Air cooling heat dissipation power system assembly for electric aircraft

Abstract

The utility model discloses an air cooling heat dissipation power system assembly for an electric aircraft. An air cooling heat dissipation power system assembly for an electric aircraft comprises a motor and a controller. The motor comprises a stator and a rotor; the stator comprises a stator shaft and a stator frame, and a stator coil is mounted on the stator frame; the rotor comprises a front cover which is rotatably installed on the stator shaft, a rotating shell is installed on one side of the front cover, and magnetic steel is installed in the rotating shell. According to the air-cooling heat dissipation power system assembly for the electric aircraft, by arranging the controller installed at the tail of the motor, the overall installation structure of the motor and the controller is more compact, the occupied space is saved, internal space design of the unmanned aerial vehicle is facilitated, when the motor rotates, the first fins rotate along with the motor, and the heat dissipation efficiency is improved. According to the utility model, the rotating air flow can be formed behind the motor to dissipate heat of the controller behind the motor, and ventilation and heat dissipation can be carried out on the interior of the motor through the air inlet holes, so that the heat dissipation effect is better.

Description

Technical Field

[0001] The present invention relates to the technical field of motor heat dissipation, and in particular to an air-cooled heat dissipation power system assembly for an electric aircraft. Background Art

[0002] Unmanned aerial vehicles, or UAVs for short, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are operated completely or intermittently autonomously by onboard computers. Compared with manned aircraft, drones are often more suitable for tasks that are too "dull, dirty or dangerous". Drones can be divided into military and civilian applications according to their application areas. In the military, drones are divided into reconnaissance aircraft and target aircraft. In the civilian sector, drones + industry applications are the real rigid demand for drones; their applications in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, creating romance, etc. have greatly expanded the use of drones themselves, and developed countries are also actively expanding industry applications and developing drone technology.

[0003] Most existing drones are powered by electric motors, i.e. electric drones. The onboard controller controls the start and stop of the motor and the speed, thereby controlling the take-off and landing and flight speed of the drone. The traditional onboard controller is installed separately from the motor. The onboard controller generally uses a method of increasing the heat dissipation area for passive heat dissipation, which has a poor heat dissipation effect. The motor and the onboard controller are two structural components, and the installation is not compact enough, which is not conducive to the internal structure design of the electric aircraft.

[0004] Therefore, it is necessary to provide an air-cooled power system assembly for electric aircraft to solve the above technical problems. Summary of the invention

[0005] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides an air-cooled heat dissipation power system assembly for an electric aircraft, which can make the overall structure of the motor and the controller more compact and have a better heat dissipation effect.

[0006] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0007] The invention discloses an air-cooled heat dissipation power system assembly for electric aircraft, comprising: an electric motor and a controller, wherein the controller is mounted at the tail end of the electric motor; the electric motor comprises a stator and a rotor; the stator comprises a stator shaft and a stator frame mounted on the stator shaft, wherein the stator frame is fixed on the body of an unmanned aerial vehicle, and a stator coil is mounted on the stator frame; the rotor comprises a front cover rotatably mounted on the stator shaft, a rotating shell is fixedly mounted on one side of the front cover, a magnetic steel is mounted on the inner side of the rotating shell, and the magnetic steel is arranged on the outer side of the stator coil; after the stator coil is energized, the changing magnetic field generated drives the magnetic steel to rotate, thereby causing the rotating shell and the front cover to rotate with the stator shaft as the axis, so that the aircraft blade connected to the front cover can rotate; the controller comprises a shell composed of a heat dissipation shell and a rear cover, wherein a control terminal for controlling the action of the motor is arranged in the shell, and the heat dissipation shell is fixedly mounted on one side of the stator frame, so that the controller and the electric motor are compactly mounted together, which greatly saves space and is beneficial to the internal space design of the unmanned aerial vehicle; an air inlet hole is opened on the circumference of the front cover, and a plurality of positive arc-shaped first fins are evenly mounted on the rotating shell.

[0008] Preferably, a connecting tube is coaxially mounted on the stator frame, the stator coil is sleeved on the connecting tube, and inner heat dissipation fins are provided on the inner side of the connecting tube.

[0009] Preferably, an exhaust hole is provided on the stator frame.

[0010] Preferably, a plurality of reverse-arc-shaped second fins are evenly mounted on the circumference of the heat dissipation shell, and the bending and tilting directions of the first fins and the second fins are opposite.

[0011] Preferably, a plurality of ribs are evenly arranged on one side of the heat dissipation shell, and the ribs face the side of the stator frame. The ribs enhance the structural strength of the heat dissipation shell and increase the heat dissipation area of ​​the heat dissipation shell.

[0012] Preferably, a heat conducting sheet is installed in the heat dissipation shell, and the heat conducting sheet is installed in close contact with the heat dissipation shell.

[0013] Preferably, a plurality of threaded holes are formed on the connecting pipe, a plurality of positioning holes are formed on the heat dissipation shell, and the positioning holes are aligned one by one with the threaded holes.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] (1) The present invention makes the overall installation structure of the motor and the controller more compact by arranging a controller installed at the tail of the motor, saving space and facilitating the internal space design of the UAV. When the motor rotates, the first fin rotates accordingly, so that a rotating airflow can be formed behind the motor to dissipate heat for the controller at the rear, and the inside of the motor can be ventilated and cooled through the air inlet, so that the heat dissipation effect is better;

[0016] (2) The present invention provides a connecting pipe, an exhaust hole and an inner heat dissipation fin, so that the air entering the motor can be discharged from the rear, which is beneficial to the heat dissipation of the stator coil;

[0017] (3) The present invention can improve the heat dissipation speed of the controller by evenly installing the second fins on the heat dissipation shell, thereby greatly improving the heat dissipation performance of the controller;

[0018] (4) The present invention can enhance the structural strength of the heat dissipation shell and increase the heat dissipation area of ​​the heat dissipation shell by installing fins on one side of the heat dissipation shell, thereby accelerating the heat dissipation speed of the controller;

[0019] (5) The present invention can facilitate heat conduction of components inside the controller and accelerate the heat dissipation of the controller by installing a heat conductive sheet inside the heat dissipation shell;

[0020] (6) The present invention can facilitate the connection between the heat dissipation shell and the stator frame by setting positioning holes and threaded holes, thereby facilitating the connection between the controller and the motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of the structure of the air-cooling power system assembly for an electric aircraft provided by the present invention;

[0022] Figure 2 for Figure 1 The structural schematic diagram of the stator frame, front cover and rotating shell in the air-cooled heat dissipation power system assembly for the electric aircraft shown;

[0023] Figure 3 for Figure 1 The structural schematic diagram of the stator frame in the air-cooled power system assembly for the electric aircraft shown;

[0024] Figure 4 for Figure 1 The schematic diagram of the structure of the heat sink shell in the air-cooled heat dissipation power system assembly for the electric aircraft shown;

[0025] Figure 5 for Figure 1 The schematic diagram of the structure of the heat sink shell in the air-cooled power system assembly for the electric aircraft is shown.

[0026] Among them, the names corresponding to the figure marks are: 1-stator shaft, 2-stator frame, 3-stator coil, 4-front cover, 5-rotating shell, 6-magnetic steel, 7-heat dissipation shell, 8-rear cover, 9-air inlet, 10-first fin, 11-connecting pipe, 12-exhaust hole, 13-second fin, 14-inner heat dissipation fin, 15-heat conducting plate, 16-control end, 17-positioning hole, 18-threaded hole, 19-rib. DETAILED DESCRIPTION

[0027] The present invention is further described below in conjunction with the accompanying drawings and embodiments. The embodiments of the present invention include but are not limited to the following embodiments.

[0028] Embodiment 1:

[0029] like Figure 1-5 As shown, the air-cooled heat dissipation power system assembly for electric aircraft provided by the present invention includes: an electric motor and a controller, the controller is installed at the tail end of the electric motor; the electric motor includes a stator and a rotor; the stator includes a stator shaft 1 and a stator frame 2 installed on the stator shaft 1, the stator frame 2 is fixed on the drone body, and a stator coil 3 is installed on the stator frame 2; the rotor includes a front cover 4 rotatably installed on the stator shaft 1, a rotating shell 5 is fixedly installed on one side of the front cover 4, a magnetic steel 6 is installed on the inner side of the rotating shell 5, and the magnetic steel 6 is arranged on the outer side of the stator coil 3. After the stator coil 3 is energized, the changing magnetic field generated drives the magnetic steel 6 to rotate, thereby causing the rotating shell 5 to rotate together with the front cover 4 with the stator shaft as the axis, and the aircraft blade connected to the front cover 4 can rotate; the controller includes a shell composed of a heat dissipation shell 7 and a rear cover 8, and a control terminal 16 (control terminal 16) for controlling the action of the motor is provided in the shell. Boards and other electronic components), specifically, the heat dissipation shell 7 is fixedly installed on one side of the stator frame 2, so that the controller and the motor are compactly installed together, which greatly saves space and is beneficial to the internal space design of the drone. For example, the space share of the battery inside the drone is increased, which is beneficial to improving the endurance of the drone; an air inlet hole 9 is opened on the circumference of the front cover 4, and a plurality of first fins 10 in a positive arc shape are evenly installed on the rotating shell 5. When the motor rotates, the first fins 10 rotate accordingly, thereby playing the role of a centrifugal fan, accelerating the flow rate of the external airflow introduced into the interior of the motor through the air inlet hole 9, thereby improving the heat dissipation speed of the motor. In addition, when the motor rotates in a counterclockwise direction, the first fins 10 rotate synchronously with the motor, forming a rotating airflow behind the motor to dissipate heat to the controller behind. Compared with passive heat dissipation, this heat dissipation method has a better effect on the controller.

[0030] By installing the controller at the tail of the motor, the overall installation structure of the motor and the controller is made more compact, which saves space and facilitates the internal space design of the drone. When the motor rotates, the first fin 10 rotates accordingly, so that a rotating airflow can be formed behind the motor to dissipate the heat of the controller at the rear, and the inside of the motor can be ventilated and cooled through the air inlet 9, resulting in a better heat dissipation effect.

[0031] Embodiment 2:

[0032] like Figure 3As shown, a connecting pipe 11 is coaxially installed on the stator frame 2, and the stator coil 3 is sleeved on the connecting pipe 11. An inner heat dissipation fin 14 is provided on the inner side of the connecting pipe 11, and an exhaust hole 12 is opened on the stator frame 2. When in use, one end of the stator shaft 1 is connected to the mounting hole in the middle of the stator frame 2. The airflow entering the motor from the air inlet hole 9 dissipates the heat of the stator coil 3 and is discharged through the exhaust hole 12. The discharged airflow blows toward the heat dissipation shell 7 to dissipate the heat of the controller, and the inner heat dissipation fin 14 increases the heat dissipation area of ​​the connecting pipe 11, which is beneficial to improving the heat dissipation speed of the stator coil 3 installed on the connecting pipe 11.

[0033] By providing the connecting pipe 11 , the exhaust hole 12 and the inner heat dissipation fins 14 , the air entering the interior of the motor can be discharged from the rear, which is beneficial to the heat dissipation of the stator coil 3 .

[0034] Embodiment 3:

[0035] like Figure 1 and Figure 4-5 As shown, a plurality of reverse arc-shaped second fins 13 are evenly installed on the circumference of the heat dissipation shell 7, and the bending and tilting directions of the first fins 10 and the second fins 13 are opposite. When in use, on the one hand, the second fins 13 are utilized to increase the heat dissipation area of ​​the heat dissipation shell 7, thereby improving the heat dissipation speed of the controller. On the other hand, the airflow generated by the rotation of the first fins 10 blows toward the second fins 13, and the second fins 13 compress and rectify the airflow. The principle is similar to that of a turbine, which speeds up the air flowing through the second fins 13, thereby improving the heat dissipation speed of the second fins 13, and thereby improving the heat dissipation speed of the controller.

[0036] By evenly installing the second fins 13 on the heat dissipation shell 7, the heat dissipation speed of the controller can be increased, and the heat dissipation performance of the controller is greatly improved.

[0037] Embodiment 4:

[0038] like Figure 4 As shown, a plurality of ribs 19 are evenly arranged on one side of the heat dissipation shell 7, and the ribs 19 face the side of the stator frame 2. The ribs 19 enhance the structural strength of the heat dissipation shell 7 and increase the heat dissipation area of ​​the heat dissipation shell 7. The air discharged from the exhaust hole 12 blows toward the ribs 19 and is distributed to all sides to dissipate the heat of the heat dissipation shell 7, thereby accelerating the heat dissipation speed of the heat dissipation shell 7 and further accelerating the heat dissipation speed of the controller.

[0039] By installing the rib 19 on one side of the heat dissipation shell 7, the structural strength of the heat dissipation shell 7 can be enhanced, and the heat dissipation area of ​​the heat dissipation shell 7 can be increased, thereby accelerating the heat dissipation speed of the controller.

[0040] Embodiment 5:

[0041] like Figure 5As shown, a heat conducting sheet 15 is installed in the heat dissipation shell 7, and the heat conducting sheet 15 is installed in close contact with the heat dissipation shell 7. Further, the heat conducting sheet is installed on the back cover 8, and one side of the heat conducting sheet 15 is in close contact with the heat generating components on the control end 16. When the control end 16 is working, the heat generated by the heat generating components is transferred to the heat dissipation shell 7 through the heat conducting sheet 15, and the heat dissipation shell 7 is transferred to the external air through the second fins 13 and the ribs 19, so as to accelerate the heat dissipation, and then the control end 16 is quickly cooled through the heat dissipation shell 7.

[0042] By installing the heat conducting sheet 15 in the heat dissipation shell 7, the heat conduction of the components inside the controller can be facilitated, and the heat dissipation of the controller can be accelerated.

[0043] Embodiment 6:

[0044] like Figure 3-4 As shown, a plurality of threaded holes 18 are provided on the connecting pipe 11, and a plurality of positioning holes 17 are provided on the heat dissipation shell 7. The positioning holes 17 are aligned with the threaded holes 18 one by one. During installation, bolts are passed through the positioning holes 17 and screwed into the threaded holes 18 to connect the heat dissipation shell 7 to the stator frame 2.

[0045] By providing the positioning holes 17 and the threaded holes 18 , the connection between the heat dissipation shell 7 and the stator frame 1 can be facilitated, thereby facilitating the connection between the controller and the motor.

[0046] Working principle: When in use, the heat dissipation shell 7 is fixedly installed on one side of the stator frame 2, so that the controller and the motor are compactly installed together, which greatly saves space and is beneficial to the internal space design of the drone, such as increasing the space ratio of the internal battery of the drone, which is beneficial to improving the endurance of the drone;

[0047] When the motor rotates counterclockwise, the first fin 10 rotates synchronously with the motor. On the one hand, a rotating airflow is formed behind the motor to dissipate heat for the controller behind. Compared with passive heat dissipation, this heat dissipation method has a better effect on the controller. On the other hand, the rotating first fin 10 acts as a centrifugal fan, increasing the speed of the external airflow entering the motor through the air inlet 9, thereby increasing the heat dissipation speed inside the motor.

[0048] Therefore, the air-cooled heat dissipation power system assembly for electric aircraft designed by the present invention integrates the motor and the controller into one, which saves installation space for the electric aircraft. The heat dissipation effect of the entire air-cooled heat dissipation power system assembly is better, which is beneficial to improving the stability of the power system.

Claims

1. An air-cooled heat dissipation power system assembly for an electric aircraft, characterized in that: include: Electric motors and controllers; The electric motor comprises a stator and a rotor; The stator comprises a stator shaft (1) and a stator frame (2), and a stator coil (3) is mounted on the stator frame (2); The rotor comprises a front cover (4) rotatably mounted on the stator shaft (1), a rotating shell (5) being mounted on one side of the front cover (4), and a magnetic steel (6) being mounted inside the rotating shell (5); The controller comprises a housing and a control terminal (16); The housing comprises a heat dissipation shell (7) and a rear cover (8), and the heat dissipation shell (7) is connected to one side of the stator frame (2); The front cover (4) is provided with an air inlet hole (9); A plurality of first fins (10) are evenly mounted on the rotating shell (5).

2. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 1, characterized in that: A connecting pipe (11) is installed on the stator frame (2), and the stator coil (3) is connected to the connecting pipe (11).

3. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 2, characterized in that: Internal heat dissipation fins (14) are provided on the inner side of the connecting pipe (11).

4. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 1, characterized in that: The stator frame (2) is provided with an exhaust hole (12).

5. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 1, characterized in that: A plurality of second fins (13) are evenly mounted on the heat dissipation shell (7).

6. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 5, characterized in that: The first fin (10) and the second fin (13) are bent and tilted in opposite directions.

7. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 1, characterized in that: A plurality of ribs (19) are evenly arranged on one side of the heat dissipation shell (7) close to the stator frame (2).

8. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 1, characterized in that: A heat conducting sheet (15) is installed in the heat dissipation shell (7).

9. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 3, characterized in that: The connecting pipe (11) is provided with a plurality of threaded holes (18).

10. The air-cooled heat dissipation power system assembly for an electric aircraft according to claim 9, characterized in that: The heat dissipation shell (7) is provided with a plurality of positioning holes (17), and the positioning holes (17) are aligned one by one with the threaded holes (18).

Images