WO2016106711A1 - Motor, power device and aircraft using power device - Google Patents

Abstract

A motor (100), comprising a stator (30), and a rotor (50) and a cover body (70) rotatably covering the stator; the cover body comprises a blade (76) and a connection portion (743) connected to the rotor; the cover body is provided with a slit (741) thereon for air to flow; when the motor operates, the rotor drives the cover body to rotate, such that the blade drives surrounding air to flow, and the air in the rotor is driven out from the slit to remove the heat generated by the motor. The motor has a high heat dissipation efficiency and reduces dust build-up. Also disclosed are a power device using the motor, and aircraft using the power device.

Description

Motor, power unit and aircraft using the same Technical field

The present invention relates to an electric machine, a power unit using the same, and an aircraft using the same.

Background technique

Brushless motors are widely used in mechatronics applications due to their low loss, low noise, smooth operation and long life. Generally, a brushless motor includes a base, a stator disposed on the base, a rotor disposed on the stator, and an outer cover coupled to the rotor. Generally, the outer cover is of an open structure having a large opening to facilitate heat dissipation of the motor, and heat generated by the operation of the motor is radiated into the air through the open cover.

However, the heat dissipation of the above brushless motor is only radiated by natural heat radiation, and the heat dissipation efficiency is low, which easily causes the motor magnet to fail due to high temperature. In addition, impurities such as dust in the environment easily enter the inside of the motor through the open cover, and cover the internal components of the motor. In severe cases, the motor may not operate smoothly or even operate.

Summary of the invention

In view of the above circumstances, it is necessary to provide a motor that is highly efficient in heat dissipation and dustproof, and it is also necessary to provide a power unit using the motor and an aircraft using the power unit.

An electric machine includes: a stator; a rotor rotatably disposed outside the stator; and a cover disposed on the rotor. The cover body includes a blade, and the cover body is provided with a slit. Wherein, when the motor is in operation, the rotor drives the cover to rotate, and the rotation of the blade enables air in the rotor to be discharged from the slit to take away heat generated by the motor.

Further, the cover body further includes a sidewall and a top wall, the top wall is disposed at an end of the sidewall away from the rotor, and the blade is disposed at a side of the top wall facing the rotor.

Further, the slit penetrates through at least one of the top wall and the side wall, and communicates with an inner space of the rotor.

Further, the number of the blades is plural, and the plurality of the blades are radially arranged on the top wall at intervals.

Further, each of the blades is a curved blade, and two adjacent sides of each of the blades are respectively connected to the top wall and the side wall.

Further, the cover body further includes a plurality of guiding portions connected to the side walls, the plurality of guiding portions are spaced apart from each other and are respectively received in the rotor and fixedly connected to the rotor.

Further, an end of the guiding portion away from the side wall is formed with a guiding surface, and the guiding surface is inclined with respect to a central axis of the side wall.

Further, the motor further includes a base, the base includes a fixing portion and a heat dissipating portion disposed on the fixing portion, and the stator is fixedly disposed on the fixing portion and adjacent to the heat dissipating portion.

Further, the motor further includes a rotating shaft coaxially disposed with the rotor, and one end of the rotating shaft is inserted into the fixing portion, and the other end is connected to the cover.

Further, the number of the heat dissipating portions is plural, and the plurality of heat dissipating portions are spaced apart from each other on the outer peripheral wall of the fixing portion and extend in a direction away from the fixing portion.

Further, the pedestal further includes a mounting portion connected to one end of the plurality of heat dissipating portions away from the fixing portion, and each of the two adjacent heat dissipating portions and the corresponding mounting portion A vent hole for allowing air to flow is formed therebetween, and a plurality of the vent holes formed by the plurality of heat radiating portions and the mounting portion communicate with a space inside the rotor.

Further, the mounting portion is provided with a plurality of air suction holes, and each of the air suction holes communicates with the air vent holes to communicate with the space inside the rotor through the vent holes.

Further, the base further includes a cushion, and the mounting portion is provided with a plurality of mounting slots, and the cushion is installed in the mounting slot.

Further, the heat dissipating portion includes a body disposed on the fixing portion, and the through hole is formed through the body to allow air to circulate.

Further, the heat dissipating portion further includes a heat dissipating end formed by the surface of the main body, and the heat dissipating end is at least one of a heat dissipating fin, a heat dissipating fin, and a heat dissipating cylinder.

A power unit includes a motor and a propeller. The motor includes: a stator; a rotor rotatably disposed outside the stator; and a cover disposed on the rotor. The propeller is fixedly disposed on the cover body; the cover body includes a blade, and the cover body is provided with a slit. Wherein, when the motor is in operation, the rotor drives the cover to rotate, and the rotation of the blade enables air in the rotor to be discharged from the slit to take away heat generated by the motor.

Further, the cover body further includes a sidewall and a top wall, the top wall is disposed at an end of the sidewall away from the rotor, and the blade is disposed at a side of the top wall facing the rotor.

Further, the slit penetrates through at least one of the top wall and the side wall, and communicates with an inner space of the rotor.

Further, the number of the blades is plural, and the plurality of the blades are radially arranged on the top wall at intervals.

Further, each of the blades is a curved blade, and two adjacent sides of each of the blades are respectively connected to the top wall and the side wall.

Further, the cover body further includes a plurality of guiding portions connected to the side walls, the plurality of guiding portions are spaced apart from each other and are respectively received in the rotor and fixedly connected to the rotor.

Further, an end of the guiding portion away from the side wall is formed with a guiding surface, and the guiding surface is inclined with respect to a central axis of the side wall.

Further, the motor further includes a base, the base includes a fixing portion and a heat dissipating portion disposed on the fixing portion, and the stator is fixedly disposed on the fixing portion and adjacent to the heat dissipating portion.

Further, the motor further includes a rotating shaft disposed coaxially with the rotor, the rotating shaft is inserted into the fixing portion at one end, and the other end is connected to the cover body and protrudes outside the cover body. The propeller is sleeved on one end of the rotating shaft protruding from the cover body.

Further, the heat dissipating portion includes a body disposed on the fixing portion, and the through hole is formed through the body to allow air to circulate.

Further, the heat dissipating portion further includes a heat dissipating end formed by the surface of the main body, and the heat dissipating end is at least one of a heat dissipating fin, a heat dissipating fin, and a heat dissipating cylinder.

Further, the number of the heat dissipating portions is plural, and the plurality of heat dissipating portions are spaced apart from each other on the outer peripheral wall of the fixing portion and extend in a direction away from the fixing portion.

Further, the pedestal further includes a mounting portion connected to one end of the plurality of heat dissipating portions away from the fixing portion, and each of the two adjacent heat dissipating portions and the corresponding mounting portion A vent hole for allowing air to flow is formed therebetween, and a plurality of the vent holes formed by the plurality of heat radiating portions and the mounting portion communicate with a space inside the rotor.

Further, the mounting portion is provided with a plurality of air suction holes, and each of the air suction holes communicates with the air vent holes to communicate with the space inside the rotor through the vent holes.

Further, the base further includes a cushion, and the mounting portion is provided with a plurality of mounting slots, and the cushion is installed in the mounting slot.

Further, the propeller includes a first mounting member and two blades, the first mounting member is coupled to the cover body, and the two blades are rotatably coupled to the first mounting member. The opposite ends; the blades are selectively detachable from each other and fixed to the first mounting member, or can be selectively adjacent to each other and fixed to the first mounting member.

Further, the propeller further includes a pivoting member, the pivoting member is disposed through the first mounting member and the blade to rotatably connect the blade to the first mounting member .

Further, the propeller further includes a second mounting member, the second mounting member is disposed on a side of the blade facing away from the first mounting member, and the pivoting member is disposed through the second mounting member And the paddle is coupled to the first mounting member.

Further, the pivoting member is a screw.

Further, at least one of the first mounting member and the second mounting member is provided with a weight reducing portion to reduce the relative weight of the propeller.

Further, the weight reducing portion is at least one of a through hole structure, a blind hole structure, or a groove structure.

Further, the cover body is provided with a positioning hole, and the positioning member is provided with a positioning member corresponding to the positioning hole, and the positioning member is inserted into the corresponding positioning hole to fix the propeller Positioned on the cover.

An aircraft includes an aircraft body, a motor disposed on the aircraft body, and a propeller disposed on the motor. The motor includes: a stator coupled to the aircraft body; a rotor rotatably disposed outside the stator; and a cover disposed on the rotor. The propeller is fixedly disposed on the cover body; the cover body includes a blade, and the cover body is provided with a slit. Wherein, when the motor is in operation, the rotor drives the cover to rotate, and the rotation of the blade enables air in the rotor to be discharged from the slit to take away heat generated by the motor.

Further, the cover body further includes a sidewall and a top wall, the top wall is disposed at an end of the sidewall away from the rotor, and the blade is disposed at a side of the top wall facing the rotor.

Further, the slit penetrates through at least one of the top wall and the side wall, and communicates with an inner space of the rotor.

Further, the number of the blades is plural, and the plurality of the blades are radially arranged on the top wall at intervals.

Further, each of the blades is a curved blade, and two adjacent sides of each of the blades are respectively connected to the top wall and the side wall.

Further, the cover body further includes a plurality of guiding portions connected to the side walls, the plurality of guiding portions are spaced apart from each other and are respectively received in the rotor and fixedly connected to the rotor.

Further, an end of the guiding portion away from the side wall is formed with a guiding surface, and the guiding surface is inclined with respect to a central axis of the side wall.

Further, the motor further includes a base, the base includes a fixing portion and a heat dissipating portion disposed on the fixing portion, and the stator is fixedly disposed on the fixing portion and adjacent to the heat dissipating portion.

Further, the heat dissipating portion includes a body disposed on the fixing portion, and the through hole is formed through the body to allow air to circulate.

Further, the heat dissipating portion further includes a heat dissipating end formed by the surface of the main body, and the heat dissipating end is at least one of a heat dissipating fin, a heat dissipating fin, and a heat dissipating cylinder.

Further, the motor further includes a rotating shaft disposed coaxially with the rotor, the rotating shaft is inserted into the fixing portion at one end, and the other end is connected to the cover body and protrudes outside the cover body. The propeller is sleeved on one end of the rotating shaft protruding from the cover body.

Further, the number of the heat dissipating portions is plural, and the plurality of heat dissipating portions are spaced apart from each other on the outer peripheral wall of the fixing portion and extend in a direction away from the fixing portion.

Further, the pedestal further includes a mounting portion connected to one end of the plurality of heat dissipating portions away from the fixing portion, and each of the two adjacent heat dissipating portions and the corresponding mounting portion A vent hole for allowing air to flow is formed therebetween, and a plurality of the vent holes formed by the plurality of heat radiating portions and the mounting portion communicate with a space inside the rotor.

Further, the mounting portion is provided with a plurality of air suction holes, and each of the air suction holes communicates with the air vent holes to communicate with the space inside the rotor through the vent holes.

Further, the pedestal further includes a damper, the mounting portion is provided with a plurality of mounting slots, the damper is installed in the mounting slot, and the motor is connected to the device through the mounting portion The aircraft body is in close contact with the aircraft body.

Further, the propeller includes a first mounting member and two blades, the first mounting member is coupled to the cover body, and the two blades are rotatably coupled to the first mounting member. The opposite ends; the blades are selectively detachable from each other and fixed to the first mounting member, or can be selectively adjacent to each other and fixed to the first mounting member.

Further, the propeller further includes a pivoting member, the pivoting member is disposed through the first mounting member and the blade to rotatably connect the blade to the first mounting member .

Further, the propeller further includes a second mounting member, the second mounting member is disposed on a side of the blade facing away from the first mounting member, and the pivoting member is disposed through the second mounting member And the paddle is coupled to the first mounting member.

Further, the pivoting member is a screw.

Further, at least one of the first mounting member and the second mounting member is provided with a weight reducing portion to reduce the relative weight of the propeller.

Further, the weight reducing portion is at least one of a through hole structure, a blind hole structure, or a groove structure.

Further, the cover body is provided with a positioning hole, and the positioning member is provided with a positioning member corresponding to the positioning hole, and the positioning member is inserted into the corresponding positioning hole to fix the propeller Positioned on the cover.

In the motor of the aircraft of the present invention, when the motor is running, the blades of the cover body accelerate the air flow due to the rotation, and the flowing air carries away the heat generated when the motor is operated through the slit, thereby improving the heat dissipation efficiency of the entire motor. Further, the slit formed on the cover body makes the cover body substantially a closed cover body, thereby ensuring the dustproof effect of the motor, so that impurities such as dust in the air are not easily directly entered into the motor, thereby making the motor run more. For smoothness.

DRAWINGS

1 is a perspective view of an aircraft according to an embodiment of the present invention.

2 is an exploded perspective view of the power unit of the aircraft shown in FIG. 1.

Fig. 3 is an assembled perspective view of the motor shown in Fig. 2.

Figure 4 is an exploded perspective view of the motor of Figure 2.

Figure 5 is an exploded perspective view of the motor of Figure 2 from another perspective.

Figure 6 is a perspective view of the base of the motor shown in Figure 2.

Figure 7 is a perspective view of the cover of the motor shown in Figure 2.

Figure 8 is a comparative line graph of the operating temperature variation of the motor and its electronic governor at different input powers with respect to the operating temperature of a conventional open motor at different input powers.

Main component symbol description

Motor	100
Pedestal	10
Fixed part	12
Heat sink	14
Installation department	16
Vent	161
Suction hole	163
Mounting slot	165
stator	30
Mounting parts	32
Set up department	321
Support	323
Stop	325
Coil	34
Rotor	50
Yoke	52
magnet	54
Cover	70
Top wall	72
Positioning hole	721
Side wall	74
Slit	741
Connection	743
Guide	745
Guide surface	7451
blade	76
Rotating shaft	90
propeller	200
Connection component	210
First mounting	212
Positioning member	2121
First set of holes	2123
Second mounting	214
Weight loss department	2141
Second set of holes	2143
Pivot	216
Paddle	230
Pivot	232
Blade section	234
Unmanned aerial vehicle	500
Aircraft body	510

The invention will be further illustrated by the following detailed description in conjunction with the accompanying drawings.

detailed description

Referring to Fig. 1, an unmanned aerial vehicle 500 according to an embodiment of the present invention is used for mounting an electronic device (not shown) such as a camera or a camera for photographing. The UAV 500 includes an aircraft body 510, a motor 100 disposed on the aircraft body 510, and a propeller 200 disposed on the motor 100. The motor 100 is used to drive the propeller 200 to rotate, thereby driving the UAV 500 to fly.

Referring to FIG. 2 to FIG. 4 simultaneously, the number of the motors 100 is plural, and the plurality of motors 100 are respectively disposed on the aircraft body 510. In the embodiment, the motor 100 is a brushless motor, and includes a base 10, a stator 30 fixedly disposed on the base 10, a rotor 50 rotatably coupled to the base 10, and a rotor 50 disposed on the rotor 50. The upper cover 70 and the rotating shaft 90 provided on the cover 70.

Referring to FIG. 5 and FIG. 6 , the base 10 includes a fixing portion 12 , a heat dissipation portion 14 formed on the fixing portion 12 , and a mounting portion 16 formed on the heat dissipation portion 14 .

The fixing portion 12 has a substantially cylindrical shape for mounting and fixing the stator 30.

In the present embodiment, the heat dissipating portion 14 has a rib shape, and the number thereof is plural. The plurality of heat dissipating portions 14 are formed on the outer peripheral wall of one end of the fixing portion 12, and are spaced apart from each other along the circumferential direction of the fixing portion 12, and extend substantially in a radial direction away from the fixing portion 12.

The mounting portion 16 is substantially annular, and is connected to the heat dissipating portion 14 at an end of the heat dissipating portion 14 away from the fixing portion 12 . A vent hole 161 is formed between the mounting portion 16 and each of the two adjacent heat radiating portions 14. A plurality of air suction holes 163 are formed in the mounting portion 16 , and each of the air suction holes 163 is disposed corresponding to one of the ventilation holes 161 and communicates with the corresponding ventilation hole 161 . The vent 161 and the vent 163 are used to allow air to circulate to allow the flowing air to carry away heat generated inside the motor 100 due to work. Further, the opening direction of each of the air suction holes 161 is substantially perpendicular to the opening direction of the corresponding ventilation hole 161, so that the flow direction of the air passing through the air suction holes 161 is substantially perpendicular to the air passing through the corresponding ventilation holes 161. Flow direction. The mounting portion 16 is for mounting the motor 100 as a whole in a place of use. In the present embodiment, the motor 100 is mounted on the aircraft body 510 via the mounting portion 16.

Further, the mounting portion 16 is provided with a mounting groove 165 for mounting a cushion (not shown). In the present embodiment, the number of the mounting grooves 165 is plural, and the plurality of mounting grooves 165 are spaced apart from each other at the periphery of the mounting portion 16 . Specifically, the cushion is made of a soft material such as rubber, foam, or the like. The cushion is fixedly disposed in the mounting groove 165. When the motor 100 is mounted on the aircraft body 510 through the mounting portion 16, the cushion is in close contact with the aircraft body 510 to serve The action of the vibration between the buffer motor 100 and the aircraft body 510.

Referring to FIG. 5 again, the stator 30 is disposed on the fixing portion 12 and includes a mounting member 32 and a coil 34 wound around the mounting member 32.

The mounting member 32 includes a sleeve portion 321 and a support portion 323 formed on the sleeve portion 321 . The sleeve portion 321 is substantially cylindrical and is fixedly sleeved on the fixing portion 12 and correspondingly stacked on the heat dissipating portion 14 . The number of the support portions 323 is plural, and the plurality of support portions 323 are provided on the outer peripheral wall of the sleeve portion 321 and are arranged at intervals along the circumferential direction of the sleeve portion 321 . The support portion 323 is for supporting the coil 34. The number of the coils 34 is plural, and each of the coils 34 is wound around a support portion 323.

Further, each of the supporting portions 323 is away from the end of the sleeve portion 321 to form a stopping portion 325. The size of each of the stopping portions 325 is larger than the size of the end of the corresponding supporting portion 323 to prevent the corresponding coil 34 from being detached. Support portion 323.

In some embodiments, the mounting member 32 can be made of a thermally conductive material, such as a thermally conductive plastic or a thermally conductive metal. In this case, the stop portion 325 can increase the area of heat dissipation, thereby improving heat dissipation efficiency. It can be understood that when the mounting member 32 is made of a metal material, the coil 34 is insulated from the corresponding supporting portion 323 to avoid short circuit.

The rotor 50 is disposed on the outer circumference of the mounting member 32 and includes a yoke 52 and a magnet 54 disposed on the yoke 52.

The yoke 52 has a substantially cylindrical shape and is rotatably disposed on the outer circumference of the mounting member 32. The number of the magnets 54 is plural, and the plurality of magnets 54 are fixedly disposed on the inner peripheral wall of the yoke 52 and arranged in the circumferential direction of the yoke 52. Each magnet 54 corresponds to a coil 34.

Referring to FIG. 7, the cover 70 is fixedly coupled to the yoke 52 for mounting the propeller 200. The cover 70 includes a top wall 72 and side walls 74 and a plurality of vanes 76 disposed on the top wall 72.

The top wall 72 has a substantially circular plate shape, and a plurality of positioning holes 721 are formed therethrough. A plurality of positioning holes 721 are spaced apart from each other for fixed positioning of the propeller 200 of the UAV 500.

The side wall 74 is generally cylindrical in shape and is formed around the outer edge of the top wall 72 and extends generally perpendicular to the top wall 72 and toward the yoke 52. A plurality of slits 741 are formed in the side wall 74. In the present embodiment, the slit 741 is substantially annular and extends in the circumferential direction of the side wall 74. A plurality of slits 741 are arranged along the axial direction of the side wall 74 and are spaced apart from each other. The slit 741 is used to allow air to circulate, thereby facilitating heat dissipation of the motor 100.

One end of the side wall 74 away from the top wall 72 is provided with a connecting portion 743 for connecting with the yoke 52. The connecting portion 743 is substantially annular and is disposed substantially coaxially with the side wall 74. The outer diameter of the connecting portion 743 is smaller than or equal to the inner diameter of the yoke 52, and is formed by the end surface of the side wall 74 and is housed in the yoke 52.

A plurality of guiding portions 745 are disposed on an end surface of the connecting portion 743. A plurality of guide portions 745 are formed to extend from the end faces of the side walls 74 toward the yoke 52, and the plurality of guide portions 745 are spaced apart from each other. The guide portion 745 is used to guide the direction of movement when the connecting portion 743 is inserted into the yoke 52. A guiding surface 7451 is formed at one end of each guiding portion 745 away from the connecting portion 743. The guiding surface 7451 is formed on a side of the guiding portion facing away from the central axis of the connecting portion 743, and is inclined with respect to a central axis of the connecting portion 743, so that the The cover 70 can be coaxially aligned with the yoke 52 through the guide portion 745.

In the present embodiment, each guiding portion 745 is fixed between two adjacent magnets 54. The guiding portion 745 and the side wall of the magnet 54 are fixed together by adhesive bonding. Therefore, the cover 70 is fixedly disposed on the yoke 52. It can be understood that the connection between the cover 70 and the yoke 52 can be a connection other than glue bonding, such as a welded connection, an interference fit connection, a connection by a fastener, or the like.

A plurality of the vanes 76 are disposed on a side of the top wall 72 facing the yoke 52. In the present embodiment, the blade 76 is a centrifugal fan blade. A plurality of vanes 76 are spaced apart from one another on the top wall 72 and are generally radially arranged. Each of the vanes 76 is generally curved in the shape of a vane, and the adjacent two sides are connected to the top wall 72 and the side wall 74, respectively. The side of each of the vanes 76 that meets the side wall 74 intersects the plurality of slits 741 to form a grid-like structure with the plurality of slits 741. When the rotor 50 drives the cover 70 to rotate relative to the stator 30, the blades 76 simultaneously perform a rotational motion to accelerate the air flow velocity around the blades to improve the heat dissipation efficiency of the motor 100.

Referring to FIG. 2 to FIG. 4 again, the rotating shaft 90 is substantially in the shape of a cylindrical rod, and one end of the rotating shaft 90 is fixedly inserted at a substantially central position of the top wall 72 of the cover 70, and the other end is rotatably inserted into the base 10. In the fixing portion 12. When the motor 100 is energized, the rotor 50 drives the cover 70 and the rotating shaft 90 to rotate relative to the stator 30 and the base 10. Further, the end of the rotating shaft 90 protrudes from the surface of the top wall 72 of the cover body 70 for mounting the propeller 200 and driving the propeller 200 to rotate. It can be understood that the rotating shaft 90 can be not limited to the above-mentioned arrangement. For example, one end of the rotating shaft 90 can be fixedly inserted into the fixing portion 12 of the base 10, and the other end can be rotatably inserted into the top wall 72 of the cover 70. In the above, the rotor 50, the cover 70, and the propeller 200 can be rotated about the axis of the rotating shaft 90 with respect to the stator 30 and the base 10.

Referring to FIG. 1 and FIG. 2 again, in the embodiment, the number of the propellers 200 is multiple, and each of the propellers 200 is mounted on one of the motors 100 to jointly form a power device. The unmanned aerial vehicle 500 provides the power of flight. Each of the propellers 200 includes a connection assembly 210 and a paddle 230 disposed on the connection assembly 210.

The connecting component 210 is mounted on the cover 70 of the motor 100. The connecting component 210 includes a first mounting member 212, a second mounting member 214 disposed adjacent to the first mounting member 212, and a first mounting member. 212 and a pivoting member 216 on the second mounting member 214.

The first mounting member 212 is disposed on the top wall 72 of the cover 70. In the present embodiment, the first mounting member 212 is substantially in the form of a sheet, and a positioning member 2121 is disposed on one side thereof. The positioning member 2121 is for positioning the propeller 200 on the motor 100. In the present embodiment, the positioning member 2121 is substantially columnar and has a plurality of numbers. The plurality of positioning members 2121 are spaced apart from each other and formed by the surface of the first mounting member 212. The positioning member 2121 is for positioning the propeller 200 on the motor 100. Specifically, the positioning member 2121 is disposed corresponding to the positioning hole 721 of the cover body 70 and is inserted into the corresponding positioning hole 721.

A first sleeve hole 2123 is defined in a substantially central portion of the first mounting member 212. The first mounting member 212 is sleeved on the first end of the rotating shaft 90 to protrude from the end of the cover body 70. The positioning member 2121 is inserted into the corresponding positioning hole 721 to integrally position and mount the propeller 200 on the motor 100.

The second mounting member 214 is substantially parallel to the first mounting member 212 and spaced apart from the rotating shaft 90 for fixing the paddle 230 with the first mounting member 212 and the pivoting member 216. The structure of the second mounting member 214 is substantially the same as that of the first mounting member 212. It is also a sheet-like structure and is provided with a second sleeve hole 2143. The second set of holes 2143 is disposed substantially coaxially with the first set of holes 2123. The second mounting member 214 is sleeved on the end of the rotating shaft 90 through the second sleeve hole 2143 and located on a side of the first mounting member 212 facing away from the positioning member 2121.

The number of the pivoting members 216 is two, and the two pivoting members 216 are respectively disposed at opposite ends of the second mounting member 214. The pivoting member 216 is used to mount the blade 230 on the connecting component 210. In this embodiment, the pivoting member 216 is a screw. Each of the pivoting members 216 is disposed on the second mounting member 214 and screwed onto the first mounting member 212 .

The number of the blades 230 is two, and the two blades 230 are respectively rotatably disposed at opposite ends of the connecting component 210, and are connected to the first mounting member 212 and the second mounting member through the pivoting member 216. 214. Each of the blades 230 includes a pivoting portion 232 and a blade portion 234 disposed on the pivoting portion 232.

Each of the pivoting portions 232 is disposed at one end of the connecting component 210 and located between the first mounting member 212 and the second mounting member 214 . The pivoting member 216 is inserted into the second mounting member 214 and the pivoting portion 232, and is screwed onto the first mounting member 212 to rotatably mount the blade 230 to the first mounting member 212 and the second mounting member 212. Two mounting members 214.

The blade portion 234 is formed on one side of the pivot portion 232 and extends in a direction away from the connection assembly 210. There is a certain frictional resistance between the pivoting portion 232 and the first mounting member 212 and between the pivoting portion 232 and the second mounting member 214. The frictional resistance keeps the relative position between the blade 230 and the connection assembly 210 constant without applying an external force; even when the external force applied to the blade 230 is small, the external force cannot make the blade 230 The opposite connection assembly 210 rotates; when the external force applied to the blade 230 reaches a predetermined value, the blade 230 rotates relative to the connection assembly 210. In the present embodiment, when the motor 100 is in operation, the connection assembly 210 and the blade 230 are rotated, and the connection assembly 210 and the blade 230 are both subjected to centrifugal force. When the rotational speed of the motor 100 rises and reaches a predetermined value, the centrifugal force of the blade portion 234 of the blade 230 is increased, and the two blade portions 234 are rotated relative to the connecting assembly 210 under the centrifugal force until two The blade portions 234 are deployed away from each other and are generally in a straight line, and the propeller 200 continues to rotate to a stable equilibrium state, thereby driving the UAV 500 to fly. When the propeller 200 is not required, the two blade portions 234 are rotated by an external force to rotate the two blade portions 234 relative to the connecting assembly 210 and close to each other, so that the two blades 230 can be adjacent to each other and fixedly mounted to the first The mounting member 212 and the second mounting member 214 are disposed to relatively reduce the space occupied by the propeller 200 and the UAV 500 during storage.

When the motor 100 of the present embodiment is assembled, first, the coil 34 is wound around the mounting member 32, and the mounting member 32 is fixedly disposed on the fixing portion 12. Then, the magnet 54 is mounted on the yoke 52, the yoke 52 is fixedly coupled to the cover 70, and one end of the rotating shaft 90 is inserted into the top wall 72 of the cover 70. Finally, one end of the rotating shaft 90 away from the cover body 70 is rotatably inserted into the fixing portion 12, and the yoke 52 is rotatably provided on the outer circumference of the stator 30. At this time, the air suction hole 163 on the base 10 communicates with the cavity (not shown) inside the yoke 52 through the vent hole 161, and the slit 741 on the cover body 70 also passes through the inner cavity of the side wall 74 (Fig. Not shown) is in communication with the cavity inside the yoke 52, so that an air flow passage (not shown) is formed between the cover 70, the yoke 52 and the base 10 to allow air to circulate and take the motor 100 to work. The heat generated.

When the motor 100 is in operation, the cover 70 and the rotor 50 rotate relative to the stator 30 and the base 10, and the blades 76 of the cover 70 disturb the surrounding air due to the rotation, accelerating the flow of the surrounding air, and the airflow passes through the air suction holes 163 and The vent hole 161 enters the inside of the yoke 52 and is discharged through the slit 741, thereby taking away heat generated when the motor 100 operates.

Further, the motor 100 is required to be equipped with an electronic governor (not shown) to allow the electronic governor to control the operating speed of the motor 100. The electronic governor is fixed on the base 10, and the motor 100 performs heat dissipation while dissipating heat to the electronic governor. After experimentally collecting data, the operating temperature variation of the motor 100 and its electronic governor of the present invention is shown in relation to the operating temperature variation of the conventional open motor as shown in FIG. 8 of the specification.

Please refer to FIG. 8 at the same time. FIG. 8 records the difference between the operating temperature of the motor 100 and the electronic speed regulating device of the present invention at different input powers with respect to the ambient temperature (referred to as the relative ambient temperature rise), and records the traditional open type. The difference between the operating temperature of the motor and its electronic speed control device at different input powers relative to the ambient temperature (referred to as the relative ambient temperature rise).

By comparing the relative environmental temperature rise data of the two groups, it can be intuitively obtained that the same part of the motor or its electronic governor is temperature-measured in the case of equal input power, the motor 100 of the present invention and its electronic governor The relative ambient temperature rise value is significantly lower than the relative temperature rise of the electronic governor of the traditional open motor. Therefore, it can be seen that the heat dissipation effect of the motor 100 of the present invention is better than that of the conventional open type motor.

At the same time, when the input power is relatively large, the difference between the relative temperature rise of the motor 100 and its electronic governor of the present invention and the relative ambient temperature rise value of the conventional open motor is also relatively large. It can be seen that the heat dissipation efficiency of the motor 100 of the present invention is higher than that of the conventional open type motor.

When it is required to apply the motor 100 of the present embodiment to the unmanned aerial vehicle 500, the motor 100 is fixedly disposed on the aircraft body 510 through the mounting portion 16 of the base 10, and then the first of the propellers 200 is The mounting member 212 and the second mounting member 214 are sleeved on one end of the rotating shaft 90 protruding from the cover body 70, and the positioning member 2121 on the first mounting member 212 is inserted into the corresponding positioning hole 721. Finally, the connecting assembly 210 of the propeller 200 is fixed to the cover 70, and the blade 230 is mounted on the connecting assembly 210.

The motor 100 of the unmanned aerial vehicle 500 of the present invention has a suction hole 163 and a vent hole 161 provided in the base 10 thereof, and a side wall 74 of the cover 70 is provided with a slit 741 for the cover body 70 and the yoke 52. An air flow passage is formed between the base 10. When the motor 100 is in operation, the blades 76 of the cover 70 accelerate the air flow by the rotation, and the flowing air carries away the heat generated when the motor 100 operates through the air flow passage, thereby improving the heat dissipation efficiency of the motor 100 as a whole. Further, the heat dissipating portion 14 on the susceptor 10 is a ribbed structure. When the heat generated by the motor 100 is transmitted to the susceptor 10, the heat dissipating portion 14 has a relatively large contact area with air, so that the heat can be faster. The ground radiates into the air. Moreover, the flowing air can also quickly carry away the heat conducted to the heat radiating portion 14. In addition, the top wall 72 of the cover 70 of the motor 100 is substantially plate-shaped, and only the side wall 74 defines a slit 741 for allowing air to flow, so that the cover 70 is substantially a closed cover, which ensures the motor 100. The dustproof effect makes it difficult for impurities such as dust in the air to directly enter the inside of the motor 100, thereby making the motor 100 run more smoothly. The grid-like structure in which the plurality of blades 76 are in contact with the side wall 74 and the plurality of slits 741 further improves the dustproof effect of the motor 100 without affecting the air flow and heat dissipation.

Further, the blade 230 of the propeller 200 of the inventive UAV 500 is rotatably disposed on the connection assembly 210, and when the propeller 200 is required to be used, the centrifugal force generated by the rotation of the two blades 230 at the motor 100 Expand below. When the propeller 200 is not required to be used, the two blades 230 can be relatively closed, so that the two blades 230 can be adjacent to each other and fixedly mounted on the connecting assembly 210, thereby relatively reducing the occupation of the propeller 200 during storage. space.

It can be understood that the slit 741 on the side wall 74 can also be opened on the top wall 72 of the cover 70, or a plurality of slits 741 can be respectively opened on the top wall 72 and the side wall 74. Therefore, the grid-like structure composed of the side of each blade 76 that is in contact with the side wall 74 or the top wall 72 and the plurality of slits 741 can ensure the dustproof effect of the motor 100 without affecting the heat dissipation of the air.

It can be understood that the shape of the slit 741 is not limited to the above-described annular structure, and it may be designed as a porous structure, a rectangular structure, a grid structure or other irregular pattern structure or the like to allow the cover body 70 to be dust-proof. At the same time, it does not affect the air circulation and heat dissipation.

It can be understood that the heat dissipation portion 14 of the susceptor 10 is not limited to the radial rib heat dissipation structure described above, and it can be designed as another heat dissipation structure. For example, the heat dissipating portion 14 may include a substantially plate-shaped body and a heat dissipating end protrudingly formed on the body, the body being disposed at one end of the fixing portion 12, and the mounting portion 16 being formed at a periphery of the body. Further, the body may be provided with a plurality of through holes for allowing air to circulate, so that the air suction holes 163 of the base 10 can communicate with the inner space of the rotor 50 through the plurality of through holes. Further, the heat dissipation end may be a heat dissipation fin formed by the surface of the body, a heat dissipation blade, a heat dissipation cylinder or the like, to increase the contact area between the heat dissipation portion of the base 10 and the air. Further improve heat dissipation efficiency.

It can be understood that the second mounting member 214 of the propeller 200 can be omitted, and the blade 230 is rotatably connected to the first mounting member 212 through the pivoting member 216, respectively, and the first mounting member 212 is fixedly disposed on the cover body. 70 on.

It can be understood that in order to avoid the weight of the propeller 200 itself being too heavy, a part of the material can be removed from the member to open the weight reducing portion 2141 (see Fig. 1). For example, the weight reducing portion 2141 may be opened on the second mounting member 214 or may be opened on the first mounting member 212. It can be understood that the weight reducing portion 2141 can be in the form of a through hole, a blind hole or a groove.

It can be understood that the blade 230 of the propeller 200 can also be integrally formed with the connecting component 210. The paddle 230 is directly fixed to the rotating shaft 90, and is not limited to the embodiment.

In addition, those skilled in the art can make other changes in the spirit of the present invention. Of course, the changes made in accordance with the spirit of the present invention should be included in the scope of the present invention.

Claims (59)

1.  A motor comprising:

   stator;

   a rotor rotatably disposed outside the stator;

   a cover body disposed on the rotor, the cover body includes a blade, and the cover body is provided with a slit;

   Wherein, when the motor is in operation, the rotor drives the cover to rotate, and the rotation of the blade enables air in the rotor to be discharged from the slit to take away heat generated by the motor.
2.  The motor according to claim 1, wherein said cover further comprises a side wall and a top wall, said top wall being disposed at an end of said side wall away from said rotor, said blade being disposed at said top The wall faces one side of the rotor.
3.  The motor according to claim 2, wherein said slit penetrates at least one of said top wall and said side wall and communicates with an inner space of said rotor.
4.  The motor according to claim 2, wherein said plurality of blades are plural, and said plurality of said blades are radially arranged on said top wall at intervals from each other.
5.  The motor according to claim 4, wherein each of said blades is a curved blade, and adjacent two sides of each of said blades are coupled to said top wall and said side wall, respectively on.
6.  The motor according to claim 2, wherein the cover further comprises a plurality of guiding portions connected to the side wall, the plurality of guiding portions are spaced apart from each other and are each received in the rotor. And fixedly connected to the rotor.
7.  The motor according to claim 6, wherein one end of said guide portion away from said side wall is formed with a guide surface which is inclined with respect to a central axis of said side wall.
8.  The motor according to claim 1, wherein the motor further comprises a base, the base includes a fixing portion and a heat dissipating portion disposed on the fixing portion, and the stator is fixedly disposed on the fixing portion And adjacent to the heat dissipation portion.
9.  The motor according to claim 8, wherein said motor further comprises a rotating shaft coaxially disposed with said rotor, said rotating shaft being inserted into said fixing portion at one end and connected to said cover at the other end .
10.  The motor according to claim 8, wherein the number of the heat dissipating portions is plural, and the plurality of heat dissipating portions are spaced apart from each other on the outer peripheral wall of the fixing portion and away from the fixing portion The direction extends.
11.  The motor according to claim 10, wherein the base further comprises a mounting portion connected to one end of the plurality of heat dissipating portions away from the fixing portion, each of the two adjacent ones a vent hole for allowing air to flow between the heat dissipating portion and the corresponding mounting portion, and a plurality of the vent holes formed by the plurality of heat dissipating portions and the mounting portion are connected to a space inside the rotor .
12.  The motor according to claim 11, wherein said mounting portion is provided with a plurality of suction holes, each of said suction holes being in communication with said vent hole, thereby passing said vent hole and said vent hole The space inside the rotor is connected.
13.  The motor according to claim 11, wherein the base further comprises a cushion, and the mounting portion is provided with a plurality of mounting grooves, and the cushion is installed in the mounting groove.
14.  The motor according to claim 8, wherein said heat dissipating portion comprises a body disposed on said fixing portion, and said body is provided with a through hole for allowing air to flow therethrough.
15.  The motor of claim 14, wherein the heat dissipating portion further comprises a heat dissipating end formed by the surface of the main body, wherein the heat dissipating end is at least one of a heat dissipating fin, a heat dissipating fin, and a heat dissipating cylinder. Kind.
16.  A power unit includes a motor and a propeller, wherein the motor comprises:

    stator;

    a rotor rotatably disposed outside the stator;

    a cover body disposed on the rotor, the propeller is fixedly disposed on the cover body; the cover body comprises a blade, and the cover body is provided with a slit;

    Wherein, when the motor is in operation, the rotor drives the cover to rotate, and the rotation of the blade enables air in the rotor to be discharged from the slit to take away heat generated by the motor.
17.  A power unit according to claim 16, wherein said cover body further comprises a side wall and a top wall, said top wall being disposed at an end of said side wall away from said rotor, said blade being disposed at said The top wall faces one side of the rotor.
18.  The power unit according to claim 17, wherein said slit penetrates at least one of said top wall and said side wall and communicates with an inner space of said rotor.
19.  A power unit according to claim 17, wherein said plurality of blades are plural, and said plurality of said blades are radially arranged on said top wall at intervals from each other.
20.  A power unit according to claim 19, wherein each of said blades is a curved blade, and adjacent two sides of said blade are coupled to said top wall and said side, respectively On the wall.
21.  A power unit according to claim 17, wherein said cover body further comprises a plurality of guiding portions connected to said side walls, said plurality of guiding portions being spaced apart from each other and housed in said rotor And fixedly connected to the rotor.
22.  A power unit according to claim 21, wherein one end of said guide portion away from said side wall is formed with a guide surface which is inclined with respect to a central axis of said side wall.
23.  The power unit according to claim 16, wherein the motor further includes a base, the base includes a fixing portion and a heat dissipating portion disposed on the fixing portion, and the stator is fixedly disposed on the The heat dissipating portion is adjacent to the fixing portion.
24.  A power unit according to claim 23, wherein said motor further comprises a rotating shaft coaxially disposed with said rotor, said rotating shaft having one end inserted in said fixing portion and the other end connected to said cover And protruding from the outside of the cover, the propeller is sleeved on an end of the rotating shaft protruding from the cover.
25.  The power unit according to claim 23, wherein the heat dissipating portion comprises a body disposed on the fixing portion, and the body is provided with a through hole for allowing air to flow therethrough.
26.  The power unit according to claim 25, wherein the heat dissipating portion further comprises a heat dissipating end formed by the surface of the body, the heat dissipating end being at least one of a heat dissipating fin, a heat dissipating fin, and a heat dissipating cylinder One.
27.  The power unit according to claim 23, wherein the number of the heat dissipating portions is plural, and the plurality of heat dissipating portions are spaced apart from each other on the outer peripheral wall of the fixing portion, and are spaced apart from the fixing portion. The direction of the department extends.
28.  The power unit according to claim 27, wherein the base further comprises a mounting portion, the mounting portion being connected to one end of the plurality of heat dissipating portions away from the fixing portion, each adjacent two a vent hole for allowing air to flow between the heat dissipating portion and the corresponding mounting portion, and a plurality of the vent holes formed by the plurality of heat dissipating portions and the mounting portion are connected to a space inside the rotor through.
29.  A power unit according to claim 28, wherein said mounting portion is provided with a plurality of air suction holes, each of said air suction holes being in communication with said air vent holes, thereby passing through said vent holes The spaces inside the rotor are connected to each other.
30.  The power unit according to claim 28, wherein the base further comprises a cushion, and the mounting portion is provided with a plurality of mounting slots, and the cushion is installed in the mounting slot.
31.  A power unit according to claim 16, wherein said propeller includes a first mounting member and two blades, said first mounting member being coupled to said cover body, and said two said blades are rotatable Connected to opposite ends of the first mounting member; the blades can be selectively offset from each other and fixed to the first mounting member, or can be selectively adjacent to each other and fixed to the first On the mounting piece.
32.  A power unit according to claim 31, wherein said propeller further comprises a pivoting member, said pivoting member being disposed through said first mounting member and said blade to allow said blade to be Rotatingly coupled to the first mounting member.
33.  A power unit according to claim 32, wherein said propeller further includes a second mounting member, said second mounting member being disposed on a side of said blade facing away from said first mounting member, said pivot A connector is disposed through the second mounting member and the blade and coupled to the first mounting member.
34.  A power unit according to claim 32, wherein said pivoting member is a screw.
35.  A power unit according to claim 32, wherein at least one of said first mounting member and said second mounting member is provided with a weight reducing portion to reduce the relative weight of said propeller.
36.  A power unit according to claim 35, wherein said weight reducing portion is at least one of a through hole structure, a blind hole structure, and a groove structure.
37.  The power device according to claim 31, wherein the cover body is provided with a positioning hole, and the positioning member is provided with a positioning member corresponding to the positioning hole, and the positioning member is inserted in the corresponding The positioning hole is configured to position the propeller on the cover.
38.  An aircraft comprising an aircraft body, a motor disposed on the aircraft body, and a propeller disposed on the motor, wherein the motor comprises:

    a stator coupled to the aircraft body;

    a rotor rotatably disposed outside the stator;

    a cover body disposed on the rotor, the propeller is fixedly disposed on the cover body; the cover body comprises a blade, and the cover body is provided with a slit;

    Wherein, when the motor is in operation, the rotor drives the cover to rotate, and the rotation of the blade enables air in the rotor to be discharged from the slit to take away heat generated by the motor.
39.  The aircraft according to claim 38, wherein said cover further comprises a side wall and a top wall, said top wall being disposed at an end of said side wall away from said rotor, said blade being disposed on said top The wall faces one side of the rotor.
40.  The aircraft according to claim 39, wherein said slit penetrates at least one of said top wall and said side wall and communicates with an inner space of said rotor.
41.  The aircraft according to claim 39, wherein said plurality of blades are plural, and said plurality of said blades are radially arranged on said top wall at intervals from each other.
42.  The aircraft according to claim 41, wherein each of said blades is a curved blade, and adjacent two sides of each of said blades are coupled to said top wall and said side wall, respectively on.
43.  The aircraft according to claim 39, wherein the cover further comprises a plurality of guiding portions connected to the side walls, the plurality of guiding portions are spaced apart from each other and are each received in the rotor. And fixedly connected to the rotor.
44.  The aircraft according to claim 43, wherein one end of said guide portion away from said side wall is formed with a guide surface which is inclined with respect to a central axis of said side wall.
45.  The aircraft according to claim 38, wherein the motor further comprises a base, the base comprising a fixing portion and a heat dissipating portion disposed on the fixing portion, the stator being fixedly disposed on the fixing portion And adjacent to the heat dissipation portion.
46.  The aircraft according to claim 45, wherein said heat dissipating portion comprises a body disposed on said fixing portion, and said body is provided with a through hole for allowing air to flow therethrough.
47.  The aircraft of claim 46, wherein the heat dissipating portion further comprises a heat dissipating end formed by the surface of the body, the heat dissipating end being at least one of a heat dissipating fin, a heat dissipating fin, and a heat dissipating cylinder Kind.
48.  The aircraft according to claim 45, wherein said motor further comprises a rotating shaft coaxially disposed with said rotor, said rotating shaft being inserted into said fixing portion at one end and connected to said cover at the other end And protruding from the outside of the cover, the propeller is sleeved on one end of the rotating shaft protruding from the cover.
49.  The aircraft according to claim 45, wherein the number of the heat dissipating portions is plural, and the plurality of heat dissipating portions are spaced apart from each other on the outer peripheral wall of the fixing portion, and away from the fixing portion The direction extends.
50.  The aircraft according to claim 49, wherein said base further comprises a mounting portion, said mounting portion being coupled to one end of said plurality of heat dissipating portions away from said fixing portion, each adjacent said two a vent hole for allowing air to flow between the heat dissipating portion and the corresponding mounting portion, and a plurality of the vent holes formed by the plurality of heat dissipating portions and the mounting portion are connected to a space inside the rotor .
51.  The aircraft according to claim 50, wherein said mounting portion is provided with a plurality of suction holes, each of said suction holes being in communication with said vent hole, thereby passing said vent hole and said vent hole The space inside the rotor is connected.
52.  The aircraft according to claim 50, wherein the base further comprises a cushion, the mounting portion is provided with a plurality of mounting slots, and the cushion is mounted in the mounting slot. The motor is coupled to the aircraft body through the mounting portion such that the cushion is in close contact with the aircraft body.
53.  The aircraft according to claim 38, wherein said propeller includes a first mounting member and two blades, said first mounting member being coupled to said cover body, said two said blades being rotatably Connecting to opposite ends of the first mounting member; the blades are selectively detachable from each other and fixed to the first mounting member, or are selectively adjacent to each other and fixed to the first mounting On the piece.
54.  The aircraft according to claim 53, wherein said propeller further comprises a pivoting member, said pivoting member being disposed through said first mounting member and said blade to rotate said blade Groundly connected to the first mounting member.
55.  The aircraft according to claim 54, wherein said propeller further comprises a second mounting member, said second mounting member being disposed on a side of said blade facing away from said first mounting member, said pivoting The piece is disposed on the second mounting member and the blade and connected to the first mounting member.
56.  The aircraft of claim 54 wherein said pivoting member is a screw.
57.  The aircraft according to claim 54, wherein at least one of said first mounting member and said second mounting member is provided with a weight reducing portion to reduce the relative weight of said propeller.
58.  The aircraft according to claim 57, wherein said weight reducing portion is at least one of a through hole structure, a blind hole structure, or a groove structure.
59.  The aircraft according to claim 53, wherein the cover body is provided with a positioning hole, and the positioning member is provided with a positioning member on the first mounting member, and the positioning member is inserted in the corresponding position. Positioning the hole to position the propeller on the cover.

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