WO2015176240A1

WO2015176240A1 - Power device and aircraft

Info

Publication number: WO2015176240A1
Application number: PCT/CN2014/077964
Authority: WO
Inventors: 陶冶; 邓涛
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2014-05-21
Filing date: 2014-05-21
Publication date: 2015-11-26
Also published as: CN104684805A; CN104684805B

Abstract

A power device and an aircraft. Said power device comprises a propeller and a motor. Said propeller comprises propeller blades (11) and a propeller hub (12). Said motor comprises a stator component (1), a rotor component (2) and a rotating shaft (3). Said rotor component (2) comprises a sleeve body (21) and a cover body (22). Said propeller hub (12) is provided with a center hole (121) and a first buckle portion (122). Said cover body (22) is provided with a second buckle portion (221). Said first buckle portion of the propeller hub and said second buckle portion of the cover body are matched through a buckle, and said rotating shaft is matched with said center hole of the propeller hub to fix said propeller on said motor. By the present invention, the motor and the propeller in an aircraft power device is more convenient to be assembled and disassembled. Meanwhile, the concentricity and the verticality of the motor and the propeller are ensured to a certain extent.

Description

Power plant and aircraft

[Technical Field]

The present invention relates to the field of flight technology, and in particular, to a power device and an aircraft.

【Background technique】

A rotorcraft is a flying device that uses a motor to drive a propeller to generate power to achieve space flight. Portable rotorcraft includes UAVs (Unmanned Aerial Vehicles) that are controlled by ground remote control, etc. These aircrafts are widely used because of their relatively low cost and the ability to provide lightweight, flexible low-altitude, low-speed flight. To a variety of civilian areas, especially in various fields of geographic mapping, aerial photography and so on.

The power device of the existing rotorcraft generally includes: a motor driver connected to the flight controller, a motor that drives the propeller to rotate, and a propeller, and the propeller is fixed between the motor and the propeller through a hole between the motor shaft and the propeller. On the motor. Specifically, the motor shaft is fixed by screwing between the shaft of the propeller and the hole of the propeller, or a protrusion is arranged on the rotating shaft of the motor, and a W slot is arranged in the hole of the propeller, and the propeller is fixed by the cooperation between the protrusion and the W slot. On the motor.

Although the propeller is well fixed to the motor by screwing, the assembly and disassembly generally require the use of tools, making the assembly and disassembly of the propeller inconvenient. While the fixing by the projections and the recesses is easy to assemble and disassemble, the cooperation of the projections and the grooves is easy to loosen, which is disadvantageous for the flight of the aircraft.

[Summary of the Invention]

The technical problem to be solved by the embodiments of the present invention is to provide a power device and an aircraft, which can effectively ensure that the propeller is fixed on the motor and is easy to assemble and disassemble.

An embodiment of the present invention provides a power device, including: a propeller and a motor, the propeller includes a blade and a hub, the motor includes a stator assembly, a rotor assembly, and a rotating shaft, and the rotor assembly includes a sleeve body and a cover body. among them:

The hub is provided with a central hole, a first fastening portion, and the cover body is provided with a second fastening portion; between the first fastening portion of the hub and the second fastening portion of the cover A snap fit, and the rotating shaft cooperates with a center hole of the hub to fix the propeller to the motor.

Wherein the first buckle portion of the hub and the second buckle portion of the cover body are buckled Fit.

Wherein, the rotating shaft and the central hole of the hub are an interference fit.

The first locking portion includes a fastening member, and the fastening member is fixed on the inner wall of the receiving cavity; the first fastening portion is disposed on the inner wall of the receiving cavity;

The bottom of the cover is connected to the sleeve, the second fastening portion is protruded from the upper surface of the cover, and the second fastening portion includes: a buckle with the first fastening portion a member - a snap fit projection and a resisting member for resisting the fastener of the first snap portion.

The bottom of the cover body is connected to the sleeve body, the second buckle portion is protruded from the upper surface of the cover body, and the second buckle portion includes a fastener;

The first latching portion is disposed on an inner wall of the receiving cavity, and the first latching portion includes: The fastener of the second fastening portion is a snap-fit projection and a resisting member for resisting the fastener of the second fastening portion.

The cover body and the second fastening portion provided on the cover body are integrally formed.

Wherein the paddle and the hub are integrally formed.

Wherein, the motor comprises a brushless motor.

Correspondingly, an embodiment of the present invention further provides an aircraft, including: an aircraft body and a power device fixed to the aircraft body, wherein the power device includes: a propeller and a motor, the propeller including a blade and a paddle a hub, the motor includes a stator assembly, a rotor assembly, and a rotating shaft, the rotor assembly including a sleeve body and a cover body, wherein:

Wherein, the first fastening portion of the hub and the second fastening portion of the cover are interference-fitted by the buckle.

Wherein, the rotating shaft has an interference fit with a center hole of the hub.

Wherein, the motor comprises a brushless motor.

In the embodiment of the present invention, the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion formed on the cover of the motor are more convenient. The assembly and disassembly of the motor and the propeller in the aircraft power unit are completed, and the concentricity and verticality of the motor and the propeller can be ensured to some extent. [Description of the Drawings]

1 is a schematic structural view of a motor of a power unit according to an embodiment of the present invention;

2 is a schematic structural view of a power unit according to an embodiment of the present invention;

3 is a schematic structural view of a portion of a propeller according to an embodiment of the present invention;

4 is a schematic structural view of a part of a motor according to an embodiment of the present invention;

Figure 5 is a schematic view showing another structure of a portion of a propeller according to an embodiment of the present invention;

Figure 6 is a cross-sectional view taken along line VI-VI of Figure 5;

7 is another schematic structural view of a part of a motor according to an embodiment of the present invention;

Figure 8 is a schematic cross-sectional view taken along line VIII-VIII of Figure 2.

The technical solutions in the embodiments of the present invention are clearly and completely described in the following with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of them. An embodiment. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without the creative work are all within the scope of the present invention.

In the embodiment of the present invention, the center hole of the propeller cooperates with the rotating shaft of the motor, and the first fastening portion of the propeller cooperates with the second fastening portion of the cover of the motor, and the two matching manners can be fixed by using an interference fit. Therefore, the assembly and disassembly work between the propeller and the motor can be better accomplished without tools, and the propeller can be better fixed to ensure flight safety.

A power device of one of the embodiments of the present invention will be described in detail below with reference to Figs. 1, 2, 3, 4 and 8.

1 is a schematic structural view of a motor of a power unit according to an embodiment of the present invention, FIG. 2 is a schematic structural view of a power unit according to an embodiment of the present invention, and FIG. 3 is a schematic view of a portion of a propeller according to an embodiment of the present invention. 4 is a schematic structural view of a part of a motor according to an embodiment of the present invention, and FIG. 8 is a schematic cross-sectional view taken along line VIII-VIII of FIG.

The power unit according to the present invention includes: a propeller and a motor, wherein the propeller includes a blade 11 and a hub 12, the motor includes a stator assembly 1, a rotor assembly 2, and a rotating shaft 3, and the rotor assembly 2 includes a casing 21. Cover body 22. The stator assembly 1 is located at one end of the sleeve body 21, and the sleeve The other end of the body 21 is fixedly coupled to the cover 22. It can be understood that the position between the stator assembly 1, the rotor assembly 2 and the rotating shaft 3 and the connection relationship thereof 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. As shown in FIG. 4, the cover 22 is provided with a second fastening portion 221; The first fastening portion 122 is snap-fitted with the second fastening portion 221 of the cover 22, and the rotating shaft 3 is engaged with the central hole 121 of the hub 12 to fix the propeller to the The power unit 2 is described so that the propeller is better fixed to the motor. In the embodiment of the present invention, the first fastening portion 122 includes four fasteners. In other embodiments, the first fastening portion 122 may include one, two, three, and the like as needed. As long as it can cooperate with the corresponding second hooking portion 221, the entire propeller can be fixed to the motor.

The first fastening portion 122 and the second fastening portion 221 are interference fit after being rotated or the like, and the rotating shaft 3 and the central hole 121 of the hub 12 are also interference fit. Through the cooperation between the rotating shaft 3 and the central hole 121 of the hub 12, not only the effect of fixing the propeller on the rotor assembly 2 of the motor and the removal of the propeller from the motor can be achieved, but also the motor and the motor can be better ensured. Concentricity between the shafts. Also, by the interference fit between the first fastening portion 122 and the second fastening portion 221 after rotation, the effect of better fixing the propeller on the motor and facilitating the removal of the propeller from the motor is further ensured. It is also possible to better ensure the verticality of the propeller.

Specifically, as shown in FIG. 3, the hub 12 is provided with a receiving cavity 123, the central hole 121 is disposed at a center of the receiving cavity 123, and the first fastening portion 122 includes at least two fasteners. In the case of the four fasteners 1221, the fasteners 1221 are fixed on the inner wall of the receiving cavity 123. Specifically, each of the two fasteners 1221 can be disposed at a fixed interval. The inner wall of the receiving cavity 123. Of course, other distribution means can also be used to fix the fasteners 1221 to ensure that the first fastening portion 122 and the second fastening portion 221 are fastened to better secure the propeller to the motor. Wherein, in the embodiment of the invention, the paddle and the hub may be integrally formed. The center hole 121 is fixed in the receiving cavity 123 by four symmetrical fixing members. The fixing member may include only one, two or three, etc., as long as the center hole 121 can be fixed in the receiving cavity 123. Just fine.

The bottom of the cover 22 is connected to the sleeve 21, as shown in FIG. 4, the second fastening portion 221 Protruding on the upper surface of the cover 22 includes: a protrusion 2211 that is snap-fitted with the fastener 1221 of the first fastening portion 122, and is configured to respectively resist the first fastening portion 122 The fastener of the fastener 2212. The cover 22 and the second fastening portion 221 disposed on the cover 22 may be integrally formed.

Further, the side surface of the cover 22 can be provided with a heat dissipation hole, which can effectively dissipate heat during the operation of the brushless single machine.

In the embodiment of the present invention, the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion opened on the cover of the motor can be more effective. The ground ensures that the propeller is fixed on the relevant components of the motor, and the assembly and disassembly between the motor and the propeller in the aircraft power device can be conveniently performed, and the concentricity and verticality of the motor and the propeller can be ensured to some extent.

Next, a power device of another configuration according to an embodiment of the present invention will be described in detail with reference to Figs. 1, 2, 5, 6, 7, and 8.

5 is a schematic structural view of another portion of a propeller according to an embodiment of the present invention; FIG. 6 is a cross-sectional view taken along line VI-VI of FIG. 5; and FIG. 7 is another schematic structural view of a portion of the motor of the embodiment of the present invention. .

As shown in FIG. 2, the power device according to the embodiment of the present invention includes: a propeller and a motor, wherein the propeller includes a blade 11 and a hub 12, and the motor includes a stator assembly 1, a rotor assembly 2, and a rotating shaft 3, The rotor assembly 2 includes a sleeve body 21 and a cover body 22. The sleeve 21 and the cover 22 may be in a fixed connection.

As shown in FIG. 6, the hub 12 is provided with a central hole 421 and a first fastening portion 422. As shown in FIG. 7, the cover 22 is provided with a second fastening portion 521; The first fastening portion 422 is snap-fitted with the second fastening portion 521 of the cover 22, and the rotating shaft 3 is engaged with the central hole 421 of the hub 12 to fix the propeller in the On the device assembly 2 of the motor.

The rotating shaft 3 and the central hole 421 of the hub 12 can be interference-fitted, and the first fastening portion 422 and the second locking portion 521 are interference fit after being rotated or the like. By the cooperation between the rotating shaft 3 and the central hole 421 of the hub 12, not only the propeller and the fixed motor can be fixed on the motor. In order to remove the propeller from the motor, it is also possible to better ensure the concentricity between the motor and the shaft. Also, by the interference fit between the first fastening portion 422 and the second fastening portion 521 after rotation, the effect of better fixing the propeller on the motor and facilitating the removal of the propeller from the motor is further ensured. It is also possible to better ensure the verticality of the propeller.

The bottom of the cover body 22 is connected to the sleeve body 21. As shown in FIG. 7, the second fastening portion 521 is protruded from the upper surface of the cover body 22. The second fastening portion 521 includes At least two fasteners 5211; specifically, a fixed spacing size distribution between each of the two fasteners 5211. Of course, it is also possible to fix the fasteners 5211 by other distribution means to ensure that the first fastening portion 122 and the second fastening portion 221 are fastened to better fix the propeller on the motor. In the embodiment of the present invention, the cover 22 and the second fastening portion 221 disposed on the cover 22 may be integrally formed. The number of fasteners of the second fastening portion 521 may include only one, two or three or the like as needed, as long as the first fastening portion 422 can cooperate with the first fastening portion 422 to fix the propeller to the motor.

As shown in FIG. 6, the hub 12 is provided with a receiving cavity 423. The center hole 421 is disposed at a center of the receiving cavity 423, and the first fastening portion 422 is disposed at the receiving cavity 423. On the inner wall, the first fastening portion 422 includes: a protrusion 4221 that is engaged with the fastening member 5211 of the second fastening portion 521, and a fastener for resisting the second fastening portion 521 The resisting member 4222 of 5211. Wherein, in the embodiment of the invention, the paddle and the hub may be integrally formed.

An embodiment of the present invention further provides an aircraft, the aircraft comprising: an aircraft body and a power device fixed to the aircraft body, wherein the power device comprises: a propeller and a motor, The propeller includes a paddle, a hub, the motor includes a stator assembly, a rotor assembly, and a rotating shaft, and the rotor assembly includes a sleeve body and a cover body, wherein:

The hub is provided with a central hole, a first fastening portion, and the cover body is provided with a second fastening portion; between the first fastening portion of the hub and the second fastening portion of the cover A snap fit, and the shaft cooperates with a central bore of the hub to secure the propeller to an associated component of the motor to secure the propeller on the motor.

A first interference between the first fastening portion of the hub and the second fastening portion of the cover body is achieved by a snap fit. The rotating shaft is in an interference fit with a center hole of the hub.

The hub is provided with a receiving cavity, the central hole is disposed at a center of the receiving cavity, and the first fastening portion includes at least two fasteners, and at least two fasteners are fixed to the receiving cavity On the inner wall; the paddle and the hub are integrally formed.

The bottom of the cover body is connected to the sleeve body, and the second fastening portion is protruded from the upper surface of the cover body, and includes: a buckle that is engaged with the first buckle portion a projection, and a resisting member for respectively resisting the fastener of the first fastening portion. The cover body and the second fastening portion provided on the cover body are integrally formed.

A heat dissipation hole is defined in a side surface of the cover body. The motor includes a brushless motor. For a detailed description of the related structure of the power component in the aircraft of the embodiment of the present invention, reference may be made to the description of the corresponding contents of the above FIG. 1 to FIG.

In the embodiment of the present invention, the cooperation between the center hole of the hub and the motor shaft, and the first buckle portion opened in the hub and the second buckle portion opened on the cover of the motor can be more effective. The ground ensures that the propeller is fixed on the motor, and the assembly and disassembly of the motor and the propeller in the aircraft power unit can be conveniently performed, and the concentricity and verticality of the motor and the propeller can be ensured to a certain extent, thereby making the flight of the aircraft more convenient. stable.

The above is only the embodiment of the present invention, and is not intended to limit the scope of the invention, and the equivalent structure or equivalent process transformations made by the specification and the drawings of the present invention may be directly or indirectly applied to other related technologies. The scope of the invention is included in the scope of patent protection of the present invention.

Claims

Rights request

What is claimed is: 1. A power unit, comprising: a propeller and a motor, the propeller comprising a blade, a hub, the motor comprising a stator assembly, a rotor assembly and a rotating shaft, the rotor assembly comprising a sleeve body and a cover body, among them:

2. The power unit according to claim 1, wherein the first hooking portion of the hub and the second latching portion of the cover are engaged by a snap fit.

3. The power unit according to claim 1, wherein the rotating shaft is in an interference fit with a center hole of the hub.

4. A power unit according to any one of claims 1 to 3, characterized in that

The hub is provided with a receiving cavity, the center hole is disposed at a center of the receiving cavity, and the first fastening portion includes a fastener, and the fastener is fixed on an inner wall of the receiving cavity;

The power unit according to any one of claims 1 to 3, characterized in that

The bottom of the cover is connected to the sleeve, the second fastening portion is protruded from the upper surface of the cover, and the second fastening portion includes a fastener;

The hub is provided with a receiving cavity, and the center hole is disposed at a center of the receiving cavity, and the first fastening portion includes: a convexity that is snap-fitted with the fastener of the second fastening portion And a resisting member for resisting the fastener of the second fastening portion.

6. The power unit according to claim 1, wherein the cover body and the cover are disposed on the cover The second buckle portion of the body is integrally formed

7. The power unit according to claim 1, wherein the paddle and the hub are integrally formed.

8. The power unit of claim 1 wherein said motor comprises a brushless motor.

9. An aircraft, comprising: an aircraft body and a power unit fixed to the aircraft body, wherein the power unit comprises: a propeller and a motor, the propeller including a blade, a hub, The motor includes a stator assembly, a rotor assembly, and a rotating shaft, the rotor assembly including a sleeve body and a cover body, wherein:

10. The aircraft of claim 9, wherein the first snap portion of the hub and the second snap portion of the cover are interference-fitted by a snap.

11. The aircraft of claim 9, wherein the rotating shaft is in interference fit with a center hole of the hub.

12. An aircraft according to any of claims 9-11, wherein the electric machine comprises a brushless motor.