A comprehensive identification test device and method based on software radio technology

Abstract

This invention discloses a comprehensive identification test device and method based on software-defined radio technology, belonging to the field of avionics equipment testing. The device includes: a core processing and control unit, employing a multi-channel high-speed AD / DA and MPSoC FPGA architecture, supporting concurrent operation of various conventional aircraft identification functions through multiple internally integrated models; a radio frequency transceiver module, connected to the core processing and control unit, used for digital frequency conversion and analog-to-digital conversion of signals; a high-power radio frequency front-end component, internally equipped with multi-stage attenuation circuits and isolation devices, used for physical isolation and filtering attenuation of transmitted and received signals, ensuring its power covers the dynamic range of airborne received signals; and a remote control interface for receiving remote control commands to achieve automated test linkage. This invention allows direct connection to test the receiving performance of airborne equipment without the need for external high-power accessories, achieving a high degree of integration and automation of the test equipment, significantly improving detection and troubleshooting efficiency.

Description

Technical Field

[0001] This invention relates to the field of avionics equipment testing, specifically to a comprehensive identification testing device and method based on software radio technology, used for testing, accepting, and troubleshooting the functions and performance of conventional aircraft identification systems in avionics laboratories. Background Technology

[0002] The statements in this section are provided only as background information in connection with this disclosure and may not constitute prior art.

[0003] In the field of avionics testing and maintenance, routine testing and troubleshooting of various aircraft identification systems are typically required. However, current general-purpose benchtop testing equipment for the integrated identification functions of aircraft ATC (Air Traffic Control), ADS-B (Automatic Dependent Surveillance-Broadcast), AIS (Automatic Identification System), and TCAS (Traffic Collision Avoidance System) generally suffers from the following shortcomings: Limited testing dimensions: Existing testing equipment can often only perform basic tests on system functions. If performance indicators (such as the aircraft's receiving sensitivity and dynamic range) are to be tested, an external high-power accessory must be connected, which is cumbersome and increases the complexity of the test.

[0004] Insufficient signal detection capability: Existing equipment can usually only provide signals to airborne equipment as an excitation source for simple testing, but it cannot perform in-depth analysis and detection of the response signals returned (received) by airborne equipment (e.g., it cannot accurately measure response pulse waveform parameters, duty cycle, rising edge, falling edge, and pulse width, etc.), which is not conducive to in-depth development and troubleshooting.

[0005] Low integration and high cost: Existing test equipment often has single functions and lacks comprehensive design, which means that to complete a comprehensive identification test, it is necessary to purchase multiple different single-function devices, resulting in high costs for building a single device and the overall test system.

[0006] Lack of automated testing capabilities: Existing equipment generally lacks hardware and software interfaces for remote control, and cannot be remotely invoked via network or external commands. Therefore, it cannot work with other testing equipment to form an automated collaborative testing environment. Summary of the Invention

[0007] The purpose of this invention is to address the problems of current general-purpose testing equipment for aircraft ATC, ADS-B, AIS, and TCAS integrated identification functions, such as limited testing dimensions, the need for external power accessories, insufficient signal detection and analysis capabilities, single and unintegrated functions, and the inability to form an automated testing environment through remote interfaces. This invention provides an integrated identification testing device and method based on software radio technology. Based on built-in high-power components and multi-stage attenuation circuits, a core processing and control unit using a multi-channel high-speed AD / DA combined with FPGA architecture, intermediate frequency acquisition and playback technology, and remote network interface design, it achieves a high degree of integration of ATC, ADS-B, AIS, and TCAS functions into one unit. It can directly test the full dynamic range of airborne reception performance as an excitation source, and can also perform in-depth detection and analysis of airborne response signals (such as frequency, power, pulse waveform parameters, etc.). At the same time, it supports remote control and linkage with other devices, thus providing a high-performance, high-precision, intelligent, and automated collaborative testing solution for small benchtop integrated testing.

[0008] The technical solution of the present invention is as follows: A comprehensive identification test device based on software radio technology includes: The core processing and control unit adopts a multi-channel high-speed AD / DA and MPSoC FPGA architecture. The core processing and control unit includes an ARM processor and an FPGA chip. The ARM processor is used to parse the configuration parameters of external input, convert the configuration parameters into control parameters of the signal processing model and the transmission link, and distribute them to the FPGA chip through the bus. The FPGA chip integrates multiple functional signal processing models to support the concurrent operation of various conventional aircraft identification functions. The FPGA chip is used to distribute the received control parameters to the corresponding functional signal processing models through logic decoding to generate digital intermediate frequency signals or process the acquired digital signals. The radio frequency transceiver module, connected to the core processing and control unit, is used to perform digital up-conversion and digital-to-analog conversion on the digital intermediate frequency signal to generate a radio frequency transmission signal, and to perform analog-to-digital conversion and down-conversion on the input radio frequency reception signal before outputting it to the core processing and control unit. A high-power radio frequency front-end component is connected to the radio frequency transceiver module. The high-power radio frequency front-end component includes multi-stage attenuation circuits and isolation devices to isolate the radio frequency transmission signal from the externally input test reception signal, and to perform multi-stage filtering, attenuation and amplification processing on the radio frequency transmission signal and the test reception signal to cover the dynamic range of the airborne reception signal. The remote control interface, connected to the core processing and control unit, has a network interface based on a software interface protocol for receiving external remote control commands to interact with an external automated testing environment.

[0009] Furthermore, the high-power radio frequency front-end assembly includes a high-power radio frequency device capable of withstanding a peak power of 400W and an average power of 200W; the high-power radio frequency front-end assembly is internally equipped with an attenuator, a circulator and an isolator to achieve physical isolation between the output signal and the input signal of the test equipment.

[0010] Furthermore, the radio frequency transceiver module includes a QDUC chip and an ADC chip; the QDUC chip is used to implement digital up-conversion and converts the digital signal into an analog signal through its internal DAC section to generate the radio frequency transmission signal; the ADC chip is used to implement the analog intermediate frequency acquisition of the test received signal; the analog front-ends of both the QDUC chip and the ADC chip use a balun balun transformer coupling.

[0011] Furthermore, the RF transceiver module uses a B9361 agile transceiver to process the transmission and reception of UV and L band signals; the RF front-end of the RF transceiver module uses a balun-coupled balanced-to-unbalanced converter to achieve single-ended differential conversion; the power supply of the RF transceiver module is a low-noise, low-dropout linear regulator (LDO), and the reference clock is provided by a temperature-controlled crystal oscillator.

[0012] Furthermore, the various conventional aircraft identification functions include at least ATC, ADS-B, TCAS, and AIS integrated identification functions; the device also includes a time division duplex (TDD) switch disposed in the radio frequency link, the TDD switch being used to switch between the transmit link and the receive link for processing the radio frequency received signal according to the instructions of the core processing and control unit.

[0013] Furthermore, the core processing and control unit is implemented based on the Zynq architecture, and controls the link gain adjustment and power-on / off timing of the RF transceiver module and the high-power RF front-end component through LVTTL, UART and SPI low-speed communication interfaces.

[0014] Furthermore, it also includes a system control module, which runs device human-machine interaction software employing a three-layer general architecture. The three-layer general architecture, from top to bottom, includes: The presentation layer is used to provide a user interface, collect the configuration parameters and pass them to the business logic layer, and present feedback information. The business logic layer is used to execute core business logic and data processing, and to coordinate the order and conditions of different test business activities. The basic service layer is used to manage software startup and functional business transitions, provide data persistence management and a unified access interface, and provide communication support to the business logic layer.

[0015] Furthermore, the basic service layer specifically includes a log service, a database service, and a bus service; the log service is used to monitor and record events during application operation to ensure fault location; the database service is used to implement persistent management of test data and support automatic generation of test reports; the bus service is used to ensure data transmission and reliable communication between the system and external systems.

[0016] This invention also proposes a method for checking the routine identification functions of an aircraft using the integrated identification test equipment based on software radio technology as described above, comprising the following steps: Step S1: Select test items through a unified software platform and transmit configuration parameters to the core processing and control unit via the network; Step S2: The core processing and control unit converts the configuration parameters into control parameters for the signal processing model and the transmission link and distributes them to the FPGA chip, driving the corresponding multi-functional signal processing model to work concurrently and automatically generating excitation signals in the form of digital intermediate frequency. Step S3: After the excitation signal is digitally up-converted and digital-to-analog converted by the radio frequency transceiver module, it is attenuated and amplified by the high-power radio frequency front-end component and output to the airborne receiving device under test. Step S4: Automatically receive the response signal fed back by the airborne receiving device under test. The response signal is physically isolated by the high-power radio frequency front-end component and input to the radio frequency transceiver module for analog-to-digital conversion and down-conversion before being sent to the core processing and control unit. Step S5: The core processing and control unit performs automatic functional performance analysis on the received response signal.

[0017] Furthermore, in step S5, the automatic functional performance analysis of the received response signal specifically includes: Extract the frequency parameters and peak power parameters of the response signal; The response pulse waveform parameters of the response signal are analyzed. The response pulse waveform parameters include at least the response delay, pulse duty cycle, rising edge, falling edge, pulse width, and pulse top unevenness.

[0018] Compared with existing technologies, the advantages of this invention are: 1. Significantly improved detection efficiency: No additional high-power accessories are required, and it can be directly connected to the airborne system; at the same time, the received signals can be analyzed without relying on additional general-purpose detection equipment (power meters, spectrum analyzers, and oscilloscopes, etc.), making signal observation more intuitive and signal detection, development, and troubleshooting more convenient.

[0019] 2. High integration in miniaturization: By adopting software-defined radio (SDR) and high-density integrated chip technology, the functions that originally required multiple independent devices are condensed into a single handheld terminal, achieving the optimal solution for the comprehensive functionality of test equipment.

[0020] 3. Intelligent and Information-based: Built-in test database management and automatic test report generation functions realize the electronic and traceable maintenance records, providing a data foundation for preventive maintenance.

[0021] 4. Strong environmental adaptability: The robust casing and industrial-grade wide-temperature components enable it to meet the protection requirements of a typical laboratory environment. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments recorded in the embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0023] Figure 1 This is an exploded structural diagram of the integrated identification test device based on software radio technology provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the overall structure of the testing equipment provided in an embodiment of the present invention; Figure 3 This is a hardware design principle block diagram of the testing equipment provided in the embodiments of the present invention; Figure 4 This is a circuit block diagram of the core processing and control unit and the radio frequency transceiver module provided in the embodiments of the present invention; Figure 5 This is a three-layer structure design block diagram of the human-computer interaction software inside the system control module provided in this embodiment of the invention. Detailed Implementation

[0024] It should be noted that relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof 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 elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0025] The features and performance of the present invention will be further described in detail below with reference to embodiments.

[0026] Example 1 like Figures 1 to 5 As shown, this embodiment provides a comprehensive identification test device based on software-defined radio technology, mainly used for testing, accepting, and troubleshooting the functions and performance of conventional aircraft identification systems in avionics laboratories. This device is highly integrated into a miniaturized platform in its physical structure. For details, please refer to... Figure 1 The exploded view of the equipment shown and Figure 2 The diagram shows the overall equipment, which specifically includes: a 4U chassis, front panel assembly, rear panel assembly, display screen, buttons, power module, RF cable, low-frequency cable, and various connectors and miscellaneous components. The 4U chassis features a robust outer shell and industrial-grade wide-temperature components, enabling it to meet the environmental requirements of typical laboratory settings.

[0027] The specific physical hardware components of this device are shown in Table 1 below: Table 1 Equipment Composition Table

[0028] At the system logic and circuit architecture level, refer to Figure 3 The device design principle block diagram shown above integrates ATC / ADS-B / TCAS / AIS functional modules and a system control module within its physical structure. The comprehensive identification and testing device in this embodiment specifically includes the following core components: 1. Core Processing and Control Unit Combination Figure 4The core circuit unit block diagram shown is based on the Zynq architecture, taking into account factors such as concurrent RF signal requirements, device structure, power consumption, size, and debugging / testing. It employs a multi-channel high-speed AD / DA converter and an MPSoC FPGA architecture. Specifically, this unit includes an ARM processor and an FPGA chip. (1) ARM processor: Runs relevant software to parse the configuration parameters. The display interface of the system control module transmits the configuration parameters to the ARM processor via the network. The ARM processor calls the API functions provided by the parameter calculation and distribution software to convert the configuration parameters into control parameters for the signal processing model and the transmission link, and distributes them to the FPGA chip via the on-chip bus or serial port.

[0029] (2) FPGA chip: FPGA model design is performed, and different functions are implemented through different FPGA models. The FPGA integrates multiple functional signal processing models to support the concurrent operation of various conventional aircraft identification functions such as ATC, ADS-B, TCAS, and AIS. The FPGA chip distributes the received control parameters (obtained by writing to registers) to the corresponding functional signal generation model through logic decoding to generate digital intermediate frequency signals or process the acquired digital intermediate frequency signals.

[0030] In addition, the core processing and control unit also uses a microwave control board to control the link gain adjustment and power-on / off timing related operations of the RF transceiver module and the high-power RF front-end components described later through low-speed communication interfaces such as LVTTL, UART and SPI.

[0031] 2. Radio Frequency Transceiver Module Continue reading Figure 4 The RF transceiver module connects to the core processing and control unit, primarily implementing intermediate frequency (IF) acquisition, IF playback, and RF reception and transmission technology based on agile transceivers. Specifically, it includes: (1) A QDUC chip is used to realize digital up-conversion, and the digital intermediate frequency signal from the FPGA is converted into an analog signal through its internal DAC section, thereby realizing digital-to-analog conversion and generating radio frequency transmission signal.

[0032] (2) An ADC chip is used to realize the analog intermediate frequency acquisition and analog-to-digital conversion of the external test received signal.

[0033] (3) The analog front-ends of both the QDUC chip and the ADC chip use balun converters for transformer coupling. Selecting a transformer or balun with excellent balance characteristics as the front-end device can significantly reduce the performance degradation caused by unbalance characteristics, making it suitable for applications that are sensitive to SNR (signal-to-noise ratio) and SFDR (spurious-free dynamic range).

[0034] (4) A B9361 agile transceiver is used to process the transmission and reception of UV and L band signals. The RF transceiver front-end of this part also uses a balun-coupled balanced-to-unbalanced converter to achieve single-ended differential conversion. In addition, to reduce the impact of power supply noise on device performance, a low-noise low-dropout linear regulator (LDO) is used for the power supply; a temperature-controlled crystal oscillator is used for the reference clock to meet the clock accuracy requirements, and the number of crystal oscillators is reduced through the whole board design, thereby reducing the impact of crystal oscillators on the receiving sensitivity.

[0035] 3. High-power radio frequency front-end components A high-power RF front-end assembly connects to the RF transceiver module, replacing traditional external power accessories and allowing test equipment to be directly connected to the airborne system (aircraft CNI system). This assembly includes high-power RF devices capable of handling peak power of 400W and average power of 200W, with its transmit power covering the dynamic range of airborne received signals, enabling direct testing of the receiving performance of airborne equipment.

[0036] High-power radio frequency (RF) front-end components internally incorporate multi-stage attenuation circuits, circulators, and isolation devices. Through multi-stage filtering, attenuation, and amplification, they achieve high-range transmission and high-precision power output. Simultaneously, components such as isolators and circulators physically isolate the RF transmission signal output from the test equipment from the externally input test reception signal.

[0037] Specifically, considering the characteristics of time-division protocols, this embodiment incorporates a time-division duplex (TDD) switch in the radio frequency link (such as the AIS signal transceiver link). This TDD switch is used to perform high-speed switching between the transmit link (including filtering, amplification, and attenuation) and the receive link (including filtering and amplification) for processing radio frequency received signals, according to instructions issued by the microwave control board (core processing and control unit).

[0038] 4. Remote control interface and system control module The testing equipment features a remote control interface with a gigabit Ethernet network interface (10M / 100M / 1000M) based on a software interface protocol. This interface receives external remote control commands, enabling remote control via tablets and industrial PCs. This facilitates integration with other testing equipment, allowing for the rapid construction of automated testing systems and the creation of collaborative communication scenarios. The equipment also includes RS422 and USB debugging interfaces.

[0039] In terms of software implementation, the test equipment includes a system control module, which internally runs device human-machine interface software using a three-tier general architecture, supporting functional testing with concurrent mechanisms. (See also...) Figure 5 The software architecture diagram shown depicts a three-tiered general architecture, with the tiers arranged from top to bottom as follows: (1) Presentation layer: responsible for the design and implementation of user interaction interface, providing interactive experience through intuitive button layout, menu and prompt information, collecting user input (i.e. configuration parameters) and passing it to business logic layer, presenting feedback information, and designing interactive logic to respond to user events (click, focus switching, etc.).

[0040] (2) Business Logic Layer: Executes the core business logic and processes of the application (including functional business data and process scheduling logic, functional business protocol sequence number and deserialization logic), including data processing, verification, calculation and decision-making, coordinating and controlling the order and conditions of different business activities, ensuring the correctness of operation, and returning the processing results to the presentation layer.

[0041] (3) Basic Service Layer: Responsible for managing the software startup and functional business jumps, and providing the following specific services: Log service: Monitors and records events during application operation to ensure reliable fault location.

[0042] Database service: Enables persistent management of test data and provides a unified access interface. It supports intelligent functions such as test database management and automatic generation of test reports, and realizes electronic and traceable maintenance records.

[0043] Bus service: Ensures efficient data transmission and reliable communication within and outside the system, and supports stable operation of the business logic layer.

[0044] Framework Management and Remote Control Services: Supports plugin management, configuration management, and external remote control communication.

[0045] 5. Workflow for routine aircraft identification function checks (method implementation examples) Based on the aforementioned hardware and software architecture, this embodiment also provides an automated testing method, the specific steps of which are as follows: Step S1: The tester selects the test item through the unified software platform of the presentation layer. The presentation layer transmits the configuration parameters to the core processing and control unit (ARM processor) via network or bus. Step S2: The core processing and control unit parses the setting parameters, converts the parameters into control parameters for the signal processing model and the transmission link, and distributes them to the FPGA chip to drive the corresponding multi-functional signal processing model (ATC / ADS-B / TCAS / AIS model) to work concurrently and automatically generate excitation signals in the form of digital intermediate frequency. Step S3: After the excitation signal is digitally up-converted and digital-to-analog converted by the radio frequency transceiver module (QDUC chip, B9361 chip), it is attenuated, filtered and amplified by the high-power radio frequency front-end component, and then output to the aircraft CNI system (airborne receiving equipment) under test. Step S4: The test equipment automatically receives the response signal fed back by the airborne equipment under test. After the response signal is physically isolated by the circulator / isolator in the high-power RF front-end component (or switched to the receiving link by the TDD switch), it is input to the RF transceiver module (ADC chip) for analog-to-digital conversion and analog intermediate frequency acquisition down-conversion, and finally sent to the core processing and control unit for processing. Step S5: The core processing and control unit performs automatic functional performance analysis on the received response signal. At this point, without relying on additional general-purpose testing equipment (such as power meters, spectrum analyzers, and oscilloscopes), the frequency parameters and peak power parameters of the response signal can be directly extracted, and the response pulse waveform parameters of the response signal (including response delay, pulse duty cycle, rising edge, falling edge, pulse width, and pulse top unevenness, etc.) can be analyzed. Finally, the basic service layer automatically generates a test report and persists it.

[0046] The technical solution adopted in this embodiment achieves a significant improvement in detection efficiency and a high degree of integration and miniaturization of testing equipment. It can complete high-precision and intuitive observation and troubleshooting of airborne signals without the need for external accessories, and has extremely high engineering application and promotion value.

[0047] The embodiments described above merely illustrate specific implementation methods of this application, and while the descriptions are detailed and specific, they should not be construed as limiting the scope of protection of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the technical solution of this application, and these modifications and improvements all fall within the scope of protection of this application.

[0048] This background section is provided to generally present the context of the invention. The work of the currently named inventors, the work to the extent described in this background section, and aspects of this section that did not constitute prior art at the time of application are neither expressly nor impliedly acknowledged as prior art to the invention.

Claims

1. A comprehensive identification testing device based on software-defined radio technology, characterized in that, include: The core processing and control unit adopts a multi-channel high-speed AD / DA and MPSoC FPGA architecture. The core processing and control unit includes an ARM processor and an FPGA chip. The ARM processor is used to parse the configuration parameters of external input, convert the configuration parameters into control parameters of the signal processing model and the transmission link, and distribute them to the FPGA chip through the bus. The FPGA chip integrates multiple functional signal processing models to support the concurrent operation of various conventional aircraft identification functions. The FPGA chip is used to distribute the received control parameters to the corresponding functional signal processing models through logic decoding to generate digital intermediate frequency signals or process the acquired digital signals. The radio frequency transceiver module, connected to the core processing and control unit, is used to perform digital up-conversion and digital-to-analog conversion on the digital intermediate frequency signal to generate a radio frequency transmission signal, and to perform analog-to-digital conversion and down-conversion on the input radio frequency reception signal before outputting it to the core processing and control unit. A high-power radio frequency front-end component is connected to the radio frequency transceiver module. The high-power radio frequency front-end component includes multi-stage attenuation circuits and isolation devices to isolate the radio frequency transmission signal from the externally input test reception signal, and to perform multi-stage filtering, attenuation and amplification processing on the radio frequency transmission signal and the test reception signal to cover the dynamic range of the airborne reception signal. The remote control interface, connected to the core processing and control unit, has a network interface based on a software interface protocol for receiving external remote control commands to interact with an external automated testing environment.

2. The integrated identification test equipment based on software radio technology according to claim 1, characterized in that, The high-power radio frequency front-end assembly includes high-power radio frequency devices capable of withstanding peak power of 400W and average power of 200W; the high-power radio frequency front-end assembly is internally equipped with attenuators, circulators and isolators to achieve physical isolation between the output signal and the input signal of the test equipment.

3. The integrated identification test equipment based on software radio technology according to claim 1, characterized in that, The radio frequency transceiver module includes a QDUC chip and an ADC chip; the QDUC chip is used to implement digital up-conversion and converts the digital signal into an analog signal through its internal DAC section to generate the radio frequency transmission signal; the ADC chip is used to implement the analog intermediate frequency acquisition of the test received signal; the analog front-end of both the QDUC chip and the ADC chip uses a balun balun transformer coupling.

4. The integrated identification test equipment based on software radio technology according to claim 1, characterized in that, The radio frequency transceiver module uses a B9361 agile transceiver to process and transmit UV and L band signals; the radio frequency front-end of the radio frequency transceiver module uses a balun-coupled balanced-to-unbalanced converter to achieve single-ended differential conversion; the power supply of the radio frequency transceiver module is a low-noise, low-dropout linear regulator (LDO), and the reference clock is provided by a temperature-controlled crystal oscillator.

5. The integrated identification test equipment based on software radio technology according to claim 1, characterized in that, The various conventional aircraft identification functions include at least ATC, ADS-B, TCAS, and AIS integrated identification functions; the device also includes a time division duplex (TDD) switch installed in the radio frequency link, which is used to switch between the transmit link and the receive link for processing the radio frequency received signal according to the instructions of the core processing and control unit.

6. The integrated identification test equipment based on software radio technology according to claim 1, characterized in that, The core processing and control unit is implemented based on the Zynq architecture and controls the link gain adjustment and power-on / off timing of the RF transceiver module and the high-power RF front-end component through LVTTL, UART and SPI low-speed communication interfaces.

7. The integrated identification test equipment based on software radio technology according to claim 1, characterized in that, It also includes a system control module, which runs device human-machine interface software using a three-layer general architecture. The three-layer general architecture, from top to bottom, includes: The presentation layer is used to provide a user interface, collect the configuration parameters and pass them to the business logic layer, and present feedback information. The business logic layer is used to execute core business logic and data processing, and to coordinate the order and conditions of different test business activities. The basic service layer is used to manage software startup and functional business transitions, provide data persistence management and a unified access interface, and provide communication support to the business logic layer.

8. The integrated identification test equipment based on software radio technology according to claim 7, characterized in that, The basic service layer specifically includes a log service, a database service, and a bus service; the log service is used to monitor and record events during application operation to ensure fault location; the database service is used to implement persistent management of test data and support automatic generation of test reports; the bus service is used to ensure data transmission and reliable communication between the system and external systems.

9. A method for checking the routine identification function of an aircraft using an integrated identification test device based on software-defined radio technology as described in any one of claims 1 to 8, characterized in that, Includes the following steps: Step S1: Select test items through a unified software platform and transmit configuration parameters to the core processing and control unit via the network; Step S2: The core processing and control unit converts the configuration parameters into control parameters for the signal processing model and the transmission link and distributes them to the FPGA chip, driving the corresponding multi-functional signal processing model to work concurrently and automatically generating excitation signals in the form of digital intermediate frequency. Step S3: After the excitation signal is digitally up-converted and digital-to-analog converted by the radio frequency transceiver module, it is attenuated and amplified by the high-power radio frequency front-end component and output to the airborne receiving device under test. Step S4: Automatically receive the response signal fed back by the airborne receiving device under test. The response signal is physically isolated by the high-power radio frequency front-end component and input to the radio frequency transceiver module for analog-to-digital conversion and down-conversion before being sent to the core processing and control unit. Step S5: The core processing and control unit performs automatic functional performance analysis on the received response signal.

10. The method according to claim 9, characterized in that, In step S5, the automatic functional performance analysis of the received response signal specifically includes: Extract the frequency parameters and peak power parameters of the response signal; The response pulse waveform parameters of the response signal are analyzed. The response pulse waveform parameters include at least the response delay, pulse duty cycle, rising edge, falling edge, pulse width, and pulse top unevenness.

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