An automated testing system for flight controllers

Abstract

This utility model discloses an automatic testing system for flight controllers, relating to the field of unmanned aerial vehicle (UAV) technology. It includes a control unit, a sensor unit, a storage unit, a detection unit, a power supply unit, a display unit, an input unit, and an interface unit. The control power supply includes a master MCU and a slave MCU. The control unit is connected to the sensor unit, storage unit, detection unit, power supply unit, display unit, input unit, and interface unit. The sensor unit includes a compass, a barometer, and an IMU, and is connected to the detection unit. The storage unit contains a TF card. This utility model eliminates the need for additional instruments, reducing the cost of purchasing equipment. Furthermore, only the automatic testing system needs to be learned, reducing the learning difficulty and manual training costs for workers. Simultaneously, the flight controller is connected to the system via a single cable, reducing connection difficulty and shortening testing time from approximately 2 hours to about 10 minutes.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and specifically to an automatic testing system for flight controllers. Background Technology

[0002] With the rapid development of the drone industry, the performance and quality of the flight controller, as the core control unit of the drone, are of paramount importance. Comprehensive and accurate testing of the flight controller is a key step in ensuring the normal operation of the drone.

[0003] However, existing flight controller testing solutions require a regulated power supply for voltage, current, and overcurrent testing, followed by overcurrent testing using a load cell; serial port, CAN port, and USB testing require corresponding converters before connecting to a computer for communication with the host computer; I2C testing requires connecting to the corresponding sensor, with the host computer displaying whether it is detected; RC testing requires connecting to the actual remote controller, with the host computer checking for connection; TF testing is determined by checking for logs on the host computer; PWM testing uses a logic analyzer connected to the interface, with manual judgment of whether the PWM value matches the setting; IMU testing involves manual judgment of attitude data viewed on the host computer; and testing of barometers and... During testing, the current altitude and heading are first obtained through other devices, and then the corresponding data from the flight controller is obtained through the host computer. The data is then manually checked for consistency. Finally, all test results are manually recorded to the computer. Due to the variety of flight controller interface types, multiple devices need to be connected during testing, making the operation cumbersome and increasing the learning cost for workers. Data relies on manual judgment, which can easily lead to errors and omissions in the testing process, and the consistency is unclear. Test records cannot be accurately recorded, and manual operation is prone to errors and omissions. The testing time is long, taking about 2 hours to complete all steps, which leads many companies to not conduct testing or to conduct incomplete testing. Therefore, we propose an automated testing system for flight controllers. Utility Model Content

[0004] In view of the problems existing in the above-mentioned automatic testing systems for flight controllers, this utility model is proposed.

[0005] Therefore, the purpose of this utility model is to provide an automatic testing system for flight controllers, which solves the problems of existing flight controller testing schemes. These schemes require a regulated power supply for testing voltage, current, and overcurrent, followed by overcurrent testing using a load cell; testing serial ports, CAN ports, and USB ports requires connecting to corresponding converters before connecting to a computer for communication with the host computer; testing I2C requires connecting to a corresponding sensor, with the host computer displaying whether it is detected; testing RC requires connecting to a real remote controller, with the host computer checking for connection; testing TF requires checking for logs on the host computer; and testing PWM requires a logic analyzer connected to the interface, with manual judgment of whether the PWM value matches the setting. The IMU testing process involves manually judging attitude data via a host computer; when testing the barometer and compass, the current altitude and heading are first obtained through other devices, then the corresponding data from the flight controller is obtained through the host computer, and the consistency of the values ​​is manually judged; finally, all test results are manually recorded to the computer. Due to the diverse interface types of flight controllers, multiple devices need to be connected during testing, making the operation cumbersome and increasing the learning cost for workers; data relies on manual judgment, making the testing process prone to errors and omissions, and consistency unclear; test records cannot be accurately recorded, and manual operation is prone to errors and omissions; the testing time is long, taking about 2 hours to complete all steps, leading many companies to not conduct testing or to conduct incomplete testing.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] An automatic testing system for a flight controller includes a control unit, a sensor unit, a storage unit, a detection unit, a power supply unit, a display unit, an input unit, and an interface unit. The control power supply includes a master MCU and a slave MCU. The control unit is connected to the sensor unit, storage unit, detection unit, power supply unit, display unit, input unit, and interface unit. The sensor unit includes a compass, a barometer, and an IMU, and is connected to the detection unit. The storage unit contains a TF card and is connected to the control unit.

[0008] Preferably, the detection unit includes a level conversion chip, an analog signal detection module, and an I / O input module, and the detection unit is connected to the control unit and the interface unit respectively.

[0009] Preferably, the display unit includes an LCD touchscreen and is connected to the control unit.

[0010] Preferably, the input unit includes two buttons and is connected to the control unit.

[0011] Preferably, the interface unit is a J30J aviation interface, and the interface unit is connected to the detection unit and the control unit respectively.

[0012] Preferably, the power supply unit is connected to both the control unit and the interface unit.

[0013] The technical effects and advantages provided by this utility model in the above technical solution are as follows:

[0014] 1. This utility model requires no additional instruments, reducing the cost of purchasing instruments. Furthermore, only the automatic testing system needs to be learned, which reduces the learning difficulty and manual training cost for workers. At the same time, the flight controller is connected to the system through a single cable, which reduces the connection difficulty and shortens the testing time from about 2 hours to about 10 minutes.

[0015] 2. In this utility model, the testing process is completed automatically by the machine, reducing human intervention, improving the accuracy and consistency of the test, reducing the error rate, and increasing the yield of flight controllers. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0017] Figure 1 This is a schematic diagram showing the overall composition and connection relationship of this utility model.

[0018] Explanation of reference numerals in the attached figures:

[0019] 1. Control unit; 2. Sensor unit; 3. Storage unit; 4. Detection unit; 5. Power supply unit; 6. Display unit; 7. Input unit; 8. Interface unit; 9. Compass; 10. Barometer; 11. IMU; 12. TF card. Detailed Implementation

[0020] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0021] This utility model discloses an automatic testing system for flight controllers.

[0022] This utility model provides, for example Figure 1An automatic testing system for a flight controller is shown, comprising a control unit 1, a sensor unit 2, a storage unit 3, a detection unit 4, a power supply unit 5, a display unit 6, an input unit 7, and an interface unit 8. The control power supply includes a master MCU and a slave MCU. The control unit 1 is connected to the sensor unit 2, storage unit 3, detection unit 4, power supply unit 5, display unit 6, input unit 7, and interface unit 8. The sensor unit 2 includes a compass 9, a barometer 10, and an IMU 11, and is connected to the detection unit 4. The storage unit 3 includes a TF card 12 and is connected to the control unit 1. The sensor unit 2 is used to measure the heading, altitude, and attitude of the current automatic testing system. The storage unit 3 is used to store various test results generated during the testing process. The control unit 1 is used to control the operation of the entire system, process various detection data, and make judgments.

[0023] This utility model discloses an automatic testing system for a flight controller. The detection unit 4 includes a level conversion chip, an analog quantity detection module, and an IO input module. The detection unit 4 is connected to the control unit 1 and the interface unit 8, respectively. The detection unit 4 is used to detect the voltage, current, serial port, CAN port, PWM, RC, I2C, etc. of the flight controller.

[0024] This utility model discloses an automatic testing system for flight controllers. The display unit 6 includes an LCD touch screen and is connected to the control unit 1. The display unit 6 is used to display the testing process and results.

[0025] This utility model discloses an automatic testing system for flight controllers. The input unit 7 includes two buttons and is connected to the control unit 1. The input unit 7 is used for switching test items and entering firmware update modes of the automatic testing system.

[0026] This utility model discloses an automatic testing system for a flight controller. The interface unit 8 is a J30J aviation interface, and the interface unit 8 is connected to the detection unit 4 and the control unit 1 respectively. The interface unit 8 is used to connect the flight controller and the automatic testing system.

[0027] This utility model discloses an automatic testing system for flight controllers. The power supply unit 5 is connected to the control unit 1 and the interface unit 8 respectively. The power supply unit 5 is used to supply power to the entire automatic testing system and the flight controller to be tested.

[0028] During use, the flight controller connects to the automatic testing system via interface unit 8. Control unit 1 controls power supply unit 5 to supply power to the flight controller. Simultaneously, it acquires the voltage and current of the flight controller via detection unit 4 to determine if there is an internal short circuit. Control unit 1 performs communication tests on the flight controller's serial port via detection unit 4, using a question-and-answer format to determine if the serial port is functioning correctly. It also performs communication tests on the CAN port, acquiring data and calculating packet loss rate to determine if the CAN interface is faulty. For PWM testing, control unit 1 acquires the current PWM output value of the flight controller via detection unit 4 and simultaneously acquires the actual output value via the PWM interface of detection unit 4, comparing the two to determine if the PWM is functioning correctly. For RC testing, control unit 1 acquires the current RC input value of the flight controller via detection unit 4 and simultaneously outputs an RC value to the flight controller via the RC interface of detection unit 4, comparing the two RC values ​​to determine if the RC is functioning correctly. Control unit 1 downloads the flight controller's logs via serial communication with detection unit 4. If the download is successful, the TF (transmission unit) is functioning correctly. The flight controller then functions as an I2C host. When in motion, the system initiates a sensor reading operation. After obtaining the address requested by the flight controller through the detection unit 4, the control unit 1 confirms that the I2C interface is normal. As a USB host, the control unit 1 connects to the flight controller's USB interface through the interface unit 8, obtains the USB device descriptor, and determines the flight controller type and whether the USB interface is normal based on the descriptor. The control unit 1 obtains the flight controller's attitude information through serial communication with the detection unit 4 and compares it with the attitude of the automatic test system measured by the sensor unit 2. If they match, it indicates that the IMU 11 is normal. Similarly, the control unit 1 compares the flight controller's altitude and heading with the corresponding system data measured by the sensor unit 2 to determine whether the barometer 10 and compass 9 are normal. The control unit 1 sets the flight controller's parameters through serial communication with the detection unit 4, controls its power-off to ensure that the parameters are stored in the ferroelectric memory, and then reads the parameters. If the read and write are consistent, it indicates that the ferroelectric memory is normal. The control unit 1 stores each test result through the storage unit 3 and displays the test process and results through the display unit 6. The user can switch test items and enter firmware update operations through the input unit 7.

[0029] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An automatic testing system for a flight controller, comprising a control unit (1), a sensor unit (2), a storage unit (3), a detection unit (4), a power supply unit (5), a display unit (6), an input unit (7), and an interface unit (8), characterized in that, The control unit includes a master MCU and a slave MCU, and the control unit (1) is connected to the sensor unit (2), storage unit (3), detection unit (4), power supply unit (5), display unit (6), input unit (7) and interface unit (8) respectively. The sensor unit (2) includes a compass (9), a barometer (10) and an IMU (11), and the sensor unit (2) is connected to the detection unit (4). The storage unit (3) includes a TF card (12), and the storage unit (3) is connected to the control unit (1).

2. The automatic testing system for flight controllers according to claim 1, characterized in that, The detection unit (4) includes a level conversion chip, an analog quantity detection module and an IO input module, and the detection unit (4) is connected to the control unit (1) and the interface unit (8) respectively.

3. The automatic testing system for flight controllers according to claim 1, characterized in that, The display unit (6) includes an LCD touch screen and is connected to the control unit (1).

4. The automatic testing system for flight controllers according to claim 1, characterized in that, The input unit (7) includes two buttons and is connected to the control unit (1).

5. The automatic testing system for flight controllers according to claim 1, characterized in that, The interface unit (8) is a J30J aviation interface, and the interface unit (8) is connected to the detection unit (4) and the control unit (1) respectively.

6. The automatic testing system for flight controllers according to claim 1, characterized in that, The power supply unit (5) is connected to the control unit (1) and the interface unit (8) respectively.

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