A multi-type and multi-function-oriented aircraft general detection system and application method

Abstract

The application discloses a multi-type and multi-functional aircraft general detection system and an application method, relates to the field of aircraft guarantee, and provides a multi-type and multi-functional aircraft general detection system and an aircraft general detection method which maximally simplifies operation difficulty. The aircraft general detection system comprises a communication simulation detection subsystem, a flight control and management detection subsystem, a power supply and power source detection subsystem, a general detection system client and an interface adapter. The three subsystems of the application can be independently or integrally operated, the general detection system client of the application can independently or centrally control the three subsystems, the central control computers of the three subsystems of the application can be used as master computers of the whole test system, can be backed up to each other, and can provide complete test analysis support. The application integrates hardware resources and integrates standards, greatly reduces cost, and improves efficiency and reliability.

Description

Technical Field

[0001] This invention relates to a universal aircraft testing system and application method for multiple aircraft types and functions, belonging to the field of aircraft support. Background Technology

[0002] Throughout aircraft development, airborne system integration resources have become increasingly abundant, and the types of communication interfaces have proliferated, placing ever higher demands on testing systems. Traditional testing methods, while highly specialized, have low levels of automation, require a wide variety of equipment, and consequently, face more problems, making it difficult to meet the testing needs of different aircraft. Furthermore, traditional testing methods consume enormous amounts of personnel, equipment, and time, are cumbersome, frequently result in inaccurate tests, and have a high probability of requiring repeated testing, leading to a waste of testing support resources.

[0003] To develop testing and inspection methods for airborne systems of various UAV models, research institutes and industrial sectors have conducted in-depth research. Patent CN115728636A designs a testing system and method for aircraft motors, enabling component-level testing of the motor system, but it cannot perform complete aircraft testing. Patent CN214875663U designs a UAV testing system based on a client, battery testing system, frame testing unit, motor testing unit, flight testing unit, and remote control testing unit. It can test aircraft architecture design, operating mechanisms, and functional performance; however, it lacks sufficient external testing interfaces and software functional modules, making it difficult to achieve universal testing for multiple aircraft models and functions.

[0004] This application proposes a universal testing system and application method for multiple aircraft models and functions. It integrates and standardizes hardware resources, encompasses the main communication interface types currently used in UAVs, and has interface and function expansion capabilities. Combined with relevant equipment and technologies, it significantly reduces costs and improves efficiency and reliability. Summary of the Invention

[0005] The purpose of this invention is to address the problems of complex and cumbersome aircraft inspection processes, low automation levels, and the large number and dispersed nature of the equipment involved. This invention establishes a system-level simulation model, customizes dedicated test content, reconstructs test resources and configures test items to meet the testing needs of different types of aircraft in production and maintenance stages. For different test items, different strategies are adopted to efficiently complete the tasks. By combining relevant equipment and technologies, this invention provides a universal aircraft inspection system and application method that is applicable to multiple aircraft types and functions.

[0006] The technical solution of this invention:

[0007] A universal aircraft testing system for multiple aircraft types and functions includes: a communication simulation testing subsystem, a flight control and management testing subsystem, a power supply and power consumption testing subsystem, a universal testing system client, and interface adapters. The communication simulation testing subsystem is used for simulating the aircraft's telemetry and control link and testing and analyzing communication indicators. The flight control and management testing subsystem is used for simulation and excitation testing of the aircraft's flight control, navigation, instrument, and servo functions based on multiple communication signals and bus signals, for real-time reception of feedback status and data, and for comprehensive analysis of test results. The power supply and power consumption testing subsystem provides the aircraft's power supply and provides a power performance testing channel. The interface adapters are used to interconnect the three subsystems with the aircraft's electrical and communication interfaces. The communication simulation testing subsystem, flight control and management testing subsystem, and power supply and power consumption testing subsystem are respectively assembled in three movable ruggedized cabinets. The universal testing system client is installed in the central control computer of the subsystems. The interface adapters are connected to the movable ruggedized cabinets of the three subsystems via a GXI integrated bus.

[0008] Furthermore, the communication simulation detection subsystem includes a signal generation device unit, a signal analysis device unit, and a radio frequency conditioning combination unit; the signal generation device unit provides a low-power radio frequency signal and amplifies and controls its power to simulate aircraft telemetry / radio frequency signals; the signal analysis device unit provides a radio frequency signal acquisition channel for analyzing aircraft communication indicators and measuring parameters; the radio frequency conditioning combination unit provides a microwave switch and an attenuator for controlling the on / off state of signals in each channel and for signal attenuation.

[0009] Furthermore, the flight control and management testing subsystem includes: a flight control function testing unit, an airborne bus testing unit, and a multi-type signal input / output unit; the flight control function testing unit provides multiple servo test channels for testing the angle performance of the servos, and also provides multiple switching channels to realize the switching excitation and testing of the aircraft flight control system; the airborne bus testing unit provides one 1553b bus and eight serial bus channels, and has corresponding bus fault injection functions, which can realize bus communication testing and fault injection testing, and quickly complete the fault location and troubleshooting of flight control, navigation, instrument and other equipment; the multi-type signal input / output unit provides multiple analog input / output channels and TTL digital IO channels, which can realize the acquisition of analog input signals with a sampling rate of 100kbps, the output of analog signals with a voltage range of -10V to 10V, and digital IO signal communication.

[0010] Furthermore, the power supply and power detection subsystem includes: a programmable DC power supply unit, a three-phase AC power supply unit, and a power supply testing equivalent device unit; the programmable DC power supply unit is used to provide 35V DC power with a full-load current of 8.5A to the aircraft's airborne equipment, realizing programmable DC power supply for the airborne equipment; the three-phase AC power supply unit is used to provide 36V AC power to the aircraft's AC equipment, realizing AC power supply for the airborne equipment; the power supply testing equivalent device unit is used to simulate the airborne equipment and complete the aircraft power supply performance test as a simulated load.

[0011] Furthermore, the central control computers of the three subsystems can all serve as the main control computer for the entire testing system, and can serve as backups for each other, providing complete test analysis support.

[0012] Furthermore, the communication simulation detection subsystem, flight control and management detection subsystem, and power supply and power detection subsystem are connected via a gigabit Ethernet bus, which can form an internal local area network or be connected to the Internet.

[0013] An application method for a universal aircraft testing system applicable to multiple aircraft types and functions includes the following steps:

[0014] Step S01: Connect the interface adapter to the removable ruggedized cabinet of the subsystem via the GXI integrated bus, and connect the aircraft to the interface adapter via different communication and electrical buses.

[0015] Step S02: Open the aircraft general inspection system client, operate the aircraft general inspection system client, plan the test items, input the test actions, and generate the script;

[0016] Step S03: Configure the test hardware environment of the central control computer, calculate the script information, and generate a set of instructions and actions;

[0017] Step S04: Execute the instruction action and provide feedback on the instruction execution result;

[0018] Step S05: Compare the calibration command data and feedback data to determine the qualification of the tested aircraft product and generate a test report.

[0019] Furthermore, if the test script described in step S02 is a single-function, single-point test instruction script, then proceed to step S04 for execution; if it is an automated, multi-functional, multi-point test instruction script, then proceed to step S03 for execution; the test script has a standardized format.

[0020] Furthermore, in the calibration process described in step S05, if all command execution results are qualified, the tested aircraft product is qualified; otherwise, the aircraft product is unqualified. The generated test report can generate the entire test process, or the user can choose the test module independently.

[0021] The beneficial effects of this invention are as follows:

[0022] This invention employs a core test component / software as a general-purpose basic system, designed for test application environments rather than specific engineering projects. The system possesses sufficient excitation, measurement, and input / output resources, which are reusable. The system should be reconfigurable, open, and easily expandable, and its construction should adhere to internationally recognized test hardware and software standards. The system interface design should follow standards or established general specifications, providing interface specifications and development tools for the development of corresponding Test Procedure Sets (TPS). This invention significantly improves integration, broadens its application scope, and enhances versatility, enabling it to provide testing services for various stages of multi-functional and multi-type aircraft, including final assembly, ground testing, and flight support. Attached Figure Description

[0023] Figure 1 The working principle diagram of the general detection system of the present invention.

[0024] Figure 2 The system product decomposition architecture diagram of the present invention.

[0025] Figure 3 Flowchart of the detection method of the present invention. Detailed Implementation

[0026] The invention will now be further explained with reference to the accompanying drawings.

[0027] Example 1: As Figure 1 As shown, a multi-functional aircraft universal testing system for multiple aircraft types includes: a communication simulation testing subsystem, a flight control and management testing subsystem, a power supply and power consumption testing subsystem, a universal testing system client, and interface adapters. The communication simulation testing subsystem, the flight control and management testing subsystem, and the power supply and power consumption testing subsystem are respectively assembled in three mobile military-grade ruggedized cabinets. The universal testing system client is installed in the central control computer of the subsystem. The interface adapters are connected to the three subsystem cabinets via a GXI integrated bus.

[0028] The general testing system client is used to control the three subsystem devices. The central control computer of each of the three subsystems can serve as the main control computer of the entire testing system, and can back up each other, providing complete test analysis support.

[0029] The interface adapter is used to interconnect the aircraft general testing system with the aircraft's electrical and communication interfaces.

[0030] The communication simulation detection subsystem, flight control and management detection subsystem, and power supply and power detection subsystem are connected via a gigabit Ethernet bus, which can form an internal local area network or be connected to the Internet.

[0031] like Figure 2 As shown, a universal testing system for multiple aircraft types and functions is divided into a four-level architecture: system level, subsystem level, core unit, and module. The universal testing system consists of three major subsystems and random accessories. The subsystems are composed of various core units, and the core units are integrated from multiple functional modules.

[0032] The communication simulation and testing subsystem is used for simulating the aircraft telemetry and control link and testing and analyzing communication indicators. It includes: a signal generation device unit, a signal analysis device unit, and a radio frequency conditioning unit. The signal generation device unit includes: a baseband module, a frequency synthesizer module, a low-frequency band module, an IQ modulation and filtering module, a frequency division processing and ACL control module, and a millimeter-wave frequency multiplication and mixing module. The signal analysis device unit includes: a down-conversion module and an intermediate frequency digital analysis module. The radio frequency conditioning unit includes: a microwave switch module, a power amplifier unit module, and an attenuator module.

[0033] The baseband module in the signal generation equipment generates I / Q baseband signals and performs dynamic conditioning of these signals. The frequency synthesizer module generates low-frequency step-hopping signals within a specific range. The low-frequency band module performs IQ modulation and pulse modulation. The IQ modulation and filtering module performs IQ modulation, ALC control, pulse modulation, and filtering within the frequency band. The frequency division and ALC control module performs frequency expansion, signal amplification, compensation, and outputs ALC control levels to the corresponding modules. The millimeter-wave frequency multiplier and mixer module performs mixing, filtering, power combining, and pulse modulation of high-frequency signals.

[0034] The downconversion module in the signal analysis equipment is responsible for frequency conversion, bandwidth conversion, and power conditioning of the radio frequency signal from its frequency and power to the intermediate frequency signal. The intermediate frequency digital analysis module in the signal analysis equipment is responsible for bandpass sampling of the intermediate frequency signal and digital intermediate frequency signal processing and analysis.

[0035] The microwave switch module in the RF conditioning assembly is used to switch the RF channel; the power amplifier unit module in the RF conditioning assembly is used to amplify the signal power; and the attenuator module in the RF conditioning assembly is used to attenuate the output signal.

[0036] The flight control and management testing subsystem is used for simulation and excitation testing of aircraft flight control, navigation, instrumentation, and servo functions based on multiple communication signals and bus signals. It is used to receive feedback status and data in real time and to comprehensively analyze test results. It includes: a flight control function testing unit, an airborne bus testing unit, and multiple signal input / output units. The flight control function testing unit includes: a PWM interface, a digital input / output interface, and an Ethernet interface. The airborne bus testing unit includes: RS422 / RS485 / RS232 / ARINC429 / 1553b / CAN interfaces, etc. The multiple signal input / output units include: analog input interfaces, analog output interfaces, and digital I / O interfaces, etc.

[0037] The PWM interface in the flight control function test unit is used for servo PWM signal simulation and testing; the switch signal interface in the flight control function test unit is used for switch signal simulation and testing of flight control and navigation equipment; the Ethernet interface in the flight control function test unit is used to complete communication interaction between this unit and other units.

[0038] The RS422 / RS485 / RS232 interfaces in the airborne bus test unit are used for the simulation and testing of serial port signals of flight control and servo equipment; the ARINC429 interface in the airborne bus test unit is used for the simulation and testing of 4289 signals of navigation equipment; the 1553b interface in the airborne bus test unit is used for the simulation and testing of 1553b bus signals of flight control and navigation equipment; and the CAN interface in the airborne bus test unit is used for the simulation and testing of CAN bus signals of servo equipment.

[0039] The analog input interface in the multi-type signal input / output unit is used to acquire and analyze analog signals; the analog output interface in the multi-type signal input / output unit is used to generate and output analog signals for testing; the digital I / O interface in the multi-type signal input / output unit is used to acquire, analyze, and output digital I / O signals.

[0040] The power supply and power detection subsystem is used to provide power to the aircraft and to provide a power performance testing channel, including: a programmable DC power supply unit, a three-phase AC power supply unit, and a power test equivalent device unit; the programmable DC power supply unit includes: a control circuit, a voltage and current feedback circuit, and an output protection circuit; the three-phase AC power supply unit includes: a sine wave reference generation circuit, a control circuit, a three-phase inverter circuit, and a drive circuit; the power test equivalent device unit includes: a DC electronic load.

[0041] The control circuit in the programmable DC unit is responsible for the precise and stable control of the DC power supply; the voltage and current feedback circuit in the programmable DC unit is responsible for the high-precision output of the voltage value; and the output protection circuit in the programmable DC unit is responsible for timely cutting off the power supply through overcurrent protection, protecting the power supply and load equipment, and automatically restoring the power supply when appropriate.

[0042] The sinusoidal reference generating circuit in the three-phase AC power supply unit generates three high-precision sinusoidal waves with a phase difference of 120 degrees. The control circuit in the three-phase AC power supply unit performs precise and stable control of the AC power supply. The three-phase inverter circuit in the three-phase AC power supply unit realizes voltage regulation and short-circuit protection. The drive circuit in the three-phase AC power supply unit drives the signal.

[0043] like Figure 3 As shown, an application method for a multi-model, multi-functional aircraft universal testing system is characterized by the following steps:

[0044] Step S01: Connect the interface adapter to the subsystem's mobile military ruggedized cabinet via the GXI integrated bus, and connect the aircraft to the interface adapter via different communication and electrical buses.

[0045] Step S02: Open the aircraft general inspection system client, operate the aircraft general inspection system client, plan the test items, input the test actions, and generate the script;

[0046] Step S03: Configure the test hardware environment of the central control computer, calculate the script information, and generate a set of instructions and actions;

[0047] Step S04: Execute the instruction action and provide feedback on the instruction execution result;

[0048] Step S05: Compare the calibration command data and feedback data to determine the qualification of the tested aircraft product and generate a test report.

[0049] Furthermore, if the test script mentioned in step S02 is a single-function, single-point test instruction script, then the script information is calculated and the process proceeds to step S04 for execution; if it is an automated, multi-functional, multi-point test instruction script, then the process proceeds to step S03 for execution; the test script has a standardized format.

[0050] Furthermore, in the calibration process described in step S05, if all command execution results are qualified, the tested aircraft product is qualified; otherwise, the aircraft product is unqualified. The generated test report can generate the entire test process, or the user can choose the test module independently.

[0051] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A universal aircraft testing system for multiple aircraft types and functions, characterized in that, include: Communication simulation testing subsystem, flight control and management testing subsystem, power supply and power consumption testing subsystem, general testing system client and interface adapter; The communication simulation and testing subsystem is used to simulate the aircraft telemetry and control link and test and analyze communication indicators. The flight control and management testing subsystem is used for simulation and excitation testing of aircraft flight control, navigation, instrument and servo functions based on multiple communication signals and bus signals, and is used to receive feedback status and data in real time, as well as to comprehensively analyze test results. The power supply and power detection subsystem is used to provide power to the aircraft and to provide a power performance testing channel; the interface adapter is used to interconnect the three subsystems with the aircraft's electrical and communication interfaces. The communication simulation testing subsystem, flight control and management testing subsystem, and power supply and power source testing subsystem are respectively assembled in three mobile ruggedized cabinets; the general testing system client is installed in the central control computer of the subsystem. The interface adapters are connected to the mobile ruggedized cabinets of the three subsystems via the GXI integrated bus. The flight control and management testing subsystem includes: a flight control function testing unit, an airborne bus testing unit, and a multi-type signal input / output unit. The flight control function testing unit provides multiple servo test channels for testing the angle performance of servos, and also provides multiple switching channels to excite and test the switching signals of the aircraft flight control system. The airborne bus testing unit provides one 1553b bus and eight serial bus channels, and has corresponding bus fault injection functions, enabling bus communication testing and fault injection testing, and quickly locating and troubleshooting faults in flight control, navigation, and instrumentation equipment. The multi-type signal input / output unit provides multiple analog input / output channels and TTL digital IO channels, enabling analog input signal acquisition at a sampling rate of 100kbps, analog signal output with a voltage range of -10V to 10V, and digital IO signal communication. The power supply and power detection subsystem includes: a programmable DC power supply unit, a three-phase AC power supply unit, and a power supply testing equivalent device unit; the programmable DC power supply unit provides 35V DC power with a full-load current of 8.5A to the aircraft's onboard equipment, realizing programmable DC power supply for the onboard equipment; the three-phase AC power supply unit provides 36V AC power to the aircraft's AC equipment, realizing AC power supply for the onboard equipment; the power supply testing equivalent device unit is used to simulate the onboard equipment and serve as a simulated load to complete the aircraft's power supply performance test; The central control computers of the three subsystems can all serve as the main control computer for the entire test system, and can serve as backups for each other, providing complete test analysis support.

2. The universal aircraft testing system for multiple aircraft types and functions according to claim 1, characterized in that, The communication simulation and detection subsystem includes a signal generation device unit, a signal analysis device unit, and a radio frequency conditioning combination unit. The signal generation device unit provides a low-power radio frequency signal and amplifies and controls its power to simulate aircraft telemetry / radio frequency signals. The signal analysis device unit provides a radio frequency signal acquisition channel for analyzing aircraft communication indicators and measuring parameters. The radio frequency conditioning combination unit provides microwave switches and attenuators for controlling the on / off state of signals in each channel and for signal attenuation.

3. The universal aircraft testing system for multiple aircraft types and functions according to claim 1, characterized in that, The communication simulation detection subsystem, flight control and management detection subsystem, and power supply and power detection subsystem are connected via a gigabit Ethernet bus, which can form an internal local area network or be connected to the Internet.

4. The application method of the multi-model, multi-functional aircraft universal testing system according to any one of claims 1-3, characterized in that, Includes the following steps: Step S01: Connect the interface adapter to the removable ruggedized cabinet of the subsystem via the GXI integrated bus, and connect the aircraft to the interface adapter via different communication and electrical buses. Step S02: Open the aircraft general inspection system client, operate the aircraft general inspection system client, plan the test items, input the test actions, and generate the test script; Step S03: Configure the test hardware environment of the central control computer, calculate the script information, and generate a set of instructions and actions; Step S04: Execute the instruction action and provide feedback on the instruction execution result; Step S05: Compare the calibration command data and feedback data to determine the qualification of the tested aircraft product and generate a test report.

5. The application method according to claim 4, characterized in that: If the test script described in step S02 is a single-function, single-point test instruction script, then proceed to step S04 for execution; if it is an automated, multi-functional, multi-point test instruction script, then proceed to step S03 for execution; the test script has a standardized format.

6. The application method according to claim 4, characterized in that: If all command execution results are qualified, the tested aircraft product is qualified; otherwise, the aircraft product is unqualified. The generated test report can show the entire test process or allow users to select test modules.

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