CN106043682B - Screw, motor, power device and aircraft - Google Patents
Screw, motor, power device and aircraft Download PDFInfo
- Publication number
- CN106043682B CN106043682B CN201610521251.3A CN201610521251A CN106043682B CN 106043682 B CN106043682 B CN 106043682B CN 201610521251 A CN201610521251 A CN 201610521251A CN 106043682 B CN106043682 B CN 106043682B
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- propeller
- hub
- motor
- buckling part
- buckling
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
The invention provides a propeller, a motor, a power device with the propeller and the motor, and an aircraft with the propeller and the motor. Wherein, the screw includes paddle, propeller hub, the motor includes the rotor subassembly, the rotor subassembly includes the lid, wherein: the propeller hub is provided with a first buckling part, and the cover body is provided with a second buckling part; the first buckling part of the propeller hub is in buckling fit with the second buckling part of the cover body, so that the propeller is fixed on the motor. The invention can conveniently finish the assembly and disassembly of the motor and the propeller in the aircraft power device, and can ensure the verticality of the motor and the propeller to a certain extent.
Description
The application is a divisional application of an invention patent application with the international application number of PCT/CN2014/077964, the international application date of 5-21 2014, the application number of 201480002509.8 entering the Chinese national stage and the name of 'a power device and an aircraft'.
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of flight, in particular to a propeller, a motor, a power device and an aircraft.
[ background of the invention ]
The rotor craft is a flying device which drives a propeller to rotate through a motor to generate power so as to realize space flight. Portable rotorcraft, including some UAVs (Unmanned Aerial vehicles) that complete flight by ground remote control, etc., have been widely used in various civil fields, especially in various geographic mapping and Aerial photography, due to their relatively low cost and capability of providing light, flexible, low altitude, and low speed flight.
The power plant of an existing rotorcraft generally comprises: the motor driver is connected with the flight controller, the motor drives the propeller to rotate and the propeller, and the motor and the propeller are matched with each other through a motor rotating shaft and holes formed in the propeller to fix the propeller on the motor. The method specifically comprises the following steps: the motor is fixed in a rotating shaft and a hole of the propeller through a thread mode, or a protrusion is arranged on the rotating shaft of the motor, a groove is arranged in the hole of the propeller, and the propeller is fixed on the motor through the matching between the protrusion and the groove.
Although the screw propeller can be well fixed on the motor by the screw thread fixing mode, tools are generally needed for assembling and disassembling the screw propeller, so that the screw propeller is inconvenient to assemble and disassemble. Although the fixing mode of matching the protrusion and the groove is easy to assemble and disassemble, the matching of the protrusion and the groove is easy to loose, which is not beneficial to the flight of the aircraft.
[ summary of the invention ]
The technical problem mainly solved by the embodiment of the invention is to provide a propeller, a motor, a power device and an aircraft, which can effectively ensure that the propeller is fixed on the motor and are easy to assemble and disassemble.
The embodiment of the invention provides a propeller, which comprises blades and a propeller hub, wherein the propeller is used for being assembled on a motor, the motor comprises a rotor assembly, the propeller hub is provided with a first buckling part, and the first buckling part of the propeller hub is in buckling fit with a second buckling part arranged on the rotor assembly, so that the propeller is fixed on the motor.
Further, the first buckling part of the propeller hub is in buckling fit with the second buckling part of the cover body.
Further, the first buckling part and the second buckling part are in interference fit after rotation.
Furthermore, the hub is provided with an accommodating cavity, the first buckling part comprises a fastener, and the fastener is fixedly arranged on the inner wall of the accommodating cavity; or
The oar hub has been seted up and has been acceptd the chamber, first buckle portion set up in on acceping the inner wall in chamber, first buckle portion includes: the buckle comprises bulges matched with the fasteners of the second buckling part in a one-to-one buckling mode, and a blocking piece used for blocking the fasteners of the second buckling part.
Further, the blades and the hub are integrally formed.
Further, the propeller hub is provided with a center hole, the motor further comprises a rotating shaft, and the center hole of the propeller hub is matched with the rotating shaft.
Further, the central hole of the hub is in interference fit with the rotating shaft.
Furthermore, the hub is provided with an accommodating cavity, and the central hole is formed in the central position of the accommodating cavity.
The embodiment of the invention also provides a motor which comprises a rotor assembly, wherein the motor is used for assembling the propeller and driving the propeller to rotate, the propeller comprises blades and a propeller hub, the rotor assembly comprises a cover body, the cover body is provided with a buckling part, and the buckling part of the cover body is in buckling fit with the buckling part of the propeller hub so that the propeller is fixed on the motor.
Furthermore, the buckling part of the cover body is in buckling fit with the buckling part of the propeller hub.
Further, the buckling part of the cover body and the buckling part of the propeller hub are in interference fit after rotation.
Further, the buckle portion protruding of lid is located the upper portion surface of lid, the buckle portion of lid includes: the hub comprises protrusions which are in one-to-one buckling fit with fasteners of the buckling part of the hub, and a resisting part for resisting the fasteners of the buckling part of the hub; or, the buckling part of the cover body comprises a fastener.
Further, the motor still includes stator module, the rotor subassembly still includes the cover body, stator module is located the one end of the cover body, the bottom of lid with the other end of the cover body links to each other.
Further, the cover body and a buckling part of the cover body arranged on the cover body are integrally formed.
Further, the motor includes a brushless motor.
Furthermore, the side surface of the cover body is provided with heat dissipation holes.
Further, the motor also comprises a rotating shaft, the hub is provided with a central hole, and the rotating shaft is matched with the central hole of the hub.
Further, the rotating shaft is in interference fit with the central hole of the hub.
The embodiment of the invention also provides a power device, which comprises: the propeller and the motor.
An embodiment of the present invention further provides an aircraft, including: the power device is fixedly arranged on the aircraft body and comprises the propeller and the motor.
In the embodiment of the invention, based on the buckling and matching of the first buckling part arranged in the propeller hub and the second buckling part arranged on the cover body of the motor, the assembly and disassembly of the motor and the propeller in the aircraft power device can be conveniently completed, and the verticality of the motor and the propeller can be ensured to a certain extent.
[ description of the drawings ]
FIG. 1 is a schematic view of a configuration of a motor of a power plant in accordance with an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a power plant according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of a configuration of portions of a propeller according to an embodiment of the present invention;
fig. 4 is a schematic structural view of a part of a motor according to an embodiment of the present invention;
FIG. 5 is another schematic illustration of a portion of a propeller according to an embodiment of the present invention;
FIG. 6 is a schematic sectional view taken along line VI-VI in FIG. 5;
fig. 7 is another structural schematic diagram of a part of the motor according to the embodiment of the present invention;
fig. 8 is a schematic sectional view taken along line VIII-VIII in fig. 2.
[ detailed description ] embodiments
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the embodiment of the invention, the central hole of the propeller is matched with the rotating shaft of the motor, the first buckling part of the propeller is matched with the second buckling part on the cover body of the motor, and the two matching modes can be fixed in a manner of interference fit and the like, so that the assembling and disassembling work between the propeller and the motor can be well completed without tools, the propeller can be well fixed, and the flight safety is ensured.
The power plant of one structure according to the embodiment of the present invention will be described in detail with reference to fig. 1, 2, 3, 4 and 8.
Fig. 1 is a schematic structural diagram of a motor of a power plant according to an embodiment of the present invention, fig. 2 is a schematic structural diagram of a power plant according to an embodiment of the present invention, fig. 3 is a schematic structural diagram of a portion of a propeller according to an embodiment of the present invention, fig. 4 is a schematic structural diagram of a portion of a motor according to an embodiment of the present invention, and fig. 8 is a schematic sectional view taken along line VIII-VIII in fig. 2.
The power device of the invention comprises: the propeller comprises a propeller body 11 and a propeller hub 12, the motor comprises a stator assembly 1, a rotor assembly 2 and a rotating shaft 3, and the rotor assembly 2 comprises a sleeve body 21 and a cover body 22. The stator assembly 1 is located at one end of the sleeve body 21, and the other end of the sleeve body 21 is fixedly connected with the cover body 22. It is understood that the positions and the connection relationship among the stator assembly 1, the rotor assembly 2, and the rotating shaft 3 can be referred to the prior art.
As shown in fig. 3, the hub 12 is provided with a central hole 121 and a first fastening portion 122, and as shown in fig. 4, the cover 22 is provided with a second fastening portion 221; the first fastening portion 122 of the hub 12 is in snap fit with the second fastening portion 221 of the cover 22, and the rotating shaft 3 is in fit with the central hole 121 of the hub 12, so that the propeller is fixed on the power assembly 2 to be well fixed on the motor. In the embodiment of the present invention, the first fastening portion 122 includes 4 fasteners, and in other embodiments, the first fastening portion 122 may include 1, 2, 3, etc. as needed, as long as it can cooperate with the corresponding second fastening portion 221 to fix the entire propeller on the motor.
The first buckling part 122 and the second buckling part 221 are in interference fit after rotation and the like, and the rotating shaft 3 and the central hole 121 of the hub 12 can also be in interference fit. Through the cooperation between the rotating shaft 3 and the center hole 121 of the propeller hub 12, the effects of fixing the propeller on the rotor assembly 2 of the motor and facilitating the detachment of the propeller from the motor can be achieved, and the concentricity between the motor and the rotating shaft can be well guaranteed. Through the interference fit between the first buckling part 122 and the second buckling part 221 after rotation, the effect of better fixing the propeller on the motor and facilitating the detachment of the propeller from the motor is further ensured, and the verticality of the propeller can be better ensured.
As shown in fig. 3, the hub 12 has a receiving cavity 123, the central hole 121 is disposed at a central position of the receiving cavity 123, the first fastening portion 122 includes at least two fasteners, fig. 3 shows 4 fasteners 1221, and each fastener 1221 is fixed on an inner wall of the receiving cavity 123; particularly, every two fasteners 1221 can be distributed on the inner wall of the receiving cavity 123 with a fixed spacing size. Of course, other distribution ways may be adopted to fix the fasteners 1221 to ensure that the first fastening portion 122 and the second fastening portion 221 are fastened, so as to fix the propeller on the motor better. Wherein, in the embodiment of the invention, the blade and the hub can be integrally formed. The central hole 121 is fixed in the receiving cavity 123 by 4 symmetrical fixing members, and the number of the fixing members may be only 1, 2, or 3, so long as the central hole 121 can be fixed in the receiving cavity 123.
The bottom of the cover 22 is connected to the sleeve 21, as shown in fig. 4, the second fastening portion 221 is convexly disposed on the upper surface of the cover 22, and includes: a protrusion 2211 which is in one-to-one snap fit with the fasteners 1221 of the first buckling part 122, and a blocking part 2212 which is used for respectively blocking the fasteners of the first buckling part 122. The cover 22 and the second locking portion 221 disposed on the cover 22 may be integrally formed.
Further, the side surface of the cover 22 may be provided with heat dissipation holes, so as to effectively dissipate heat generated during the operation of the brushless single machine.
In the embodiment of the invention, based on the matching of the central hole of the propeller hub and the motor rotating shaft and the buckling and matching of the first buckling part arranged in the propeller hub and the second buckling part arranged on the cover body of the motor, the propeller can be effectively ensured to be fixed on related parts of the motor, the assembly and disassembly between the motor and the propeller in the aircraft power device can be conveniently completed, and the concentricity and the verticality of the motor and the propeller can be ensured to a certain extent.
The power plant of another structure according to the embodiment of the present invention will be described in detail with reference to fig. 1, fig. 2, fig. 5, fig. 6, fig. 7, and fig. 8.
FIG. 5 is another schematic illustration of a portion of a propeller according to an embodiment of the present invention; FIG. 6 is a schematic sectional view taken along line VI-VI in FIG. 5; fig. 7 is another structural schematic diagram of a part of the motor according to the embodiment of the present invention.
As shown in fig. 2, the power plant according to the embodiment of the present invention includes: the propeller comprises a propeller body 11 and a propeller hub 12, the motor comprises a stator assembly 1, a rotor assembly 2 and a rotating shaft 3, and the rotor assembly 2 comprises a sleeve body 21 and a cover body 22. The sleeve body 21 and the cover body 22 can be fixedly connected.
As shown in fig. 6, the hub 12 is provided with a central hole 421 and a first fastening portion 422, and as shown in fig. 7, the cover 22 is provided with a second fastening portion 521; the first fastening portion 422 of the hub 12 is in snap fit with the second fastening portion 521 of the cover 22, and the rotating shaft 3 is in fit with the central hole 421 of the hub 12, so that the propeller is fixed on the device assembly 2 of the motor.
The rotating shaft 3 and the central hole 421 of the hub 12 can be in interference fit, and the first buckling part 422 and the second buckling part 521 are in interference fit after rotation and the like. Through the cooperation between the rotating shaft 3 and the center hole 421 of the propeller hub 12, the effect of fixing the propeller on the motor and being convenient for detaching the propeller from the motor can be achieved, and the concentricity between the motor and the rotating shaft can be well ensured. Through first buckle portion 422 with interference fit after rotating between the second buckle portion 521, further ensured the effect of fixed screw better on the motor and being convenient for dismantle the screw from the motor, can also guarantee the straightness that hangs down of screw better.
The bottom of the cover 22 is connected to the sleeve 21, as shown in fig. 7, the second fastening portion 521 is disposed on the upper surface of the cover 22 in a protruding manner, and the second fastening portion 521 includes at least two fasteners 5211; a fixed spacing size distribution may be used between every two fasteners 5211. Of course, other distribution ways may also be adopted to fix the fasteners 5211 to ensure that the first locking portion 122 and the second locking portion 221 are locked, so as to fix the propeller on the motor better. In the embodiment of the present invention, the cover 22 and the second fastening portion 221 disposed on the cover 22 can be integrally formed. The number of the fasteners of the second fastening part 521 may only include 1, 2 or 3 fasteners as required, as long as the fasteners can be matched with the first fastening part 422 to fix the propeller on the motor well.
As shown in fig. 6, the hub 12 has a receiving cavity 423, the central hole 421 is disposed at a central position of the receiving cavity 423, the first locking portion 422 is disposed on an inner wall of the receiving cavity 423, and the first locking portion 422 includes: projections 4221 snap-fitted with the fasteners 5211 of the second fastening part 521 one by one, and a blocking member 4222 for blocking the fasteners 5211 of the second fastening part 521. Wherein, in the embodiment of the invention, the blade and the hub can be integrally formed.
Further, the side surface of the cover 22 may be provided with heat dissipation holes, so as to effectively dissipate heat generated during the operation of the brushless single machine.
In the embodiment of the invention, based on the matching of the central hole of the propeller hub and the motor rotating shaft and the buckling and matching of the first buckling part arranged in the propeller hub and the second buckling part arranged on the cover body of the motor, the propeller can be effectively ensured to be fixed on related components of the motor, the assembly and disassembly between the motor and the propeller in the aircraft power device can be conveniently completed, and the concentricity and the verticality of the motor and the propeller can be ensured to a certain extent.
An embodiment of the present invention further provides an aircraft, including: aircraft main part and the power device who sets firmly in the aircraft main part, wherein, power device includes: screw and motor, the screw includes paddle, propeller hub, the motor includes stator module, rotor subassembly and pivot, the rotor subassembly is including the cover body, lid, wherein:
the propeller hub is provided with a central hole and a first buckling part, and the cover body is provided with a second buckling part;
the first buckling part of the propeller hub is in buckling fit with the second buckling part of the cover body, and the rotating shaft is matched with the center hole of the propeller hub, so that the propeller is fixed on a related component of the motor to realize the fixation of the propeller on the motor.
The first buckling part of the propeller hub is in interference fit with the second buckling part of the cover body through a buckle.
The rotating shaft is in interference fit with the central hole of the hub.
The propeller hub is provided with an accommodating cavity, the central hole is formed in the center of the accommodating cavity, the first buckling part comprises at least two fasteners, and the at least two fasteners are fixedly arranged on the inner wall of the accommodating cavity; the blades and the hub are integrally formed.
The bottom of lid with the cover body links to each other, the protruding locating of second buckle portion the upper portion surface of lid includes: the buckle comprises a bulge which is matched with the fasteners of the first buckling part in a one-to-one buckling mode, and a blocking part which is used for respectively blocking the fasteners of the first buckling part. The cover body and a second buckling part arranged on the cover body are integrally formed.
The side surface of the cover body is provided with heat dissipation holes. The motor comprises a brushless motor. The specific description of the structure related to the power assembly in the aircraft according to the embodiment of the invention can refer to the description of the corresponding contents in fig. 1 to 8.
In the embodiment of the invention, based on the matching of the central hole of the propeller hub and the motor rotating shaft and the buckling and matching of the first buckling part arranged in the propeller hub and the second buckling part arranged on the cover body of the motor, the propeller can be effectively ensured to be fixed on the motor, the assembly and disassembly of the motor and the propeller in the power device of the aircraft can be conveniently completed, and the concentricity and the perpendicularity of the motor and the propeller can be ensured to a certain extent, so that the flight of the aircraft is more stable.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (16)
1. A propeller comprises blades and a propeller hub, wherein the propeller is used for being assembled on a motor, the motor comprises a rotor assembly, and the propeller is characterized in that the propeller hub is provided with a first buckling part, the first buckling part of the propeller hub is in buckling fit with a second buckling part arranged on the rotor assembly, so that the propeller is fixed on the motor, and the first buckling part and the second buckling part are in interference fit after rotation;
the propeller hub is provided with an accommodating cavity, the first buckling part comprises a fastener, and the fastener is fixedly arranged on the inner wall of the accommodating cavity and protrudes towards the inside of the accommodating cavity; the second buckling part comprises bulges which are in one-to-one buckling fit with the fasteners of the first buckling part, and a resisting piece which is used for resisting the fasteners of the first buckling part at the outer side of the fasteners of the first buckling part; or
The rotor assembly comprises a cover body, the second buckling part is convexly arranged on the upper surface of the cover body, and the second buckling part comprises a fastener; and, the oar hub has been seted up and has been acceptd the chamber, first buckle portion set up in accept on the inner wall in chamber, first buckle portion includes: the buckle comprises a bulge which is matched with the fasteners of the second buckling part in a one-to-one buckling mode, and a blocking piece which is used for blocking the fasteners of the second buckling part at the outer side of the fasteners of the second buckling part.
2. The propeller of claim 1 wherein the first catch portion of the hub and the second catch portion of the cover are snap-fit.
3. The propeller of claim 1 wherein said blades and said hub are integrally formed.
4. The propeller of claim 1 wherein the hub is provided with a central bore and the motor further comprises a shaft, the hub central bore engaging the shaft.
5. The propeller of claim 4 wherein the central bore of the hub is an interference fit with the shaft.
6. A propeller as claimed in claim 4 or claim 5 wherein said central aperture is located centrally of said receiving cavity.
7. A motor comprises a rotor assembly, wherein the motor is used for assembling a propeller and driving the propeller to rotate, and the propeller comprises blades and a propeller hub;
the buckle portion protruding of lid is located the upper portion surface of lid, the buckle portion of lid includes: the hub comprises protrusions which are in one-to-one buckling fit with fasteners of a buckling part of the hub, and a resisting piece which is used for resisting the fasteners of the buckling part of the hub at the outer side of the fasteners of the buckling part of the hub;
or, the buckle portion of lid includes the fastener, the protruding buckle portion of lid is located the upper portion surface of lid, the buckle portion of propeller hub includes: the buckle part of the cover body is provided with a plurality of buckles matched with the buckles of the buckle part of the cover body, and a plurality of blocking pieces used for blocking the buckles of the buckle part of the cover body outside the buckles of the cover body.
8. The electric machine of claim 7 wherein the latch of the cover and the latch of the hub are snap-fit.
9. The electric machine of claim 7, further comprising a stator assembly, the rotor assembly further comprising a jacket body, the stator assembly located at one end of the jacket body, the bottom of the cover body coupled to the other end of the jacket body.
10. The motor of claim 7, wherein the cover and a latch portion of the cover disposed on the cover are integrally formed.
11. The motor of claim 7, wherein the motor comprises a brushless motor.
12. The motor of claim 7, wherein the side of the cover is provided with heat dissipation holes.
13. The electric machine of claim 7 further comprising a shaft, the hub being provided with a central aperture, the shaft engaging the central aperture of the hub.
14. The electric machine of claim 13 wherein said shaft is an interference fit with said hub central bore.
15. A power plant, comprising:
a propeller as claimed in any one of claims 1 to 3; and
an electrical machine as claimed in any one of claims 7 to 12.
16. An aircraft, comprising: aircraft main part and power device, power device set firmly in on the aircraft main part, power device includes:
a propeller as claimed in any one of claims 1 to 3; and
an electrical machine as claimed in any one of claims 7 to 12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610521251.3A CN106043682B (en) | 2014-05-21 | 2014-05-21 | Screw, motor, power device and aircraft |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201480002509.8A CN104684805B (en) | 2014-05-21 | 2014-05-21 | A kind of power set and aircraft |
| CN201610521251.3A CN106043682B (en) | 2014-05-21 | 2014-05-21 | Screw, motor, power device and aircraft |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480002509.8A Division CN104684805B (en) | 2014-05-21 | 2014-05-21 | A kind of power set and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106043682A CN106043682A (en) | 2016-10-26 |
| CN106043682B true CN106043682B (en) | 2021-04-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610521251.3A Active CN106043682B (en) | 2014-05-21 | 2014-05-21 | Screw, motor, power device and aircraft |
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| Country | Link |
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| CN (1) | CN106043682B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111003168B (en) * | 2016-10-28 | 2021-12-17 | 深圳市大疆创新科技有限公司 | Locking mechanical system, screw, motor, driving system subassembly and aircraft |
| CN209410327U (en) * | 2018-09-30 | 2019-09-20 | 深圳市大疆创新科技有限公司 | A kind of propeller arrangement, power device and unmanned vehicle |
| CN116710358A (en) * | 2021-05-14 | 2023-09-05 | 深圳市大疆创新科技有限公司 | Propeller, power device, power system and unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2649824Y (en) * | 2003-10-20 | 2004-10-20 | 达隆科技股份有限公司 | Fan blade hub structure |
| CN201140796Y (en) * | 2007-10-23 | 2008-10-29 | 郑海燕 | Split type coarse pitch four-leaf conical screw propeller |
| CN202464124U (en) * | 2012-01-13 | 2012-10-03 | 安徽理工大学 | Four-rotor aircraft |
| CN203306224U (en) * | 2013-05-31 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Propeller and aircraft provided with same |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE7914134U1 (en) * | 1979-05-16 | 1979-10-04 | Johannes Graupner Kg, 7312 Kirchheim | SPINNER FOR PROPELLER |
| US5593283A (en) * | 1994-08-08 | 1997-01-14 | Eaton Corporation | Fan and fan drive and assembly thereof |
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2014
- 2014-05-21 CN CN201610521251.3A patent/CN106043682B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2649824Y (en) * | 2003-10-20 | 2004-10-20 | 达隆科技股份有限公司 | Fan blade hub structure |
| CN201140796Y (en) * | 2007-10-23 | 2008-10-29 | 郑海燕 | Split type coarse pitch four-leaf conical screw propeller |
| CN202464124U (en) * | 2012-01-13 | 2012-10-03 | 安徽理工大学 | Four-rotor aircraft |
| CN203306224U (en) * | 2013-05-31 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Propeller and aircraft provided with same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043682A (en) | 2016-10-26 |
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