor or starts
The rotatory force of machine shaft is converted to thrust or the lift of air, promotes aircraft to rise and changes boat
To.Screw of the prior art, its outer shape is the most rectangular, to air in its rotation process
The resistance produced is relatively big, causes power conversion efficiency poor, and then reduces the flying speed of aircraft,
Shorten distance to go, have a strong impact on the flying quality of aircraft.
Utility model content
The utility model provides a kind of screw, Power Component and aircraft, it is possible to effectively reduce screw
Resistance in rotation process, to improve power conversion efficiency.
The utility model embodiment provides a kind of screw, presss from both sides including oar and is connected to the oar on described oar folder
Leaf,
At the center of the oar dish formed with described screw at 55% for oar dish radius, described blade
Chord length be 16.7mm ± 5mm, the angle of attack is 14 ° ± 2.5 °；
At the center with described oar dish at 70% for oar dish radius, the chord length of described blade is
14.4mm ± 5mm, the angle of attack is 11.7 ° ± 2.5 °；
At the center with described oar dish at 85% for oar dish radius, the chord length of described blade is
12.2mm ± 5mm, the angle of attack is 9.3 ° ± 2.5 °.
Screw as above, at the center with described oar dish at 40% for oar dish radius, institute
The chord length stating blade is 18.9mm ± 5mm, and the angle of attack is 17.9 ° ± 2.5 °.
Screw as above, at the center with described oar dish at 100% for oar dish radius, institute
The chord length stating blade is 8.9mm ± 5mm, and the angle of attack is 7.1 ° ± 2.5 °.
Screw as above, a diameter of 200mm ± 20mm of the oar dish that described screw is formed；
At the center with described oar dish at for 55mm, the chord length of described blade is 16.7mm, the angle of attack
It it is 14 °；
At the center with described oar dish at for 70mm, the chord length of described blade is 14.4mm, the angle of attack
It it is 11.7 °；
At the center with described oar dish at for 85mm, the chord length of described blade is 12.2mm, the angle of attack
It it is 9.3 °.
Screw as above, a diameter of 200mm ± 20mm of the oar dish that described screw is formed；?
With the center of described oar dish at for 40mm, the chord length of described blade is 18.9mm, and the angle of attack is 17.9 °.
Screw as above, a diameter of 200mm ± 20mm of the oar dish that described screw is formed；?
With the center of described oar dish at for 100mm, the chord length of described blade is 8.9mm, and the angle of attack is 7.1 °.
Screw as above, a length of 90mm ± 9mm of described blade.
Screw as above, described blade is provided with connecting hole, and described connecting hole is to the center of oar dish
Distance be 14.5mm ± 1.45mm.
Screw as above, described blade has blade back, blade face, connection blade back and blade face one side
The first lateral margin and connect blade back and the second lateral margin of another side of blade face；Described blade back and blade face are
Curved surface.
Screw as above, described first lateral margin has curved first and arches upward portion, the second lateral margin
Have curved second to arch upward portion.
Screw as above, described first arches upward portion and to be respectively positioned on described blade close in second portion of arching upward
One end of oar folder.
Screw as above, the described second protrusion degree arching upward portion arches upward less than first the protrusion in portion
Degree.
Screw as above, described blade is two, two blades about described oar dish center in
Central Symmetry.
Screw as above, the pitch of described blade is 35mm.
The utility model embodiment also provides for a kind of Power Component, including actuator and spiral as above
Oar, described screw is connected with described actuator by oar folder.
Power Component as above, described actuator is motor, the KV value of described motor is 1200 turns/
(minute volt).
The utility model embodiment also provides for a kind of aircraft, including fuselage, also includes at least one as above
Described Power Component, described Power Component is connected with described fuselage.
The utility model embodiment is by least three cross section chord length in blade and the setting of the angle of attack, it is possible to
Reduce screw resistance in rotation process, improve power conversion efficiency, improve the flying speed of aircraft,
Under certain power conditions supply, extend distance to go, improve flying quality.
Accompanying drawing explanation
Fig. 1 is installed on the structural representation of aircraft for the screw that the utility model embodiment provides；
The top view of blade in the screw that Fig. 2 provides for the utility model embodiment；
Fig. 3 is the left view of blade shown in Fig. 2；
Fig. 4 is the right view of blade shown in Fig. 2；
Fig. 5 is the side elevation view of blade shown in Fig. 2；
Fig. 6 is the underside view of blade shown in Fig. 2；
The screw that Fig. 7 provides for the utility model embodiment divides on blade the signal of different cross section
Figure；
Fig. 8 is the structural representation of Section A-A in Fig. 7；
Fig. 9 is the structural representation of section B-B in Fig. 7；
Figure 10 is the structural representation in C-C cross section in Fig. 7；
Figure 11 is the structural representation in D-D cross section in Fig. 7；
Figure 12 is the structural representation in E-E cross section in Fig. 7.
Reference:
1-oar presss from both sides；2-blade；21-blade back；
22-blade face；23-the first lateral margin；24-the second lateral margin；
26-first arches upward portion；27-second arches upward portion.
Detailed description of the invention
The present embodiment provides a kind of screw, it is possible to be applied on aircraft.Fig. 1 is that the utility model is real
The screw that executing example provides is installed on the structural representation of aircraft.As it is shown in figure 1, the present embodiment provides
Screw can be positive oar or anti-oar, so-called positive oar, refer to from the point of view of overlooking aircraft, suitable
Hour hands rotate and produce the screw of lift；So-called anti-oar, refers to from the point of view of overlooking aircraft,
Rotate counterclockwise and produce the screw of lift.The positive structure of oar and the structure of anti-oar are that minute surface is symmetrical, this
Embodiment only illustrates as a example by the structure of positive oar, and those skilled in the art can be according to the present embodiment institute
The mode provided is extended and obtains the structure of anti-oar.
Further, the screw that the present embodiment provides is applicable to twin shaft aircraft, four-axle aircraft or eight
Axle aircraft etc., the blade on each screw can be structure as a whole, it is also possible to for several independent oars
Leaf, such as two, three or more than three blade.The present embodiment is only constituted with two independent blades
Illustrating as a example by the mode of one screw, those skilled in the art can also be carried according to the present embodiment
The technical scheme of confession extends to the screw that blade is structure as a whole.
In Fig. 1, screw includes oar folder 1 and the blade 2 being connected on oar folder 1, wherein, oar folder 1
For being connected with carry-on actuator, drive oar folder 1 rotation by actuator, and then drive blade
2 rotate.The quantity of blade 2 is two, is respectively connecting on oar folder 1, with oar folder 1 as symmetrical centre
It is centrosymmetric.
The top view of blade in the screw that Fig. 2 provides for the utility model embodiment, Fig. 3 is Fig. 2 institute
The left view of the blade 2 shown, Fig. 4 is the right view of blade 2 shown in Fig. 2, and Fig. 5 is oar shown in Fig. 2
The side elevation view of leaf 2, Fig. 6 is the underside view of blade 2 shown in Fig. 2, above-mentioned viewing angles be all from
For direction during aircraft flight.As shown in Figures 1 to 6, the spiral shell that the present embodiment is provided
Blade in rotation oar includes blade back 21, blade face 22, connects blade back 21 and the first side of blade face 22 1 side
Edge 23 and connect blade back 21 and the second lateral margin 24 of another side of blade face 22.
Wherein, blade back 21 be aircraft in flight course, blade 2 one side upward；Blade face 22 is
Aircraft in flight course, blade 2 one side (in other words towards ground) down.Energy from Fig. 6
Enough finding out, blade back 21 and blade face 22 are curved surface, and the trend of bending is: when blade 2 generally in
During level, the first lateral margin 23 location is lower than the second lateral margin 24 location.
From the point of view of viewing angles with Fig. 2,5,6, above-mentioned first lateral margin 23 has curved towards left side
First arched upward is arched upward portion 26, and first arches upward the portion 26 remainder with the first lateral margin 23 for seamlessly transitting
Connect.On the length direction of whole blade 2, first arch upward portion 26 be positioned on blade 2 be closer to
The position of one end that oar folder 1 is connected.First portion 26 that arches upward is in addition to arching upward towards left side, also towards leaf
Arch upward in the direction in face 22, and with blade face 22 for being connected smoothly.
Above-mentioned second lateral margin 24 have curved arch upward towards right side second arch upward portion 27, the second arch
Play the portion 27 remainder with the second lateral margin 24 for being connected smoothly.Length side at whole blade 2
Upwards, second portion 27 that arches upward is positioned on blade 2 position of one end being closer to be connected with oar folder 1.
In the present embodiment, the protrusion degree that the second protrusion degree arching upward portion 27 arches upward portion 26 less than first.
First arches upward the summit in portion 26 and the second summit arching upward portion 27 is located substantially at the same transversal of blade 2
On face.Further, the surface of blade 2 is and seamlessly transits, and the most drastically reverses part, therefore has relatively
Little stress, and intensity is higher is not easily broken, and has higher reliability.Blade 2 presss from both sides 1 away from oar
End be part the thinnest in blade 2, advantageously reduce air drag.
The screw that the present embodiment is provided circle formed in the rotary course, referred to as oar dish, this circle
The center of shape becomes the center of oar dish, and circular diameter is referred to as the diameter of oar dish.For split type blade
For, the radius of oar dish is more than the length of blade.
The screw that Fig. 7 provides for the utility model embodiment divides on blade the signal of different cross section
Figure, Fig. 8 is the structural representation of Section A-A in Fig. 7, and Fig. 9 is that in Fig. 7, the structure of section B-B is shown
Being intended to, Figure 10 is the structural representation in C-C cross section in Fig. 7, and Figure 11 is the knot in D-D cross section in Fig. 7
Structure schematic diagram, Figure 12 is the structural representation in E-E cross section in Fig. 7.As shown in Fig. 7 to Figure 12, this
Embodiment improves in the size of five sections of blade 2, wherein, cuts at section B-B, C-C
The improvement that the size of face and D-D section is had have optimum effect:
Concrete, at the center of the oar dish formed with screw apart for oar dish radius 55% at, it may be assumed that
At the section B-B of distance oar disk center H2 as shown in Figure 7, the chord length of blade 2 as shown in Figure 9
L2 is 16.7mm ± 5mm, and angle of attack θ 2 is 14 ° ± 2.5 °.Wherein, chord length refers at this section,
First lateral margin 23 is positioned at the end points of the leftmost side on this cross section and the second lateral margin 24 is positioned at the rightmost side on this cross section
End points distance in the horizontal direction, the angle of attack be the first lateral margin 23 be positioned on this cross section the end points of the leftmost side with
Line between the end points of second rightmost side on this cross section of lateral margin 24 and the angle of horizontal direction, or, attack
Angle is it can be appreciated that be the string wing and the gas of blade 2 angle that carrys out flow path direction.
At the center with oar dish at 70% for oar dish radius, it may be assumed that distance oar dish as shown in Figure 7
The C-C section of center H3, chord length L3 of blade 2 as shown in Figure 10 is 14.4mm ± 5mm, attacks
Angle θ 3 is 11.7 ° ± 2.5 °.
At the center with oar dish at 85% for oar dish radius, it may be assumed that distance oar dish as shown in Figure 7
The D-D section of center H4, chord length L4 of blade 2 is 12.2mm ± 5mm, and angle of attack θ 4 is 9.3 °
±2.5°。
The present embodiment is by above three cross section chord length in blade and the setting of the angle of attack, it is possible to reduce spiral
Oar resistance in rotation process, improves power conversion efficiency, improves the flying speed of aircraft, necessarily
Power conditions supply under extend distance to go, improve flying quality.
On the basis of technique scheme, to the chord length in Section A-A and E-E cross section in blade 2 and attacking
Angle improves respectively, it is possible to reduce screw resistance in rotation process further.
At the center with oar dish at 40% for oar dish radius, it may be assumed that distance oar dish as shown in Figure 7
At the Section A-A of center H1, chord length L1 of blade 2 is 18.9mm ± 5mm, and angle of attack θ 1 is 17.9 °
±2.5°。
At the center with oar dish at 100% for oar dish radius, it may be assumed that distance oar dish as shown in Figure 7
The E-E section of center H5, chord length L5 of blade 2 is 8.9mm ± 5mm, and angle of attack θ 5 is 7.1 °
±2.5°。
It will be appreciated by persons skilled in the art that the position not office of above-mentioned section A-A and cross section E-E
It is limited to such scheme, can slightly change.
For technique scheme, the present embodiment provides a kind of concrete screw, and this screw is formed
The a diameter of 200mm ± 20mm of oar dish, as a example by oar dish diameter 200mm, at the center with oar dish apart
At 55mm, the chord length of blade 2 is specially 16.7mm, and the angle of attack is 14 °.In the center phase with oar dish
At for 70mm, the chord length of blade 2 is 14.4mm, and the angle of attack is 11.7 °.In the center phase with oar dish
At for 85mm, the chord length of blade 2 is 12.2mm, and the angle of attack is 9.3 °.
Further, at the center with oar dish at for 40mm, the chord length of blade 2 is 18.9mm,
The angle of attack is 17.9 °.At the center with oar dish at for 100mm, the chord length of blade 2 is 8.9mm,
The angle of attack is 7.1 °.It is appreciated that because the position of section A-A and cross section E-E can slightly change, therefore phase
Ying Di, the angle of attack chord long value at section A-A and cross section E-E also can change accordingly.
The chord length in above-mentioned each cross section and the setting of the angle of attack are all to be set with the size of oar dish.This reality
Execute in example, the length of blade 2 can be set to 90mm ± 9mm.Blade 2 is provided with connecting hole, uses
In being connected with oar folder 1, then this connecting hole is 14.5mm ± 1.45mm to the distance at the center of oar dish.
It addition, the screw provided according to the present embodiment, the pitch of blade can be 35mm, it may be assumed that
Blade rotates a circle, and the theoretical distance risen is 35mm.
The above-mentioned screw that the present embodiment is provided, by contrasting with screw of the prior art,
With reference to table one, it is known that, under identical pulling force, the power of the screw that the present embodiment is provided is lower,
Namely: under less power condition, the screw that the present embodiment is provided has bigger pulling force, from
And save kwh loss, increase endurance distance.Existing screw maximum is provided that the pulling force of 420g, and
The screw of the present embodiment is provided that the pulling force of 480g, and its performance is much better than existing screw.
The screw that table one the present embodiment is provided and the reduced parameter of prior art
The present embodiment also provides for a kind of Power Component, including actuator and the spiral that provided such as foregoing
Oar, this screw is connected with actuator by oar folder.Wherein, actuator is specifically as follows motor, motor
KV value be 1200 turns/(minute volt).
The present embodiment also provides for a kind of aircraft, including fuselage and above-mentioned Power Component, this Power Component
It is connected with fuselage.This aircraft uses above-mentioned Power Component, by three cross section chord lengths in blade and
The setting of the angle of attack, it is possible to reduce screw resistance in rotation process, improves power conversion efficiency, improves
The flying speed of aircraft, extends distance to go under certain power conditions supply, improves flying quality.
Last it is noted that various embodiments above is only in order to illustrate the technical solution of the utility model, and
Non-to its restriction；Although the utility model being described in detail with reference to foregoing embodiments, ability
The those of ordinary skill in territory is it is understood that it still can be to the technical scheme described in foregoing embodiments
Modify, or the most some or all of technical characteristic is carried out equivalent；And these amendment or
Person replaces, and does not make the essence of appropriate technical solution depart from the model of the utility model each embodiment technical scheme
Enclose.
Claims (17)
1. a screw, presss from both sides including oar and is connected to the blade on described oar folder, it is characterised in that
At the center of the oar dish formed with described screw at 55% for oar dish radius, described blade
Chord length be 16.7mm ± 5mm, the angle of attack is 14 ° ± 2.5 °；
At the center with described oar dish at 70% for oar dish radius, the chord length of described blade is
14.4mm ± 5mm, the angle of attack is 11.7 ° ± 2.5 °；
At the center with described oar dish at 85% for oar dish radius, the chord length of described blade is
12.2mm ± 5mm, the angle of attack is 9.3 ° ± 2.5 °.
Screw the most according to claim 1, it is characterised in that
At the center with described oar dish at 40% for oar dish radius, the chord length of described blade is
18.9mm ± 5mm, the angle of attack is 17.9 ° ± 2.5 °.
Screw the most according to claim 1, it is characterised in that in the center phase with described oar dish
At 100% for oar dish radius, the chord length of described blade is 8.9mm ± 5mm, the angle of attack is 7.1 ° ±
2.5°。
Screw the most according to claim 1, it is characterised in that the oar dish that described screw is formed
A diameter of 200mm ± 20mm；
At the center with described oar dish at for 55mm, the chord length of described blade is 16.7mm, the angle of attack
It it is 14 °；
At the center with described oar dish at for 70mm, the chord length of described blade is 14.4mm, the angle of attack
It it is 11.7 °；
At the center with described oar dish at for 85mm, the chord length of described blade is 12.2mm, the angle of attack
It it is 9.3 °.
Screw the most according to claim 2, it is characterised in that the oar dish that described screw is formed
A diameter of 200mm ± 20mm；
At the center with described oar dish at for 40mm, the chord length of described blade is 18.9mm, the angle of attack
It it is 17.9 °.
Screw the most according to claim 3, it is characterised in that the oar dish that described screw is formed
A diameter of 200mm ± 20mm；
At the center with described oar dish at for 100mm, the chord length of described blade is 8.9mm, the angle of attack
It it is 7.1 °.
Screw the most according to claim 1, it is characterised in that a length of 90mm of described blade
±9mm。
Screw the most according to claim 7, it is characterised in that described blade is provided with connecting hole,
Described connecting hole is 14.5mm ± 1.45mm to the distance at the center of oar dish.
9. according to the screw described in any one of claim 1-8, it is characterised in that described blade has
Blade back, blade face, connection blade back and the first lateral margin of blade face one side and connect blade back and blade face another
Second lateral margin of side；Described blade back and blade face are curved surface.
Screw the most according to claim 9, it is characterised in that described first lateral margin has song
The first of planar is arched upward portion, and the second lateral margin has curved second and arches upward portion.
11. screws according to claim 10, it is characterised in that described first arches upward portion and
Two portions of arching upward are respectively positioned on one end that described blade presss from both sides near oar.
12. screws according to claim 11, it is characterised in that described second arches upward the convex of portion
Go out the protrusion degree that degree arches upward portion less than first.
13. screws according to claim 12, it is characterised in that described blade is two, two
Individual blade is centrosymmetric about the center of described oar dish.
14. screws according to claim 13, it is characterised in that the pitch of described blade is
35mm。
15. 1 kinds of Power Components, it is characterised in that include actuator and such as any one of claim 1-14
Described screw, described screw is connected with described actuator by oar folder.
16. Power Components according to claim 15, it is characterised in that described actuator is motor,
The KV value of described motor is 1200 turns/(minute volt).
17. 1 kinds of aircraft, including fuselage, it is characterised in that also include that at least one is such as claim
Power Component described in 15 or 16, described Power Component is connected with described fuselage.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620083468.6U CN205524939U (en) | 2016-01-27 | 2016-01-27 | Screw, power component and aircraft |
| PCT/CN2016/099704 WO2017128744A1 (en) | 2016-01-27 | 2016-09-22 | Propeller, power assembly, and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620083468.6U CN205524939U (en) | 2016-01-27 | 2016-01-27 | Screw, power component and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205524939U true CN205524939U (en) | 2016-08-31 |
Family
ID=56772160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620083468.6U Expired - Fee Related CN205524939U (en) | 2016-01-27 | 2016-01-27 | Screw, power component and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN205524939U (en) |
| WO (1) | WO2017128744A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017128744A1 (en) * | 2016-01-27 | 2017-08-03 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
| WO2018058769A1 (en) * | 2016-09-27 | 2018-04-05 | 深圳市大疆创新科技有限公司 | Blade, airscrew, power package and unmanned aerial vehicle |
| WO2018058768A1 (en) * | 2016-09-27 | 2018-04-05 | 深圳市大疆创新科技有限公司 | Blade, airscrew, power package and unmanned aerial vehicle |
| 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 |
| 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 |
| WO2020024488A1 (en) * | 2018-08-01 | 2020-02-06 | 深圳市道通智能航空技术有限公司 | Propeller, power assembly and unmanned aerial vehicle |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4535550B2 (en) * | 2000-02-23 | 2010-09-01 | 富士重工業株式会社 | Rotor blade of rotorcraft |
| GB2400089B (en) * | 2003-04-04 | 2006-07-26 | Adrian Alexander Hubbard | High lift and high strength aerofoil section |
| US7600976B2 (en) * | 2005-05-31 | 2009-10-13 | Sikorsky Aircraft Corporation | Rotor blade twist distribution for a high speed rotary-wing aircraft |
| JP5995200B2 (en) * | 2012-03-09 | 2016-09-21 | 国立研究開発法人宇宙航空研究開発機構 | Variable pitch propeller |
| CN202765286U (en) * | 2012-05-25 | 2013-03-06 | 辽宁通用航空研究院 | High-efficiency propeller |
| CN102963522B (en) * | 2012-10-31 | 2015-04-22 | 中国航天空气动力技术研究院 | Near space propeller |
| CN104139849B (en) * | 2014-08-07 | 2015-02-25 | 西北工业大学 | High-altitude propeller and propeller tip winglet capable of improving efficiency of high-altitude propeller |
| 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 |
-
2016
- 2016-01-27 CN CN201620083468.6U patent/CN205524939U/en not_active Expired - Fee Related
- 2016-09-22 WO PCT/CN2016/099704 patent/WO2017128744A1/en active Application Filing
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017128744A1 (en) * | 2016-01-27 | 2017-08-03 | 深圳市大疆创新科技有限公司 | Propeller, power assembly, and aircraft |
| WO2018058769A1 (en) * | 2016-09-27 | 2018-04-05 | 深圳市大疆创新科技有限公司 | Blade, airscrew, power package and unmanned aerial vehicle |
| WO2018058768A1 (en) * | 2016-09-27 | 2018-04-05 | 深圳市大疆创新科技有限公司 | Blade, airscrew, power package and unmanned aerial vehicle |
| 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 |
| 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 |
| WO2020024488A1 (en) * | 2018-08-01 | 2020-02-06 | 深圳市道通智能航空技术有限公司 | Propeller, power assembly and unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| WO2017128744A1 (en) | 2017-08-03 |
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