Intelligent cockpit automated testing system, method, apparatus, processor and computer-readable storage medium thereof

Abstract

This invention relates to an automated testing system for intelligent cockpits. The system includes an industrial control computer, a CAN communication box, a serial communication module, a signal generator, a DIO module, an AIO module, a power amplifier load module, a signal conditioning board, a power supply module, a general-purpose switch, a PoE switch, a PoE camera, and host computer testing software. The invention also relates to a corresponding testing method. This automated testing system and method for intelligent cockpits provides a rich variety of hardware signal types and interfaces, supports automatic detection of various types of intelligent cockpits, and ensures that each hardware module is independent, exhibiting good compatibility and scalability. It also provides flexible and diverse instruction sets and freely editable test cases, greatly satisfying various specialized and customized testing needs of users. It is adaptable to multiple testing scenarios, has high versatility and adaptability, and reduces the problem of unusable automated testing equipment due to product iterations, thus possessing significant practical value.

Description

Technical Field

[0001] This invention relates to the field of automotive electronics testing technology, and more particularly to the field of intelligent cockpit automated testing technology, specifically to an intelligent cockpit automated testing system, method, device, processor, and computer-readable storage medium thereof. Background Technology

[0002] With the development of the automotive industry, automotive cockpit systems are becoming increasingly intelligent and electronic, with more powerful and diverse functions. While bringing great convenience and comfort to users, this also leads to increased complexity and diversity in their testing. This is especially true in recent years, as the need for multi-scenario and multi-vehicle adaptation of intelligent cockpits has deepened this situation. Traditional manual testing methods for intelligent cockpits are clearly unsuitable. The sheer number of test cases, often reaching thousands or tens of thousands, is daunting, resulting in long testing cycles and low efficiency. This is particularly true for tests that require timeliness, durability, and multi-condition parallel combinations, where manual testing may be too costly or even inadequate to cover. With the development of testing technology, automated testing technology has been introduced into intelligent cockpit testing, improving testing efficiency, simplifying manual operations, and freeing up manpower.

[0003] However, most of the existing automated testing systems are customized systems designed for a specific scenario, function, or product. They have poor test adaptability and are often forced to be upgraded or even abandoned as products iterate, resulting in huge waste. Or they cannot adapt to the different testing needs of different stages of the original product, and users often need to use other means to cover them, which further increases the testing cost. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide an intelligent cockpit automated testing system, method, device, processor and its computer-readable storage medium that can provide users with rich and flexible interfaces to adapt to diverse testing scenarios and aircraft models.

[0005] To achieve the above objectives, the intelligent cockpit automated testing system, method, apparatus, processor, and computer-readable storage medium of the present invention are as follows:

[0006] The main features of this intelligent cockpit automated testing system are that the system includes: an industrial control computer, a CAN communication box, a serial communication module, a signal generator, a DIO module, an AIO module, a power amplifier load module, a signal conditioning board, a power supply module, a general switch, a PoE switch, a PoE camera, and host computer testing software.

[0007] The industrial control computer, as the host computer, is used to run the test software, realize communication and control with other peripherals and devices under test to execute the corresponding test process, and present the current test status and the final test results to the user.

[0008] The two ends of the CAN communication box and the serial communication module are respectively connected to the industrial control computer and the smart cockpit under test, so as to realize data exchange and communication control between the industrial control computer and the smart cockpit under test;

[0009] The signal generator, DIO module, and AIO module are controlled by the industrial computer and, together with the power amplifier load module, undergo signal conditioning and transfer processing via the signal conditioning board. They are also connected to the corresponding signal pins of the smart cockpit under test to achieve the supply and acquisition of hard-wired signals.

[0010] The aforementioned ordinary switch is used to build a local area network, enabling communication and interconnection among various network devices in the test system;

[0011] The PoE switch and PoE camera together constitute the image acquisition unit of the test system, used to acquire image information from the smart cockpit screen, and the host computer will automatically determine the recognition result based on the image information; and

[0012] The host computer testing software is used to schedule the corresponding devices in the system to execute the corresponding test process based on the user-defined test case files.

[0013] Preferably, the smart cockpit under test is located outside the system and is used to receive adjustment commands sent by the system to complete corresponding functional tests and configurations, and each of the smart cockpits specifically includes:

[0014] The cockpit controller, connected to the signal conditioning board, is used to enable interactive control between upstream and downstream equipment or systems; and

[0015] The cockpit instrument panel and cockpit IVI are both LCD screens and are connected to the cockpit controller to display vehicle information to the user and respond to user operations.

[0016] Preferably, the power supply module specifically includes: a first programmable DC power supply, a second programmable DC power supply, a programmable high-power power supply, and a DC regulated power supply, wherein,

[0017] The first and second programmable DC power supplies are both connected to a common switch via an Ethernet interface and / or to the industrial control computer via a serial port. Each of the first and second programmable DC power supplies includes two output channels. The output channels are connected to the smart cockpit under test and are used to provide power to the smart cockpit under test. The output channels of the first and second programmable DC power supplies can simultaneously supply power to different functional power interfaces of the same smart cockpit, and can also provide constant power to four smart cockpits at the same time.

[0018] The programmable high-power power supply is connected to the ordinary switch via an Ethernet interface on one end and to the smart cockpit via an output channel on the other end, so as to provide test power to multiple smart cockpits at the same time.

[0019] The output terminal of the DC regulated power supply is connected to the signal conditioning board to supply power to the signal conditioning board.

[0020] Preferably, the PoE camera is a general-purpose PoE network camera, connected to the PoE switch via a network cable. The PoE switch powers the system and uploads the collected image data. The camera model, resolution, and bitrate are not limited and can be freely replaced. The PoE camera is fixed with a bracket, allowing for free adjustment of its shooting position, area, and angle. The testing system supports simultaneous shooting from eight PoE cameras and simultaneous detection of eight regions of interest (ROIs). It is used to directly capture images of the cockpit instruments and cockpit IVI screens for image recognition and video recording. The PoE switch has gigabit bandwidth and is connected to the PoE camera via a network cable. It is then connected to a regular switch via a network cable to communicate with the industrial control computer via Ethernet and upload the image data captured by the PoE camera.

[0021] Preferably, the CAN communication box includes two independently configured CAN channels for CAN bus communication processing.

[0022] The serial communication module is used to realize serial communication between the smart cockpit and the industrial control computer, or the serial communication module is used for communication with other serial devices.

[0023] The signal generator is connected to the industrial control computer and the signal conditioning board respectively, and is used to provide arbitrary waveform signals to the intelligent cockpit. It has four independent channels, two of which are directly output to the outside through the signal conditioning board, and the other two channels are expanded into 16 signals for external output through the 2-to-16 expansion module of the signal conditioning board.

[0024] The DIO module is connected to the industrial control computer and the signal conditioning board respectively. It is used to transfer the received signals to the intelligent cockpit and provide 8 DO, 8 DI and 8 DI / DO signals. The 8 DI / DO signals are directly acquired or output by the signal conditioning board and are compatible with TTL level and CMOS level. The other 8 DO signals output 24V high-level signals by the digital boost module of the signal conditioning board. The other 8 DI signals acquire the externally input 24V high-level signals by the digital buck module of the signal conditioning board.

[0025] The AIO module is connected to both the industrial control computer and the signal conditioning board. It transfers received signals to the intelligent cockpit and provides 64 AI signals and 32 AO signals, all ranging from -10V to +10V. The 32 AI signals and 16 AO signals are directly acquired or output via the signal conditioning board. The 32 AI signals acquire external input voltage signals (-32V to +32V) via the analog buck module of the signal conditioning board, and the 16 AO signals output voltage signals (-32V to +32V) via the analog boost module of the signal conditioning board.

[0026] The power amplifier load module is connected to the signal conditioning board via a cable and is used to simulate the power amplifier equipment in a smart cockpit.

[0027] Preferably, the signal conditioning board is powered by a 24V DC regulated power supply, and its main communication interface is a serial port connected to the industrial control computer for signal processing. The signal conditioning board includes:

[0028] The 2-to-16 expansion module is connected to two channels of the signal generator and is used to expand the signals of the two channels of the signal generator into 16 signals.

[0029] An analog step-down module, connected to the AIO module, is used to step down 32 AI signals from the analog input / output AIO module to acquire analog voltage signals from -32V to +32V.

[0030] An analog boost module, connected to the AIO module, is used to boost 16 AO signals from the analog input / output AIO module to achieve an analog voltage output from -32V to +32V.

[0031] A digital step-down module, connected to the DIO module, is used to step down eight of the DI signals from the digital input / output DIO module to achieve the acquisition of a 24V high-level signal.

[0032] A digital boost module, connected to the DIO module, is used to boost eight of the DO signals from the digital input / output DIO module to achieve a 24V high-level signal output.

[0033] The analog load module consists of eight resistor matrices with different base values ​​combined with a relay matrix. The resistance value is switched by opening and closing the relays within the matrix, providing eight channels of resistance signals with different resistance ranges. The analog load module is connected to the signal conditioning board via pin headers, allowing for flexible replacement of analog load modules with different resistance ranges.

[0034] The relay module is connected to the analog load module, analog boost module, analog buck module, digital boost module, digital buck module, 2-to-16 expansion module, and the smart cockpit under test. It is used to control the opening / closing of each relay through the host computer to adjust the acquired power amplifier load, analog load, AI, AO, DI, DO, and arbitrary waveform signals.

[0035] Preferably, the system integrates several functional instructions through host computer software. Users generate custom test case files based on test case templates, and then import them into the host computer software. The host computer software automatically recognizes the user's test cases, and the main test thread sequentially traverses all test cases and executes the corresponding functions according to the instructions in each test case, thereby realizing the testing of the intelligent cockpit under test.

[0036] Preferably, the host computer software integrates several function instructions, including but not limited to:

[0037] The system includes programmable power supply commands, CAN communication commands, serial communication commands, image processing commands, data acquisition and control commands, script operation commands, human-machine interaction commands, and test process control commands. Users can select or freely combine these commands according to their actual needs to form user-specific test cases.

[0038] The method for automated testing of intelligent cockpits using the aforementioned system is characterized by the following steps:

[0039] (1) The user starts the host computer software and loads the test case file to begin testing;

[0040] (2) The host computer software enters the main thread after the initialization of various devices and parameters is completed;

[0041] (3) The system executes each execution instruction of the current test case in sequence according to the received test cases;

[0042] (4) The system obtains the corresponding test results through the test judgment process of the execution instructions of each test case.

[0043] Preferably, step (4) specifically includes:

[0044] (4.1) Determine whether the execution instruction of the current test case has passed the test. If yes, proceed to step (4.2); otherwise, proceed to step (4.1.1).

[0045] (4.1.1) If the test fails, the host computer software will select whether to continue the test based on the configuration value of the user parameter file. If yes, proceed to step (4.2); otherwise, proceed directly to step (4.5).

[0046] (4.2) Determine whether the current test case has reached the loop count. If yes, proceed to step (4.3); otherwise, return to step (3) for loop processing.

[0047] (4.3) Determine whether the current test case is the last test case. If it is, proceed to step (4.4). Otherwise, update the current test case and return to step (3) for loop processing.

[0048] (4.4) Determine whether all test cases in the current system have reached the loop count. If so, proceed to step (4.5). Otherwise, update the current test case and return to step (3) for loop processing.

[0049] (4.5) Generate a report directly and stop the test.

[0050] Preferably, the method further includes:

[0051] In the process of executing the current test case after entering the main thread, when the execution instruction of the test case includes a command to start a parallel thread, the system will perform parallel thread testing according to the parallel thread command, including but not limited to: stress-based parallel thread testing, functional parallel thread testing, multi-condition parallel combination parallel thread testing, time-sensitive parallel thread testing, and fault import parallel thread testing.

[0052] The main feature of this device for automated testing of intelligent cockpits is that the device includes:

[0053] A processor is configured to execute computer-executable instructions;

[0054] The memory stores one or more computer-executable instructions, which, when executed by the processor, implement the various steps of the method for automated testing of the intelligent cockpit described above.

[0055] The processor for implementing automated testing of intelligent cockpits is characterized in that it is configured to execute computer-executable instructions, which, when executed by the processor, implement the various steps of the aforementioned automated testing method for intelligent cockpits.

[0056] The computer-readable storage medium is characterized in that it stores a computer program that can be executed by a processor to implement the various steps of the method for automated testing of the intelligent cockpit described above.

[0057] The intelligent cockpit automated testing system, method, apparatus, processor, and computer-readable storage medium of this invention provide a rich variety of hardware signal types and interfaces, supporting automatic detection of various types of intelligent cockpits and simultaneous detection of multiple intelligent cockpits. It also offers flexible and diverse instruction sets and freely editable test cases, greatly satisfying various specialized and customized testing needs of users. It is adaptable to various testing scenarios such as stress testing, functional testing, multi-condition parallel combination testing, timeliness testing, and fault import testing, exhibiting high versatility and adaptability. This reduces the problem of unusable automated testing equipment due to product iterations, demonstrating significant practical value. Attached Figure Description

[0058] Figure 1 This is a schematic diagram of the framework structure of the intelligent cockpit automated testing system of the present invention.

[0059] Figure 2 This is a schematic diagram of the software instruction set of the intelligent cockpit automated testing system of the present invention.

[0060] Figure 3 This is a flowchart illustrating the method for automated testing of an intelligent cockpit according to the present invention.

[0061] Figure 4 This is a flowchart illustrating the parallel stress testing performed for this invention.

[0062] Figure 5 This is a flowchart illustrating the functional parallel testing process for this invention.

[0063] Figure 6 This is a flowchart illustrating the parallel testing of multi-condition parallel combination classes in this invention.

[0064] Figure 7 This is a flowchart of the time-sensitive parallel testing for this invention.

[0065] Figure 8 This is a flowchart of the parallel testing of the fault import class for this invention. Detailed Implementation

[0066] To more clearly describe the technical content of the present invention, the following description is provided in conjunction with specific embodiments.

[0067] Before describing the embodiments of the present invention in detail, it should be noted that, in the following, the terms “comprising,” “including,” or any other variations are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0068] Before detailing this technical solution, the English abbreviations of some of the technical features used in this application are explained as follows:

[0069] ●IVI: Message-Digest Algorithm in-vehicle infotainment system;

[0070] ●AIO: Analog Input / Output;

[0071] ●DIO: Digital Input / Output;

[0072] ●POE: Power Over Ethernet;

[0073] ●ROI: Region of interest;

[0074] ●CAN: Controller Area Network;

[0075] ●USB: Universal Serial Bus;

[0076] ●TTL: Transistor - Transistor Logic gate circuit;

[0077] ●CMOS: Complementary Metal Oxide Semiconductor.

[0078] Please see Figure 1 As shown, the intelligent cockpit automated testing system includes: an industrial control computer, a CAN communication box, a serial communication module, a signal generator, a DIO module, an AIO module, a power amplifier load module, a signal conditioning board, a power supply module, a general-purpose switch, a PoE switch, a PoE camera, and host computer testing software.

[0079] The industrial control computer, as the host computer, is used to run the test software, realize communication and control with other peripherals and devices under test to execute the corresponding test process, and present the current test status and the final test results to the user.

[0080] The two ends of the CAN communication box and the serial communication module are respectively connected to the industrial control computer and the smart cockpit under test, so as to realize data exchange and communication control between the industrial control computer and the smart cockpit under test;

[0081] The signal generator, DIO module, and AIO module are controlled by the industrial computer and, together with the power amplifier load module, undergo signal conditioning and transfer processing via the signal conditioning board. They are also connected to the corresponding signal pins of the smart cockpit under test to achieve the supply and acquisition of hard-wired signals.

[0082] The aforementioned ordinary switch is used to build a local area network, enabling communication and interconnection among various network devices in the test system;

[0083] The PoE switch and PoE camera together constitute the image acquisition unit of the test system, used to acquire image information from the smart cockpit screen, and the host computer will automatically determine the recognition result based on the image information; and

[0084] The host computer testing software is used to schedule the corresponding devices in the system to execute the corresponding test process based on the user-defined test case files.

[0085] In a preferred embodiment of the present invention, the smart cockpit under test is located outside the system and is used to receive adjustment commands sent by the system to complete corresponding functional tests and configurations. Each of the smart cockpits specifically includes:

[0086] The cockpit controller, connected to the signal conditioning board, is used to enable interactive control between upstream and downstream equipment or systems; and

[0087] The cockpit instrument panel and cockpit IVI are both LCD screens and are connected to the cockpit controller to display vehicle information to the user and respond to user operations.

[0088] In a preferred embodiment of the present invention, the power supply module specifically includes: a first programmable DC power supply, a second programmable DC power supply, a programmable high-power power supply, and a DC regulated power supply, wherein...

[0089] The first and second programmable DC power supplies are both connected to a common switch via an Ethernet interface and / or to the industrial control computer via a serial port. Each of the first and second programmable DC power supplies includes two output channels. The output channels are connected to the smart cockpit under test and are used to provide power to the smart cockpit under test. The output channels of the first and second programmable DC power supplies can simultaneously supply power to different functional power interfaces of the same smart cockpit, and can also provide constant power to four smart cockpits at the same time.

[0090] The programmable high-power power supply is connected to the ordinary switch via an Ethernet interface on one end and to the smart cockpit via an output channel on the other end, so as to provide test power to multiple smart cockpits at the same time.

[0091] The output terminal of the DC regulated power supply is connected to the signal conditioning board to supply power to the signal conditioning board.

[0092] In a preferred embodiment of the present invention, the PoE camera is a general-purpose PoE network camera, connected to the PoE switch via a network cable. The PoE switch powers the camera and uploads the collected image data. The camera model, resolution, and bitrate are not limited and can be freely replaced. The PoE camera is fixed with a bracket, allowing for free adjustment of its shooting position, area, and angle. The testing system supports simultaneous shooting from eight PoE cameras and simultaneous detection of eight regions of interest (ROIs). It is used to directly capture images of the smart cockpit's instruments and IVI screens to achieve image recognition and video recording. The PoE switch has gigabit bandwidth and is connected to the PoE camera via a network cable. It is then connected to a regular switch via a network cable to communicate with the industrial control computer via Ethernet and upload the image data captured by the PoE camera.

[0093] In a preferred embodiment of the present invention, the CAN communication box includes two independently configured CAN channels for CAN bus communication processing.

[0094] The serial communication module is used to realize serial communication between the smart cockpit and the industrial control computer, or the serial communication module is used for communication with other serial devices.

[0095] The signal generator is connected to the industrial control computer and the signal conditioning board respectively, and is used to provide arbitrary waveform signals to the intelligent cockpit. It has four independent channels, two of which are directly output to the outside through the signal conditioning board, and the other two channels are expanded into 16 signals for external output through the 2-to-16 expansion module of the signal conditioning board.

[0096] The DIO module is connected to the industrial control computer and the signal conditioning board respectively. It is used to transfer the received signals to the intelligent cockpit and provide 8 DO, 8 DI and 8 DI / DO signals. The 8 DI / DO signals are directly acquired or output by the signal conditioning board and are compatible with TTL level and CMOS level. The other 8 DO signals output 24V high-level signals by the digital boost module of the signal conditioning board. The other 8 DI signals acquire the externally input 24V high-level signals by the digital buck module of the signal conditioning board.

[0097] The AIO module is connected to both the industrial control computer and the signal conditioning board, and is used to transfer the received signals to the intelligent cockpit. It provides 64 AI signals and 32 AO signals. The 32 AI signals and 16 AO signals are directly acquired or output via the signal conditioning board, with a signal range of -10V to +10V. The 32 AI signals acquire external input voltage signals (-32V to +32V) via the analog buck module of the signal conditioning board, and the 16 AO signals output voltage signals (-32V to +32V) via the analog boost module of the signal conditioning board.

[0098] The power amplifier load module is connected to the signal conditioning board via a cable and is used to simulate the power amplifier equipment in a smart cockpit.

[0099] In a preferred embodiment of the present invention, the signal conditioning board is powered by a 24V DC regulated power supply, and the main communication interface is a serial port connected to the industrial control computer for signal processing. The signal conditioning board includes:

[0100] The 2-to-16 expansion module is connected to two channels of the signal generator to expand the signals of the two channels of the signal generator into 16 signals.

[0101] An analog step-down module, connected to the AIO module, is used to step down 32 AI signals from the AIO module to acquire analog voltage signals from -32V to +32V.

[0102] An analog boost module, connected to the AIO module, is used to boost 16 of the AO signals from the AIO module to achieve an analog voltage output from -32V to +32V.

[0103] A digital step-down module, connected to the DIO module, is used to step down eight of the DI signals from the DIO module to achieve the acquisition of a 24V high-level signal.

[0104] A digital boost module, connected to the DIO module, is used to boost eight of the DO signals of the DIO module to achieve a 24V high-level signal output.

[0105] The analog load module consists of eight resistor matrices with different base values ​​combined with a relay matrix. The resistance value is switched by opening and closing the relays within the matrix, providing eight channels of resistance signals with different resistance ranges. The analog load module is connected to the signal conditioning board via pin headers, allowing for flexible replacement of analog load modules with different resistance ranges.

[0106] The relay module is connected to the analog load module, boost module, buck module, 2-to-16 expansion module, and smart cockpit. It is used to control the opening / closing of each relay through the host computer to adjust the acquired power amplifier load, analog load, AI, AO, DI, DO, and arbitrary waveform signals.

[0107] In practical applications, the hardware framework structure diagram of this intelligent cockpit automated testing system is shown below. Figure 1As shown, the intelligent cockpit is the device under test (DUT), mainly composed of three parts: cockpit controller, cockpit instrument panel, and cockpit IVI. The cockpit controller is the core of the intelligent cockpit, used to realize the interactive control of upstream and downstream equipment or systems, such as bus communication, data acquisition, information feedback, and output control. The cockpit instrument panel and cockpit IVI are used for human-machine interaction, usually two LCD screens, to display vehicle information to the user and respond to user operations. The number of intelligent cockpits under test is unlimited, as long as the resources used are sufficient and there are no conflicts. The industrial control computer acts as the host computer, used to run the test software, realize communication and control with other peripherals and DUTs to execute the test process, and record the corresponding data. The system displays test data, presenting the current test status and final test results to the user; ordinary switches are used to establish local area networks (LANs) to enable communication and interconnection of Ethernet devices within the LAN, such as industrial control computers, programmable power supplies, and PoE switches; PoE switches are used by industrial control computers to acquire image data from various PoE cameras for image recognition, video recording, and other processing; PoE cameras are general network cameras used to directly capture images of cockpit instruments and cockpit IVI screens, supporting up to 8 simultaneous captures and up to 8 ROIs for simultaneous detection; programmable DC power supplies 1 and 2 are connected to the switch via Ethernet interfaces by default, and can also support... Each device has a serial port for connecting to an industrial control computer, and each has two output channels, for a total of four output channels. The output terminals connect to the smart cockpit under test (DUT) for power supply. Each of the four channels can be used independently, supplying power to the "Constant Power," "ACC," and "ON" power interfaces of the same smart cockpit, or providing "Constant Power" to four different smart cockpits. A programmable high-power power supply with an Ethernet interface connects to a switch on one end and the smart cockpit under test on the other, with one output channel for simultaneous power supply to multiple smart cockpits during testing. A CAN communication box connects to both the industrial control computer and the smart cockpit on both ends for CAN bus communication. It includes two independent CAN channels; the serial communication module is used to realize serial communication between the industrial control computer and the intelligent cockpit, such as the host computer reading information reported by the intelligent cockpit or sending serial commands to the intelligent cockpit. One channel can also be used for communication with other serial devices; one end of the signal generator is connected to the industrial control computer for communication control, and the other end is connected to the signal conditioning board to transfer the signal to the intelligent cockpit, which is used to provide arbitrary waveform signals to the intelligent cockpit. The signal generator contains four output channels, two of which are expanded into 16 signals through the 2-to-16 expansion module in the signal conditioning board, which can provide a total of 18 arbitrary waveform signals at the same time;The DIO module is a digital input / output module. One end connects to an industrial control computer for communication, and the other end connects to a signal conditioning board to transfer signals to the smart cockpit. It can provide 8 DO, 8 DI, and 8 DI / DO signals. The 8 DI / DO signals are directly acquired or output via the signal conditioning board, compatible with TTL and CMOS levels. The other 8 DO signals output a 24V high-level signal via the digital boost module of the signal conditioning board, and the other 8 DI signals acquire an externally input 24V high-level signal via the digital buck module of the signal conditioning board. The AIO module is an analog input / output module. One end connects to an industrial control computer for communication, and the other end connects to a signal conditioning board to transfer signals to the smart cockpit. It can provide 64 AI channels and 32 analog input / output channels. The AO signal consists of 32 AI channels and 16 AO channels directly acquired or output via the signal conditioning board, with a signal range of -10V to +10V. The other 32 AI channels acquire external input voltage signals (-32V to +32V) via the analog buck module of the signal conditioning board, while the other 16 AO channels output voltage signals (-32V to +32V) via the analog boost module of the signal conditioning board. The power amplifier load module is located outside the signal conditioning board and is used to simulate the power amplifier equipment of the smart cockpit, such as speakers. Its standard parameters are 4Ω / 25W, which can be adjusted as needed. It connects to the signal conditioning board via cables and then to the smart cockpit under test via the relay module of the signal conditioning board. There are 8 channels in total, and the relay parameters used here are 24V / 16A. Signal conditioning... The board is used for signal conditioning and conversion in the system. It is powered by a 24V power supply and its main communication interface is a serial port, connecting to an industrial control computer. All signals are connected to the smart cockpit under test via relay modules on the board. Each relay corresponds to a power amplifier load, analog load, AI, AO, DI, DO, and arbitrary waveform signal. The host computer controls the relays on the signal conditioning board to close or open, thus controlling the input and output of each signal. An additional 24 relays provide switching signals. A step-down module reduces the voltage of the 32 analog voltage signals input from the relay modules before connecting them to the AIO module for acquisition. A boost module boosts the voltage of the 16 analog voltage signals output from the AIO module before supplying them to the smart cockpit under test via the relay modules. (2-to-1 switching...) The 6 expansion modules are used to expand the two arbitrary waveform signals from the signal generator into 16 channels, which are then supplied to the smart cockpit under test via relay modules. The analog load modules consist of eight sets of resistor matrices with different base values ​​combined with relay matrices. The resistance values ​​are switched by opening and closing the relays within the relay matrix, providing eight resistance signals with different resistance ranges. Six of these channels have a resistance range of 1 to 65535Ω, with an adjustment step of 1Ω, while the remaining two channels have a resistance range of 100 to 6553500Ω, with an adjustment step of 100Ω. The analog load modules are connected to the signal conditioning board via pin headers, allowing for flexible replacement of analog load modules with different resistance ranges. The DC regulated power supply provides +24V DC voltage to the signal conditioning board and is directly connected to the signal conditioning board interface.

[0108] Please see Figure 2 As shown, in a preferred embodiment of the present invention, the host computer software integrates several functional instructions, including but not limited to:

[0109] The system includes programmable power supply commands, CAN communication commands, serial communication commands, image processing commands, data acquisition and control commands, script operation commands, human-machine interaction commands, and test process control commands. Users can select or freely combine these commands according to their actual needs to form user-specific test cases.

[0110] In practical applications, the host computer software integrates a large number of instructions for communication control and data acquisition. Users generate custom test case files based on test case templates, and then import these files into the host computer software. The software automatically recognizes the user's test cases, and the main test thread iterates through all test cases sequentially, executing corresponding actions according to the instructions in each test case. Up to 24 parallel threads are started or stopped according to the main thread's instructions, allowing for simultaneous execution of other operations while the main thread is executing a specific instruction. This increases the adaptability of the test scenario and enables the testing of the intelligent cockpit under test. The host computer software instruction set is as follows: Figure 2 As shown, the system mainly consists of several categories: programmable power supply commands, CAN communication commands, serial communication commands, image processing commands, data acquisition and control commands, script operation commands, human-machine interaction commands, and test process control commands. Each category contains several or dozens of direct operation commands, which users can select and combine freely to form user-specific test cases. In addition, the host computer software provides various auxiliary functions, including but not limited to parameter file configuration, process data recording, one-click cleanup of past data, and anomaly reporting. The parameter file configuration function records and transmits relevant parameters, such as the number of test case executions, image recognition network flow path, programmable power supply resource number, and whether process data recording is enabled. The process data recording function automatically records data such as CAN message data, programmable power supply voltage and current data, AIO and DIO acquisition data, image recognition image data, and saved video data, based on user selection. The one-click cleanup of past data helps users easily clean up unnecessary test data files. The anomaly reporting function automatically alerts the user to the location of the anomaly, the cause of the problem, and related data when an anomaly occurs during testing.

[0111] Please see Figure 3 As shown, the method for automating intelligent cockpit testing using the aforementioned system includes the following steps:

[0112] (1) The user starts the host computer software and loads the test case file to begin testing;

[0113] (2) The host computer software enters the main thread after the initialization of various devices and parameters is completed;

[0114] (3) The system executes each execution instruction of the current test case in sequence according to the received test cases;

[0115] (4) The system obtains the corresponding test results through the test judgment process of the execution instructions of each test case.

[0116] In a preferred embodiment of the present invention, step (4) specifically includes:

[0117] (4.1) Determine whether the execution instruction of the current test case has passed the test. If yes, proceed to step (4.2); otherwise, proceed to step (4.1.1).

[0118] (4.1.1) If the test fails, the host computer software will select whether to continue the test based on the configuration value of the user parameter file. If yes, proceed to step (4.2); otherwise, proceed directly to step (4.5).

[0119] (4.2) Determine whether the current test case has reached the loop count. If yes, proceed to step (4.3); otherwise, return to step (3) for loop processing.

[0120] (4.3) Determine whether the current test case is the last test case. If it is, proceed to step (4.4). Otherwise, update the current test case and return to step (3) for loop processing.

[0121] (4.4) Determine whether all test cases in the current system have reached the loop count. If so, proceed to step (4.5). Otherwise, update the current test case and return to step (3) for loop processing.

[0122] (4.5) Generate a report directly and stop the test.

[0123] In a preferred embodiment of the present invention, the method further includes:

[0124] In the process of executing the current test case after entering the main thread, when the execution instruction of the test case includes a command to start a parallel thread, the system will perform parallel thread testing according to the parallel thread command, including but not limited to: stress-based parallel thread testing, functional parallel thread testing, multi-condition parallel combination parallel thread testing, time-sensitive parallel thread testing, and fault import parallel thread testing.

[0125] In practical applications, the method for automated testing of intelligent cockpits using the aforementioned system, as described in this invention, involves the user loading a pre-edited test case file into the host computer software after startup. The software automatically identifies and displays the test cases to be tested. Upon clicking "Start Test," the software automatically initializes various devices and parameters. After completion, it enters the main thread and automatically executes each instruction of the current test case sequentially. Routine tests include setting the programmable power supply voltage, timing the intelligent cockpit to send CAN messages, collecting hard-wired signal data from the intelligent cockpit, and acquiring PoE camera images. The software automatically determines whether the collected data and images meet expectations and updates the test results for that test case. If the test passes, it automatically proceeds to the next test case. If the test fails, the software selects whether to continue testing based on the configuration values ​​in the user parameter file. If yes, it proceeds to the next test case; otherwise, it generates a report and stops the test. After each test case is executed, the software checks whether it is the last one. If not, it proceeds to the next test case; otherwise, it generates a report and stops the test.

[0126] To further illustrate the multi-scenario adaptability of this automated testing system in this case, we will now combine... Figures 4 to 8 The following embodiments are further illustrated:

[0127] Please see Figure 4 As shown in the flowchart of the parallel stress test of the present invention, as a specific embodiment of the present invention, the specific operation process is as follows: During stress tests, such as cockpit instrument panel and cockpit IVI screen flickering / black screen tests, CAN messages are synchronously sent to simulate the real vehicle environment during the stress test, according to... Figure 1 After setting up the hardware environment according to the hardware structure diagram, place the smart cockpit to be tested, point the PoE camera at the cockpit instruments and cockpit IVI screen, update the image ROI coordinate parameters in the parameter file based on the camera images, edit the test case file, open the software, load the test case file, and click "Start Test" to enter the test process. Figure 4 As shown, after entering the test process, the corresponding instructions are executed sequentially, that is, the power supply voltage is continuously changed to repeatedly power on and off the intelligent cockpit. After the intelligent cockpit is powered on, the host computer software obtains the image from the POE network camera via Ethernet for image recognition. After recognizing the normal power-on pattern on the two LCD screens of the cockpit instrument panel and the cockpit IVI, it indicates that the power-on is normal and there is no screen distortion or black screen. The next round of testing is automatically entered. Parallel thread 1 is started by the main thread instruction. During the power-on and power-off process of the intelligent cockpit, CAN messages are continuously sent to it in parallel to simulate the real vehicle message environment until the set number of loops is reached or the test fails. If the total number of test case executions is set to -1, the test cases will be executed in a loop, that is, the long-term stress test mode is entered. If the test fails, it can be set to stop immediately upon failure and preserve the scene for product problem analysis.

[0128] Please see Figure 5 As shown in the figure, as a specific embodiment of the present invention, its specific operation flow is as shown in the flowchart of the functional parallel testing of the present invention. Specifically, general functional tests, such as the cockpit instrument left turn signal message test, are performed according to... Figure 1 After setting up the hardware environment according to the hardware structure diagram, place the smart cockpit to be tested, point the PoE camera at the cockpit instrument screen, update the image ROI coordinate parameters in the parameter file based on the camera image, edit the test case file, open the software, load the test case file, and click "Start Test" to enter the test process. Figure 5 As shown, after entering the test process, the corresponding instructions are executed in sequence, that is, the left turn light on and left turn light off messages are sent in sequence. The host computer software acquires the images from the POE camera in the two cases respectively for recognition. If the recognition is abnormal, the software automatically generates a report and stops the test.

[0129] Please see Figure 6 As shown in the figure, as a specific embodiment of the present invention, its specific operation flow is as shown in the flowchart of the parallel test of the multi-condition parallel combination class of the present invention. Specifically, the multi-condition parallel combination class test, such as the full message test of the intelligent cockpit, checks whether the intelligent cockpit works normally under the normal message environment and whether there are phenomena such as screen distortion. When the intelligent cockpit is working normally, it will receive various fixed-period and random-period messages reported by various devices on the CAN bus. This test system can send various fixed-period and random-period messages to the intelligent cockpit in parallel through the CAN communication box, according to Figure 1 After setting up the hardware environment according to the hardware structure diagram, place the smart cockpit to be tested, point the PoE camera at the cockpit instrument screen, update the image ROI coordinate parameters in the parameter file based on the camera image, edit the test case file, open the software, load the test case file, and click "Start Test" to enter the test process. Figure 6 As shown, after entering the test process, the corresponding instructions are executed in sequence. The main thread continuously detects the image data of the cockpit instruments and cockpit IVI transmitted by the POE camera. Each parallel thread sends messages with fixed and irregular periods according to its own instructions. Once an image abnormality is detected, the test stops.

[0130] Please see Figure 7 As shown in the flowchart of the parallel time-sensitive test of the present invention, the specific operation process is as follows: Time-sensitive tests, such as the ambient temperature data reporting time test, measure the time from the change in the temperature sensor signal to the reporting of temperature data via a CAN message. The temperature sensor signal is replaced by an analog load. Figure 1 After setting up the hardware environment using the hardware structure diagram, editing the test case file, opening the software, loading the test case file, and clicking "Start Test" will initiate the test process. Figure 7As shown, after entering the test process, the corresponding instructions are executed in sequence. The system continuously changes the simulated load resistance value and records the change time s1. Then, the CAN message information of the corresponding temperature is checked to obtain the CAN message reporting time s2. s2-s1 is the ambient temperature data reporting time for this test. To ensure that the test time is stable and reliable, the average value of multiple measurements is the ambient temperature data reporting time to be obtained.

[0131] Please see Figure 8 As shown in the flowchart of the parallel test for fault introduction, as a specific embodiment of the present invention, the specific operation process is as follows: For fault introduction tests, such as parking circuit low and high air pressure fault tests, the parking circuit air pressure signal is provided by an AIO module using an analog voltage excitation signal, according to... Figure 1 After setting up the hardware environment using the hardware structure diagram, editing the test case file, opening the software, loading the test case file, and clicking "Start Test" will initiate the test process. Figure 8 As shown, after entering the test process, the corresponding instructions are executed in sequence. First, the air pressure signal is set within the normal threshold range to check for air pressure fault messages. Then, the air pressure signal is set to a voltage value lower than the minimum threshold to check for low air pressure fault messages. Finally, the air pressure signal is set to a voltage value higher than the maximum threshold to check for high air pressure fault messages. This will determine whether the air pressure fault in the vehicle circuit is reported correctly.

[0132] In practical applications, this technical solution, based on both hardware and software architecture, provides the system with high versatility and adaptability. Users can flexibly create specialized and customized test cases according to their own testing needs, supporting various testing requirements under different stages and scenarios of the intelligent cockpit, including but not limited to functional testing, fault testing, stress testing, multi-condition parallel combination testing, timeliness testing, and single-unit independent or multi-unit simultaneous testing, without being limited to a certain scenario or model. Specifically, this system architecture has the following technical advantages:

[0133] (1) The system hardware architecture provides a rich variety of hardware signal types and interfaces, including 5 channel control power signals, 8 channels of low-voltage DI / DO signals, 8 channels of high-voltage 24V DO signals, 8 channels of high-voltage 24VDI signals, 32 channels of low-voltage AI signals, 32 channels of high-voltage AI signals, 16 channels of low-voltage AO signals, 16 channels of high-voltage AO signals, 8 channels of analog resistor signals, 8 channels of power load signals, 24 channels of independent switch signals, 18 channels of arbitrary waveform signals, 1 channel of serial bus signal, 2 channels of CAN bus signal, and 8 channels of image acquisition signals, which are sufficient to adapt to various types of intelligent cockpit devices and support individual detection of a single intelligent cockpit and joint detection of multiple intelligent cockpits, specifically including:

[0134] a) Among them, the 5-way controllable power signal includes 4 channels of 60V / 10A conventional power signal and 1 channel of 66V / 110A high-power power signal, all of which can be used independently. For example, it can supply power to the "constant power", "ACC" and "ON" power interfaces of the same smart cockpit to perform power-on and power-off tests on any power interface. It can also supply power to multiple smart cockpits at the same time. Assuming that the full power supply of a smart cockpit is 24V / 3A, it can supply power to at least 36 smart cockpits at the same time. When used for batch testing of smart cockpits, it can greatly improve the testing efficiency.

[0135] b) Among them, there are 8 low-voltage DI / DO signals and 8 high-voltage 24V signals. The DIO signal, 8-channel high-voltage 24VDI signal, 32-channel low-voltage AI signal, 32-channel high-voltage AI signal, 16-channel low-voltage AO signal, and 16-channel high-voltage AO signal are provided by the DIO module, AIO module, and signal conditioning board. It has both signal acquisition and signal excitation, and both digital and analog signals, covering low-voltage signals (-10V to +10V) and high-voltage signals (-32V to +32V). It can provide various high-level, low-level, high-edge, low-edge, high-voltage, low-voltage, pulse, PWM wave, and other signals. The types and quantities of signals are sufficient to meet the testing of all hard-wired signal interfaces of at least one smart cockpit device. The DIO module, AIO module, and signal conditioning board communicate with the host computer via USB port to realize signal acquisition or excitation. At the same time, if multiple smart cockpits are tested at the same time and the existing number of signal channels is insufficient, the modules can be added directly. The host computer software supports the identification and control of multiple peripheral modules of the same type. Only simple configuration is required before testing according to the specific module resources of the actual hard-wired signal connection, which has a certain degree of scalability.

[0136] c) Eight of the analog resistance signals are located on the signal conditioning board and are composed of resistor matrices with different base values ​​combined with relay matrices. They are used to simulate the general resistive loads of the smart cockpit, such as temperature sensors. The host computer software controls the opening and closing of the relay matrix to switch the different resistance values ​​of each channel. Six of the resistances have a range of 0 to 65535Ω with an adjustment step of 1Ω, and the remaining two resistances have a range of 0 to 6553500Ω with an adjustment step of 100Ω. The wide resistance range is sufficient to simulate various resistive signals of the smart cockpit. Combined with the relays, it can also support short circuit and open circuit simulation.

[0137] d) Among them, 8 power amplifier load signals are independent modules used to simulate intelligent cockpit power amplifier equipment, such as speakers. The standard parameters are 4Ω / 25W, 4Ω / 50W, and 4Ω / 100W. They can be adapted according to the actual situation. If they are still not suitable, they can be replaced with other compatible power loads.

[0138] e) The 24 switch signals are provided by the relay module on the signal conditioning board. The opening and closing control of the corresponding relays is realized by the host computer software through serial port commands, thereby providing physical switch signals to the smart cockpit.

[0139] f) The 18 channels of arbitrary waveform signals are provided by the signal generator and the signal conditioning board. The signal generator has 4 channels. Two channels are directly supplied to the smart cockpit via the relay module of the signal conditioning board. The other two channels are expanded into 16 signals via the 2-to-16 expansion module on the signal conditioning board and supplied to the smart cockpit. The host computer controls the signal generator via USB bus and controls the 2-to-16 expansion module and the relay module on the signal conditioning board via serial bus. Together, they realize the output control of arbitrary waveform signals. The signal generator can be replaced according to the actual situation. The conventional signal generator is a signal generator with a maximum output frequency of 100MHz.

[0140] g) One of the serial bus signals is generally used to communicate with the intelligent cockpit debugging serial port to send data commands and monitor and report information. The baud rate is configurable and can also be used to connect other serial communication devices. The host computer software supports the content to be sent, which can be configured arbitrarily by the user.

[0141] h) Two CAN bus signals are provided by the CAN communication box. The two CAN channels are independent of each other. Combined with the host computer software, they can both realize intelligent cockpit calibration and general CAN communication. The CAN communication frame ID and frame data can be configured by the user. The host computer software automatically recognizes the user configuration information according to the user test case file to realize CAN message transmission and reception. It can also support database files. The CAN message signal name recognized by the host computer software is compared with the signal name in the database file. If the comparison is consistent, the message transmission and reception can be realized according to the signal definition in the database file, which can more conveniently realize the custom transmission and reception of CAN messages.

[0142] i) Eight of the image acquisition signals are acquired by eight PoE cameras, which can realize functions such as image recognition, image saving and video recording. The PoE cameras are general network cameras that are powered by a PoE switch and communicate with the host computer. The PoE cameras themselves can be fixed with simple brackets, which is convenient to set up and adjust the position. The cost is low. The number of cameras can be increased or decreased according to the actual situation. There are no restrictions on the camera model. As long as the resolution and bit rate meet the requirements, one camera is generally sufficient for one smart cockpit.

[0143] j) All AIO, DIO, analog load, power amplifier load, arbitrary waveform and other signals in the signal conditioning board are connected to the outside through a relay. The host computer software controls the opening and closing of the corresponding relay on the signal conditioning board through the serial port to realize the on and off combination of arbitrary signals, so as to simulate the intelligent cockpit detection under arbitrary combination conditions.

[0144] k) The system hardware framework has a certain degree of fault tolerance and scalability. Each hardware module is independent and has abundant resources. Even if a hardware module is damaged, it will not affect the use of other modules. If a certain signal is abnormal, it can be replaced with another similar signal channel in the user test case, which is convenient and efficient. At the same time, each hardware module can be added or removed as needed. Similarly, by combining with the host computer software, the resource name or channel name in the user test case can be changed.

[0145] (2) Compared with previous automated testing systems, where test cases and test processes are fixed after the system design is completed, users can only execute tests according to the existing test cases and processes, resulting in poor autonomy and flexibility. Once the test requirements change, such as changes in the test process logic, the system cannot cover the changes and needs to update the corresponding software functions, which brings huge cost burden. The software architecture of this system provides a rich set of instructions and flexible software interfaces, including several categories such as programmable power supply instructions, CAN communication instructions, serial communication instructions, image processing instructions, data acquisition and control instructions, script operation instructions, human-computer interaction instructions, and test process control instructions. The test case file is composed of these instructions. The test case file is edited and generated by the user. The test cases and processes are completely defined and written by the user, giving the user a great degree of freedom. The host computer software can realize the detection of the corresponding function by executing the instructions in sequence according to the user's test case file.

[0146] The apparatus for automating testing of intelligent cockpits includes:

[0147] A processor is configured to execute computer-executable instructions;

[0148] The memory stores one or more computer-executable instructions, which, when executed by the processor, implement the various steps of the method for automated testing of the intelligent cockpit described above.

[0149] The processor for implementing automated testing of intelligent cockpits is configured to execute computer-executable instructions, which, when executed by the processor, implement the various steps of the aforementioned automated testing method for intelligent cockpits.

[0150] The computer-readable storage medium contains a computer program that can be executed by a processor to implement the various steps of the method for automated testing of the intelligent cockpit described above.

[0151] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing a particular logical function or process, and the scope of the preferred embodiments of the invention includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as will be understood by those skilled in the art to which embodiments of the invention pertain.

[0152] It should be understood that various parts of the present invention can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution device.

[0153] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0154] The storage media mentioned above can be read-only memory, disk, or optical disk, etc.

[0155] In the description of this specification, references to terms such as "an embodiment," "some embodiments," "example," "specific example," or "embodiment," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0156] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

[0157] The intelligent cockpit automated testing system, method, apparatus, processor, and computer-readable storage medium of this invention provide a rich variety of hardware signal types and interfaces, sufficient to adapt to the individual and joint testing of various types and multiple intelligent cockpit devices. It also provides a flexible and diverse instruction set and freely editable test cases, greatly satisfying various specialized and customized testing needs of users. It can adapt to various testing scenarios such as stress testing, functional testing, multi-condition parallel combination testing, timeliness testing, and fault import testing, exhibiting high versatility and adaptability. It reduces the problem of unusable automated testing equipment due to product iterations, and has significant practical value.

[0158] In this specification, the invention has been described with reference to specific embodiments thereof. However, it will be apparent that various modifications and variations can be made without departing from the spirit and scope of the invention. Therefore, the specification and drawings should be considered illustrative rather than restrictive.

Claims

1. An automated testing system for an intelligent cockpit, characterized in that, The system includes: an industrial control computer, a CAN communication box, a serial communication module, a signal generator, a DIO module, an AIO module, a power amplifier load module, a signal conditioning board, a power supply module, a general switch, a PoE switch, a PoE camera, and host computer testing software. The industrial control computer, as the host computer, is used to run the test software, realize communication and control with other peripherals and devices under test to execute the corresponding test process, and present the current test status and the final test results to the user. The two ends of the CAN communication box and the serial communication module are respectively connected to the industrial control computer and the smart cockpit under test, so as to realize data exchange and communication control between the industrial control computer and the smart cockpit under test; The intelligent cockpit under test is located outside the system and includes: The cockpit controller is connected to the signal conditioning board. The cockpit instruments and cockpit IVI are both LCD screens and are connected to the cockpit controller. The signal conditioning board is powered by a 24V DC regulated power supply. The main communication interface is a serial port and is connected to the industrial control computer for signal processing. The signal conditioning board includes a 2-to-16 expansion module, which is connected to two channels of the signal generator. A simulated step-down module is connected to the AIO module. An analog boost module is connected to the AIO module. A digital step-down module is connected to the aforementioned DIO module; A digital boost module is connected to the aforementioned DIO module; The simulated load module consists of 8 sets of resistor matrices with different base values ​​combined with relay matrices, and the resistance value is switched by opening and closing each relay in the relay matrix. The relay module is connected to the analog load module, analog boost module, analog buck module, digital boost module, digital buck module, 2-to-16 expansion module, and the smart cockpit under test. The signal generator, DIO module, and AIO module are controlled by the industrial computer and, together with the power amplifier load module, undergo signal conditioning and transfer processing via the signal conditioning board. They are also connected to the corresponding signal pins of the smart cockpit under test to achieve the supply and acquisition of hard-wired signals. The aforementioned ordinary switch is used to build a local area network, enabling communication and interconnection among various network devices in the test system; The PoE switch and PoE camera together constitute the image acquisition unit of the test system, used to acquire image information from the smart cockpit screen. The host computer will automatically determine the recognition result based on the image information. The PoE camera is a general-purpose PoE network camera, connected to the PoE switch via a network cable. It is powered by the PoE switch and uploads the acquired image data. The camera model, resolution, and bitrate are not limited and can be freely replaced. The PoE camera is fixed by a bracket, and the shooting position, area, and angle of the PoE camera can be freely adjusted. The test system supports simultaneous shooting by 8 PoE cameras and simultaneous detection of 8 regions of interest (ROIs). It is used to directly capture the screen images of the smart cockpit's instruments and IVI to achieve image recognition and video recording. The PoE switch has a gigabit bandwidth and is connected to the PoE camera via a network cable. It is then connected to a regular switch via another network cable to communicate with the industrial control computer via Ethernet, uploading image data captured by the PoE camera. The host computer testing software is used to schedule the corresponding devices in the system to execute the corresponding test process based on the user-defined test case files.

2. The intelligent cockpit automated testing system according to claim 1, characterized in that, The intelligent cockpit under test is used to receive adjustment commands sent by the system to complete corresponding functional tests and configurations; the cockpit controller is used to realize interactive control between upstream and downstream equipment or systems; the cockpit instrument panel and cockpit IVI are used to display vehicle information to the user and respond to user operations.

3. The intelligent cockpit automated testing system according to claim 1, characterized in that, The power supply module specifically includes: a first programmable DC power supply, a second programmable DC power supply, a programmable high-power power supply, and a DC regulated power supply, wherein... The first and second programmable DC power supplies are both connected to a common switch via an Ethernet interface and / or to the industrial control computer via a serial port. Each of the first and second programmable DC power supplies includes two output channels. The output channels are connected to the smart cockpit under test and are used to provide power to the smart cockpit under test. The output channels of the first and second programmable DC power supplies can simultaneously supply power to different functional power interfaces of the same smart cockpit, and can also provide constant power to four smart cockpits at the same time. The programmable high-power power supply is connected to the ordinary switch via an Ethernet interface on one end and to the smart cockpit via an output channel on the other end, so as to provide test power to multiple smart cockpits at the same time. The output terminal of the DC regulated power supply is connected to the signal conditioning board to supply power to the signal conditioning board.

4. The intelligent cockpit automated testing system according to claim 1, characterized in that, The CAN communication box specifically includes two independently configured CAN channels for CAN bus communication processing; The serial communication module is used to realize serial communication between the smart cockpit and the industrial control computer, or the serial communication module is used for communication with other serial devices. The signal generator is connected to the industrial control computer and the signal conditioning board respectively, and is used to provide arbitrary waveform signals to the smart cockpit under test. It has a total of 4 independent channels, of which 2 channels are directly output to the outside through the signal conditioning board, and the other 2 channels are expanded into 16-channel signals for external output through the 2-to-16 expansion module of the signal conditioning board. The DIO module is connected to the industrial computer and the signal conditioning board respectively. It is used to transfer the received signal to the smart cockpit under test and provide 8 DO, 8 DI and 8 DI / DO signals. The 8 DI / DO signals are directly acquired or output by the signal conditioning board and are compatible with TTL level and CMOS level. The other 8 DO signals output 24V high-level signals by the digital boost module of the signal conditioning board. The other 8 DI signals acquire the externally input 24V high-level signals by the digital buck module of the signal conditioning board. The AIO module is connected to the industrial control computer and the signal conditioning board, respectively, to transfer the received signals to the smart cockpit under test, and provides 64 AI signals and 32 AO signals. The 32 AI signals and 16 AO signals are directly acquired or output via the signal conditioning board, with a signal range of -10V to +10V. The 32 AI signals acquire external input voltage signals (-32V to +32V) via the analog buck module of the signal conditioning board, and the 16 AO signals output voltage signals (-32V to +32V) via the analog boost module of the signal conditioning board. The power amplifier load module is connected to the signal conditioning board via a cable to simulate a smart cockpit power amplifier device.

5. The intelligent cockpit automated testing system according to claim 4, characterized in that, The aforementioned 2-to-16 expansion module is used to expand the signals from the two channels of the signal generator into 16 signals; The analog step-down module is used to step down 32 AI signals from the AIO module to acquire analog voltage signals from -32V to +32V. The analog boost module is used to boost 16 of the AO signals from the AIO module to achieve an output of an analog voltage signal from -32V to +32V. The digital step-down module is used to step down eight of the DI signals from the DIO module to achieve the acquisition of a 24V high-level signal. The digital boost module is used to boost eight of the DO signals from the DIO module to achieve a 24V high-level signal output. The analog load module provides eight channels of resistance signals with different resistance ranges. The analog load module is connected to the signal conditioning board via pin headers, allowing for flexible replacement of analog load modules with different resistance ranges. The relay module is used to control the opening / closing of each relay via a host computer to adjust the acquired power amplifier load, analog load, AI, AO, DI, DO, and arbitrary waveform signals.

6. The intelligent cockpit automated testing system according to any one of claims 1 to 5, characterized in that, The system integrates several functional instructions through host computer software. Users generate custom test case files based on test case templates, and then import them into the host computer software. The host computer software automatically recognizes the user's test cases, and the main test thread sequentially traverses all test cases and executes the corresponding functions according to the instructions in each test case, thereby realizing the testing of the intelligent cockpit under test.

7. The intelligent cockpit automated testing system according to claim 6, characterized in that, The host computer software integrates several function instructions, including but not limited to: The system includes programmable power supply commands, CAN communication commands, serial communication commands, image processing commands, data acquisition and control commands, script operation commands, human-machine interaction commands, and test process control commands. Users can select or freely combine these commands according to their actual needs to create test cases specific to their specific requirements.

8. A method for automated testing of an intelligent cockpit using the system described in claim 7, characterized in that, The method includes the following steps: (1) The user starts the host computer software and loads the test case file to begin testing; (2) After the initialization of various devices and parameters is completed, the host computer software enters the main thread; (3) The system executes each execution instruction of the current test case in sequence according to the received test case; (4) The system obtains the corresponding test results through the test judgment process of the execution instructions of each test case.

9. The method for automated testing of intelligent cockpits according to claim 8, characterized in that, Step (4) specifically includes: (4.1) Determine whether the execution instruction of the current test case has passed the test. If yes, proceed to step (4.2); otherwise, proceed to step (4.1.1). (4.1.1) If the test fails, the host computer software will select whether to continue the test according to the configuration value of the user parameter file. If yes, proceed to step (4.2); otherwise, proceed directly to step (4.5). (4.2) Determine whether the current loop count for the test case has been reached. If yes, proceed to step (4.3); otherwise, return to step (3) for loop processing. (4.3) Determine whether the current test case is the last test case. If it is, proceed to step (4.4). Otherwise, update the current test case and return to step (3) for loop processing. (4.4) Determine whether all test cases in the current system have reached the loop count. If so, proceed to step (4.5). Otherwise, update the current test case and return to step (3) for loop processing. (4.5) Generate a report directly and stop the test.

10. The method for automated testing of intelligent cockpits according to claim 9, characterized in that, The method further includes: In the process of executing the current test case after entering the main thread, when the execution instruction of the test case includes a command to start a parallel thread, the system will perform parallel thread testing according to the parallel thread command, including but not limited to: stress-based parallel thread testing, functional parallel thread testing, multi-condition parallel combination parallel thread testing, time-sensitive parallel thread testing, and fault import parallel thread testing.

11. A device for automating testing of intelligent cockpits, characterized in that, The device includes: A processor is configured to execute computer-executable instructions; A memory that stores one or more computer-executable instructions, which, when executed by the processor, implement the steps of the method for automated testing of an intelligent cockpit as described in any one of claims 8 to 10.

12. A processor for implementing automated testing of intelligent cockpits, characterized in that, The processor is configured to execute computer-executable instructions, which, when executed by the processor, implement the steps of the method for automated testing of an intelligent cockpit as described in any one of claims 8 to 10.

13. A computer-readable storage medium, characterized in that, It stores a computer program that can be executed by a processor to implement the steps of the method for automated testing of the intelligent cockpit as described in any one of claims 8 to 10.

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