Device for testing heat dissipation power of heat dissipation module of motor controller in flight state of simulated unmanned aerial vehicle

Abstract

The invention provides a device for testing the heat dissipation power of a heat dissipation module of a motor controller in a simulated flight state of an unmanned aerial vehicle, and the device comprises a linear positioning device which is installed on a rack panel; the heat dissipation simulation device is mounted on the moving platform of the linear positioning device; the air speed and air quantity test sensor is mounted at an air outlet of the rack air duct; the test control system display equipment is mounted on the rack; the wind condition simulation device is mounted on the rack panel; the heat source simulation device is mounted on the heat dissipation simulation device; and the mechanical control button panel is mounted on the rack. The linear positioning device, the heat dissipation simulation device, the air speed and air volume test sensor, the air condition simulation device, the heat source simulation device, the mechanical control button panel and the industrial personal computer are all connected with the motion control system. And the test control system display equipment is connected with the industrial personal computer. The device provided by the invention can realize accurate simulation of heat dissipation conditions, comprehensive evaluation of heat dissipation performance and optimal design of data, and has remarkable technical advantages.

Description

TECHNICAL FIELD

[0001] The application relates to a device for testing the heat dissipation power of a motor controller heat dissipation module in a simulated flight state of an unmanned aerial vehicle, and belongs to the technical field of testing devices. BACKGROUND

[0002] With the rapid development of aviation technology, the performance requirements of unmanned aerial vehicles are increasingly improved, and the high heat power of internal electronic components has become one of the key factors restricting the performance improvement of unmanned aerial vehicles. During flight, the power module of the motor controller generates a large amount of heat, in order to ensure the reliability and service life of the motor controller, the heat generated by the power module must be effectively dissipated to ensure that the working temperature is maintained within an appropriate range. Therefore, the performance of the heat dissipation assembly is directly related to the service life and reliability of the internal units of the controller. The traditional heat dissipation assembly test method is usually carried out under static conditions, and cannot accurately simulate the heat dissipation of the aircraft in the actual flight state. Because the wind speed and environmental conditions experienced by the unmanned aerial vehicle during flight are significantly different from those on the ground, this leads to a large deviation between the actual performance of the heat dissipation assembly and the static test results. Therefore, it is particularly important to design a device for testing the heat dissipation power of a motor controller heat dissipation module in a simulated flight state. The device needs to simulate the wind speed conditions in the flight state of the unmanned aerial vehicle, and accurately measure the heat dissipation performance of the heat dissipation module under different flight states. Through this simulation test, the actual working performance of the heat dissipation module can be more accurately evaluated, thereby providing reliable data support for the design and optimization of the heat dissipation module. However, existing heat dissipation module test equipment usually does not have the function of simulating the flight state, or has certain limitations when simulating the flight state. For example, the air duct design is unreasonable, the fan speed is not adjustable, the heat source and the heat dissipation assembly do not cooperate well, and other problems may lead to inaccurate test results. Therefore, it is necessary to develop a new type of device for testing the heat dissipation power of a motor controller heat dissipation module in a simulated flight state of an unmanned aerial vehicle, which has important practical application value and broad development prospects. SUMMARY

[0003] The technical problem solved by the present application is to overcome the shortcomings of the prior art and provide a device for testing the heat dissipation power of a motor controller heat dissipation module in a simulated flight state of an unmanned aerial vehicle, which improves the efficiency of the test operation of the heat dissipation module.

[0004] The technical solution of the present application is:

[0005] The application discloses a device for testing the heat dissipation power of a motor controller heat dissipation module in a simulated flight state of an unmanned aerial vehicle, comprising a rack, a linear positioning device, a heat dissipation simulation device, a wind speed and volume test sensor, a wind condition simulation device, a heat source simulation device, an industrial computer and a motion controller, wherein,

[0006] The air duct is arranged on the rack; the linear positioning device is partially arranged in the air duct of the rack; the heat dissipation simulation device is arranged on the linear positioning device; the linear positioning device drives the heat dissipation simulation device to enter and exit the air duct.

[0007] The heat source simulation device provides a heat source for the heat dissipation simulation device, simulating the heat dissipation condition of the unmanned aerial vehicle in flight state.

[0008] The wind condition simulation device simulates the wind condition of the unmanned aerial vehicle in flight state.

[0009] The wind speed and volume test sensor is arranged in the air duct to measure the actual wind speed and volume received by the tested piece arranged on the heat dissipation simulation device.

[0010] The industrial computer sends a control instruction to the motion controller according to the wind speed and volume collected by the wind speed and volume test sensor, controls the linear positioning device to drive the heat dissipation simulation device to move linearly, controls the output wind speed of the wind condition simulation device, and obtains the heat dissipation power of the motor controller heat dissipation module in the flight state of the unmanned aerial vehicle.

[0011] Further, in the above test device, a mechanical control button panel is further included, when the industrial computer detects that the test result is unqualified, the test is stopped through the button arranged on the mechanical control button panel, the motion controller is controlled through the button, the linear positioning device withdraws the tested piece from the air duct, and the tested piece is replaced.

[0012] Further, in the above test device, the linear positioning device includes a linear module, a servo motor, a linear positioning device mounting base plate, a positioning pin and a heat dissipation simulation device mounting base; the linear module is arranged on the rack; the servo motor is arranged at the end of the linear module; the linear module is provided with a sliding rail, and a pin hole is arranged on the sliding rail; the sliding rail of the linear module is connected with the heat dissipation simulation device mounting base through the motion positioning mounting base plate; the positioning pin is fixed in the pin hole of the linear module; the motion controller controls the servo motor to drive the sliding rail of the linear module to move, drives the heat dissipation simulation device mounting base to move linearly and position; the heat dissipation simulation device mounting base is connected with the heat dissipation simulation device, and the heat dissipation condition of the unmanned aerial vehicle in flight state is simulated through the heat dissipation simulation device and the wind condition simulation device after the heat dissipation simulation device mounting base moves to a specified position.

[0013] Further, in the above test device, the heat dissipation simulation device comprises a lower positioning plate, a left wind baffle, a front wind baffle, an upper wind baffle, a heat dissipation module fin, a fin fixing plate, a fixing plate support column, a heat dissipation module heat pipe and a right wind baffle; wherein the lower positioning plate is connected with the heat dissipation simulation device installation base of the linear positioning device; the left wind baffle, the front wind baffle and the right wind baffle are connected with the lower positioning plate; the upper wind baffle is connected with the left wind baffle, the front wind baffle and the right wind baffle; the heat dissipation module fin is installed on the fin fixing plate; the fin fixing plate is supported by the fixing plate support column; the fixing plate support column is connected with the lower positioning plate; and the heat dissipation module heat pipe is connected with the heat dissipation module fin.

[0014] Further, in the above test device, after the linear positioning device moves to the specified position, the wind condition simulation device starts to simulate the wind condition of the aircraft in flight state; the left wind baffle, the front wind baffle, the upper wind baffle and the right wind baffle ensure that the wind in the air duct only acts on the heat dissipation module fin; the fin fixing plate and the fixing plate support column ensure that the heat dissipation module fin remains stable and fixed in the simulation state; the heat source provided by the heat source simulation device is conducted to the heat dissipation module fin through the heat dissipation module heat pipe, so as to simulate the heat dissipation condition of the unmanned aerial vehicle in flight state; and the actual wind speed and wind volume of the heat dissipation simulation device are measured by the wind speed and wind volume test inductor.

[0015] Further, in the above test device, it further comprises a test control system display device installed on the rack top end panel; the test control system display device is connected with the industrial computer, and displays the motion state and position of the linear positioning device, the heat source temperature and power output by the heat dissipation simulation device, the actual wind speed and wind volume measured by the wind speed and wind volume test inductor, and the heat dissipation module heat dissipation power test curve in real time.

[0016] Further, in the above test device, the wind condition simulation device comprises a front support column, a left support column, a fan installation base, a stepless speed fan, a rear support column and a right support column; wherein the front support column, the left support column, the rear support column and the right support column are installed on the inner panel of the rack air duct and connected with the rack; the fan installation base is connected with the front support column, the left support column, the rear support column and the right support column; the stepless speed fan is installed on the fan installation base; and the front support column, the left support column, the rear support column, the right support column and the fan installation base ensure the stable fixation of the stepless speed fan in the running state, so that after the heat dissipation simulation device reaches the simulation temperature, the wind speed and wind volume in different flight conditions are simulated by adjusting the stepless speed fan.

[0017] Further, in the above test device, the heat dissipation simulation device and the stepless speed fan in the wind condition simulation device are in the same central axis plane, and the position is calibrated by a laser range finder to ensure that the relative position error of the heat dissipation simulation device and the stepless speed fan is less than 0.1 mm, and the output wind speed of the stepless speed fan is adjusted to simulate the heat dissipation condition of the unmanned aerial vehicle in flight state.

[0018] Further, in the above test device, the heat source simulation device comprises a constant power programmable power supply, a left support column, a mounting base, a copper block, a right support column, a heat source heat plate and a heat pipe pressing plate; wherein the left support column and the right support column are fixed on the lower positioning plate of the heat dissipation simulation device; the mounting base is connected with the left support column and the right support column; the copper block is fixed in the notch of the mounting base; the heat source heat plate covers the copper block and is connected with the mounting base; the notch provided on the heat pipe pressing plate covers and fixes the heat pipe of the heat dissipation module of the heat dissipation simulation device, and is connected with the heat source heat plate; the constant power programmable power supply is connected with the copper block through a wire.

[0019] Further, in the above test device, the constant power programmable power supply heats the copper block, the copper block conducts the simulated heat source to the heat source heat plate, a plurality of constant power programmable power supplies and copper blocks simultaneously simulate different heat source conditions, and the heat source heat plate conducts the simulated heat source to the heat pipe of the heat dissipation module of the heat dissipation simulation device, so as to simulate the heat source condition of the unmanned aerial vehicle in flight state.

[0020] The beneficial effects of the present application over the prior art are:

[0021] (1) The present application mainly solves the problems of insufficient coverage of performance test of unmanned aerial vehicle motor controller heat dissipation module, insufficient simulation of working condition, low operation efficiency and the like, and proposes a heat dissipation power test device for simulating the heat dissipation of motor controller heat dissipation module in flight state of unmanned aerial vehicle, so as to accurately evaluate the performance of the heat dissipation module, thereby improving the overall performance and reliability of the unmanned aerial vehicle motor controller in the process of executing flight task.

[0022] (2) The present application can accurately simulate the heat dissipation working condition of the aircraft in high-altitude high-speed flight through the cooperative work of the heat dissipation simulation device and the wind condition simulation device. The heat dissipation simulation device heats the copper block through the constant power programmable power supply to simulate the heat source condition of the aircraft; the wind condition simulation device adjusts the wind speed to simulate the heat dissipation environment of the aircraft. This simulation method can highly restore the heat dissipation scene in actual flight, and provide more real conditions for the test of the heat dissipation system.

[0023] (3) The positioning mechanism, the wind condition simulation device, the heat dissipation simulation device, the sensor and the control system are highly integrated and automated, the test results are automatically generated in the form of digital display, the test efficiency is improved, the operation difficulty and error probability are reduced, the problems of complex traditional test method and low test environment restoration degree are solved. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 It is a schematic diagram of the three-dimensional structure of the present application;

[0025] Figure 2 It is a schematic diagram of the three-dimensional structure of the linear positioning device of the present application;

[0026] Figure 3 It is a schematic diagram of the three-dimensional structure of the heat dissipation simulation device of the present application;

[0027] Figure 4 It is a schematic diagram of the three-dimensional structure of the wind speed and volume test sensor of the present application;

[0028] Figure 5 It is a schematic diagram of the three-dimensional structure of the test control system display device of the present application;

[0029] Figure 6 It is a schematic diagram of the three-dimensional structure of the wind condition simulation device of the present application;

[0030] Figure 7 It is a schematic diagram of the three-dimensional structure of the heat source simulation device of the present application, (a) is a schematic diagram of the constant power program-controlled power supply structure, (b) is a schematic diagram of the left support column, the mounting base, the copper block and the right support column connection, (c) is a schematic diagram of the heat source heat plate and the heat pipe pressing plate. DETAILED DESCRIPTION

[0031] The present application will be further described in detail below in combination with the drawings and specific embodiments.

[0032] As shown in the drawings, Figure 1 The present application is a kind of simulation unmanned aerial vehicle flight state under the motor controller heat dissipation module heat dissipation power test device, including rack 1, linear positioning device 2, heat dissipation simulation device 3, wind speed and volume test sensor 4, test control system display device 5, wind condition simulation device 6, heat source simulation device 7, mechanical control button panel 8, industrial computer and motion controller;

[0033] Linear positioning device 2 is installed on rack 1;

[0034] Heat dissipation simulation device 3 is installed on linear positioning device 2;

[0035] Heat source simulation device 7 is installed on heat dissipation simulation device 3;

[0036] The wind speed and volume testing sensor 4, the testing control system display device 5, the wind condition simulation device 6 and the mechanical control button panel 8 are all installed on the device rack 1.

[0037] The linear positioning device 2, the heat dissipation simulation device 3, the wind speed and volume testing sensor 4, the wind condition simulation device 6, the mechanical control button panel 8 and the industrial computer are respectively connected with the motion controller.

[0038] The testing control system display device 5 and the industrial computer are connected.

[0039] As shown in Figure 2 , the linear positioning device 2 comprises a linear module 9, a servo motor 10, a motion positioning installation base plate 11, a positioning pin 12 and a heat dissipation simulation device installation base 13; the linear module 9 is installed on the panel of the rack 1; the servo motor 10 is installed at the front end of the linear module 9, and the linear module 9 is driven by the servo motor 10 to perform linear positioning and motion, so that the heat dissipation simulation device 3 and the stepless speed fan 25 in the wind condition simulation device 6 are in the same central axis plane, and the position is calibrated by the laser range finder, so as to ensure that the relative position error between the heat dissipation simulation device 3 and the stepless speed fan 25 is less than ±0.1mm, and the output wind speed of the stepless speed fan 25 is adjusted to simulate the heat dissipation condition of the unmanned aerial vehicle in the flight state; the motion positioning installation base plate 11 is connected with the slide rail of the linear module 9 through screw connection, and the slide rail of the linear module 9 is connected with the heat dissipation simulation device installation base 13 through the motion positioning installation base plate 11; the positioning pin 12 is fixed in the pin hole of the linear module 9; the heat dissipation simulation device installation base 13 is connected with the motion positioning installation base plate 11 through screw connection; the slide rail of the linear module 9 is driven by the servo motor 10 to move, so as to drive the heat dissipation simulation device installation base 13 to perform linear motion and positioning; the heat dissipation simulation device installation base 13 is connected with the heat dissipation simulation device 3 through screw connection, and after the heat dissipation simulation device installation base 13 moves to the specified position, the heat dissipation condition of the unmanned aerial vehicle in the flight state is simulated by the heat dissipation simulation device 3 and the wind condition simulation device 6.

[0040] As shown in Figure 3As shown, the heat dissipation simulation device 3 includes a lower positioning plate 14, a left wind baffle 15, a front wind baffle 16, an upper wind baffle 17, a heat dissipation module fin 18, a fin fixing plate 19, a fixing plate support column 20, a heat dissipation module heat pipe 21 and a right wind baffle 22; the lower positioning plate 14 is connected with the heat dissipation simulation device installation base 13 of the linear positioning device 2 through threads; the left wind baffle 15, the front wind baffle 16 and the right wind baffle 22 are connected with the lower positioning plate 14 through threads; the upper wind baffle 17 is connected with the left wind baffle 15, the front wind baffle 16 and the right wind baffle 22 through threads; the heat dissipation module fin 18 is installed on the fin fixing plate 19; the fin fixing plate 19 is supported by the fixing plate support column 20; the fixing plate support column 20 is connected with the lower positioning plate 14; the heat dissipation module heat pipe 21 is connected with the heat dissipation module fin 18; after the linear positioning device 2 moves to a specified position, the wind condition simulation device 6 starts to simulate the wind channel condition in the flight state of the unmanned aerial vehicle, the left wind baffle 15, the front wind baffle 16, the upper wind baffle 17 and the right wind baffle 22 ensure that the wind in the wind channel only acts on the heat dissipation module fin 18, and does not affect the heat source simulation device 7, the fin fixing plate 19 and the fixing plate support column 20 ensure the stable fixation of the heat dissipation module fin 18 in the simulation state, the heat source provided by the heat source simulation device 7 is conducted to the heat dissipation module fin 18 through the heat dissipation module heat pipe 21, so as to simulate the heat dissipation condition in the flight state of the unmanned aerial vehicle.

[0041] As shown in Figure 4 , the wind speed and volume test sensor 4 is installed in the wind channel of the rack 1 at a specified position before the heat dissipation simulation device 3; the actual wind speed and volume acting on the heat dissipation module fin 18 of the heat dissipation simulation device 3 are measured by the wind speed and volume test sensor 4.

[0042] As shown in Figure 5 , the test control system display device 5 is installed on the top end panel of the rack 1; the test control system display device 5 is connected with the industrial computer, and displays the motion state and position of the linear positioning device 2, the heat source temperature and power output by the heat dissipation simulation device 3, the actual wind speed and volume acting on the wind speed and volume test sensor 4, and the heat dissipation module heat dissipation power test curve in real time.

[0043] As shown in Figure 6As shown in the figure, the wind condition simulation device 6 includes a front support column 23, a left support column 24, a fan mounting base 26, a stepless speed fan 25, a rear support column 27 and a right support column 28; the front support column 23, the left support column 24, the rear support column 27 and the right support column 28 are mounted on the panel on the inner surface of the air duct of the rack 1 and are connected with the panel of the rack 1 through threads; the fan mounting base 26 is connected with the front support column 23, the left support column 24, the rear support column 27 and the right support column 28 through threads; the stepless speed fan 25 is mounted on the fan mounting base 26; the front support column 23, the left support column 24, the rear support column 27, the right support column 28 and the fan mounting base 26 ensure the stable fixation of the stepless speed fan 25 in the running state; after the heat dissipation simulation device 3 reaches the simulation temperature, the wind speed and the wind volume in different flight conditions are simulated by adjusting the stepless speed fan 25.

[0044] As shown in the figure, Figure 7 As shown in the figure, the heat source simulation device 7 includes a constant power program-controlled power supply 29, a left support column 30, a mounting base 31, a copper block 32, a right support column 33, a heat source heat plate 34 and a heat pipe pressing plate 35; the left support column 30 and the right support column 33 are fixed on the lower positioning plate 14 of the heat dissipation simulation device 3; the mounting base 31 is connected with the left support column 30 and the right support column 33 through threads; the copper block 32 is fixed in the slot of the mounting base 31; the heat source heat plate 34 covers the copper block 32 and is connected with the mounting base 31 through threads; the heat pipe pressing plate 35 covers and fixes the heat dissipation module heat pipe 21 of the heat dissipation simulation device 3 and is connected with the heat source heat plate 34 through threads; the constant power program-controlled power supply 29 heats the copper block 32, the copper block 32 conducts the simulated heat source to the heat source heat plate 34, three groups of constant power program-controlled power supply 29 and copper block 32 can simultaneously simulate different heat source conditions, the heat source heat plate 34 conducts the simulated heat source to the heat dissipation module heat pipe 21 of the heat dissipation simulation device 3, so as to simulate the heat source condition in the flight state of the unmanned aerial vehicle.

[0045] The working principle of the simulation unmanned aerial vehicle flight state motor controller heat dissipation module heat dissipation power test device of the application is as follows:

[0046] In combination with Figures 1-7At the beginning of the test process, the motor controller heat sink module to be tested is first placed on the fin fixing plate of the heat sink simulator 3. The heat source heat sink 34 and heat pipe pressing plate 35 of the heat source simulator 7 simultaneously cover and secure the heat sink module heat pipe 21 of the heat sink simulator 3. Subsequently, the servo motor 10 of the linear positioning device 2 drives the linear module 9 for precise movement and positioning to ensure accurate alignment between the heat sink simulator 3 and the wind condition simulator 6. Next, the wind condition simulator 6 and the heat source simulator 7 are started. The continuously variable speed blower 25 of the wind condition simulator 6 is activated. By adjusting the continuously variable speed blower 25, wind speed and air volume under different flight conditions can be simulated. The front support column 23, left support column 24, rear support column 27, and right support column 28 ensure the stable fixation of the continuously variable speed blower 25 in the operating state. The fin fixing plate 19 and fixing plate support column 20 of the heat sink simulator 3 ensure the stable fixation of the heat sink module fins 18 in the simulation state. The left windshield 15, front windshield 16, upper windshield 17, and right windshield 22 ensure that the wind within the air duct acts only on the heat sink module fins 18 and does not affect the heat source simulator 7. The constant-power programmable power supply 29 of the heat source simulator 7 heats a copper block 32 to simulate heat source conditions. The copper block 32 transfers the heat to the heat source vapor chamber 34, which in turn transfers the heat to the heat sink module heat pipe 21, thereby simulating the heating of the motor controller power module under different flight conditions. During the test, the test control system display device 5 displays in real time the heat sink module's heat source temperature, power, the actual wind speed and air volume measured by the wind speed and air volume test sensor 4, and the heat sink module's heat dissipation power test curve. By adjusting the continuously variable speed fan 25, heat dissipation conditions under different flight conditions are simulated to evaluate the heat sink module's performance. After the heat dissipation performance test is completed, the test control system display device 5 records and analyzes the heat sink module's heat dissipation power test curve to evaluate its performance under simulated flight conditions. If the performance of the heat dissipation module does not meet the requirements, the simulation test is stopped through the mechanical control button panel 8, the linear positioning device 2 is moved outside the air duct, the heat dissipation module is replaced, and the test is repeated according to the initial operation.

[0047] Although the present invention has been described in detail through the above preferred embodiments, it should be understood that the above description is not intended to limit the present invention. After reading the above description, various modifications and substitutions of the present invention will become apparent to those skilled in the art. Therefore, the scope of protection of the present invention should be defined by the appended claims.

[0048] The contents not described in detail in the specification of the present invention belong to the common knowledge of professionals in this field.

Claims

1. A device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions, characterized in that: It includes a frame (1), a linear positioning device (2), a heat dissipation simulation device (3), a wind speed and air volume test sensor (4), a wind condition simulation device (6), a heat source simulation device (7), an industrial computer and a motion controller; wherein, An air duct is provided on the frame (1); the linear positioning device (2) is partially installed in the air duct of the frame (1); the heat dissipation simulation device (3) is installed on the linear positioning device (2); the linear positioning device (2) drives the heat dissipation simulation device (3) in and out of the air duct; The heat source simulation device (7) provides a heat source for the heat dissipation simulation device (3) to simulate the heat dissipation conditions of the UAV in flight; A wind condition simulation device (6) for simulating wind conditions when the UAV is in flight; A wind speed and air volume test sensor (4) is installed in the air duct to measure the actual wind speed and air volume received by the test piece installed in the heat dissipation simulation device (3); The industrial computer sends a control instruction to the motion controller based on the wind speed and wind volume collected by the wind speed and wind volume test sensor (4), controls the linear positioning device (2) to drive the heat dissipation simulation device (3) to perform linear positioning movement; controls the output wind speed of the wind condition simulation device (6), and obtains the heat dissipation power of the motor controller heat dissipation module when the UAV is in flight.

2. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 1, characterized in that: It also includes a mechanical control button panel (8). When the industrial computer detects that the test result is unqualified, the test is stopped by a button set on the mechanical control button panel (8). The button controls the motion controller to control the linear positioning device (2) to withdraw the tested piece from the air duct and replace the tested piece.

3. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 1, characterized in that: The linear positioning device (2) comprises a linear module (9), a servo motor (10), a linear positioning device mounting base (11), a positioning pin (12) and a heat dissipation simulation device mounting base (13); wherein the linear module (9) is mounted on a frame (1); the servo motor (10) is mounted at the end of the linear module (9); a slide rail is provided on the linear module (9), and a pin hole is provided on the slide rail; the slide rail of the linear module (9) is connected to the heat dissipation simulation device mounting base (13) through the motion positioning mounting base (11); the positioning pin (12) is fixed in the pin hole of the linear module (9); a motion controller controls the servo motor (10) to drive the slide rail of the linear module (9) to move, thereby driving the heat dissipation simulation device mounting base (13) to perform linear motion and positioning; the heat dissipation simulation device mounting base (13) is connected to the heat dissipation simulation device (3); after the heat dissipation simulation device mounting base (13) moves to a specified position, the heat dissipation condition of the unmanned aerial vehicle in flight is simulated by the heat dissipation simulation device (3) and the wind condition simulation device (6).

4. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 3, characterized in that: The heat dissipation simulation device (3) comprises a lower positioning plate (14), a left windshield (15), a front windshield (16), an upper windshield (17), heat dissipation module fins (18), a fin fixing plate (19), a fixing plate support column (20), a heat dissipation module heat pipe (21) and a right windshield (22); wherein the lower positioning plate (14) is connected to the heat dissipation simulation device mounting base (13) of the linear positioning device (2); the left windshield (15), the front windshield (16) and the upper windshield (17) are connected to the heat dissipation simulation device mounting base (13) of the linear positioning device (2); 6) and the right windshield (22) are connected to the lower positioning plate (14); the upper windshield (17) is connected to the left windshield (15), the front windshield (16) and the right windshield (22); the heat dissipation module fins (18) are installed on the fin fixing plate (19); the fin fixing plate (19) is supported by the fixing plate support column (20); the fixing plate support column (20) is connected to the lower positioning plate (14); the heat dissipation module heat pipe (21) is connected to the heat dissipation module fins (18).

5. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 4, characterized in that: After the linear positioning device (2) moves to the specified position, the wind condition simulation device (6) starts to simulate the wind condition of the aircraft in flight; the left windshield (15), the front windshield (16), the upper windshield (17) and the right windshield (22) ensure that the wind in the air duct acts only on the heat dissipation module fins (18); the fin fixing plate (19) and the fixing plate support column (20) ensure that the heat dissipation module fins (18) remain stable and fixed in the simulation state; the heat source provided by the heat source simulation device (7) is conducted to the heat dissipation module fins (18) through the heat dissipation module heat pipe (21), thereby simulating the heat dissipation conditions of the UAV in flight; the actual wind speed and wind volume received by the heat dissipation module fins (18) of the heat dissipation simulation device (3) are measured by the wind speed and wind volume test sensor (4).

6. The device for testing the heat dissipation power of a motor controller heat dissipation module under a simulated UAV flight state according to claim 1, characterized in that: The test control system also includes a test control system display device (5), which is installed on the top panel of the frame (1); the test control system display device (5) is connected to the industrial computer and displays in real time the movement state and position of the linear positioning device (2), the heat source temperature and power output by the heat dissipation simulation device (3), the actual wind speed and wind volume measured by the wind speed and wind volume test sensor (4), and the heat dissipation power test curve of the heat dissipation module.

7. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 1, characterized in that: The wind condition simulation device (6) comprises a front support column (23), a left support column (24), a fan mounting base (26), a stepless speed-variable fan (25), a rear support column (27) and a right support column (28); wherein the front support column (23), the left support column (24), the rear support column (27) and the right support column (28) are mounted on an inner panel of an air duct of a frame (1) and connected to the frame (1); the fan mounting base (26) is connected to the front support column (23), the left support column (24), The rear support column (27) and the right support column (28) are connected; the continuously variable speed fan (25) is installed on the fan mounting base (26); the front support column (23), the left support column (24), the rear support column (27), the right support column (28) and the fan mounting base (26) ensure that the continuously variable speed fan (25) is stably fixed in the operating state. After the heat dissipation simulation device (3) reaches the simulation temperature, the wind speed and air volume under different flight conditions are simulated by adjusting the continuously variable speed fan (25).

8. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 7, characterized in that: The heat dissipation simulation device (3) and the continuously variable speed fan (25) in the wind condition simulation device (6) are located on the same central axis plane, and position calibration is performed using a laser rangefinder to ensure that the relative position error between the heat dissipation simulation device (3) and the continuously variable speed fan (25) is less than 0.1 mm. The heat dissipation condition of the UAV in flight is simulated by adjusting the output wind speed of the continuously variable speed fan (25).

9. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 4, characterized in that: The heat source simulation device (7) comprises a constant power programmable power supply (29), a left support column (30), a mounting base (31), a copper block (32), a right support column (33), a heat source soaking plate (34) and a heat pipe pressing plate (35); wherein the left support column (30) and the right support column (33) are fixed on the lower positioning plate (14) of the heat dissipation simulation device (3); the mounting base (31) is connected to the left support column (30) and the right support column (33); the copper block (32) is fixed in the notch of the mounting base (31); the heat source soaking plate (34) covers the copper block (32) and is connected to the mounting base (31); the notch provided on the heat pipe pressing plate (35) covers and fixes the heat pipe (21) of the heat dissipation module of the heat dissipation simulation device (3) and is connected to the heat source soaking plate (34); the constant power programmable power supply (29) and the copper block (32) are connected via a wire.

10. The device for testing the heat dissipation power of a motor controller heat dissipation module under simulated UAV flight conditions according to claim 9, characterized in that: The constant power programmable power supply (29) heats the copper block (32), and the copper block (32) conducts the simulated heat source to the heat source soaking plate (34). Multiple groups of constant power programmable power supplies (29) and copper blocks (32) simultaneously simulate different heat source conditions. The heat source soaking plate (34) conducts the simulated heat source to the heat pipe (21) of the heat dissipation simulation device (3), simulating the heat source conditions of the drone in flight.

Images