An aircraft system integrated test bench

Abstract

The application provides an airplane system comprehensive test bench, and relates to the technical field of equipment testing; the application provides platform function support through simulation of a flight system, comprehensive control and test auxiliary systems, data acquisition and analysis systems, software test systems, airborne system integration modules and a fault injection system, and realizes linkage comprehensive experiments with different airplane system test benches through a platform I / O resource pool, a simulation power supply and distribution system, a test network, a reflective memory network and a wiring and junction system; the application realizes the erection of the airplane system comprehensive test bench between a power device system test bench, an atmospheric inertial navigation system test bench, a passenger cabin information system test bench, a copper bird test bench and an iron bird test bench, thereby meeting the linkage test operation requirements.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of equipment testing, in particular to an aircraft system comprehensive test bench. BACKGROUND

[0002] At present, the debugging of aircraft systems is mainly carried out independently. The power plant system test bench, the atmospheric inertial navigation system test bench, the cabin information system test bench, the copper bird test bench and the iron bird test bench have been built, but there is a lack of an aircraft system comprehensive test bench for cooperative linkage comprehensive experiments of different aircraft system test benches, so that further linkage test operations cannot be carried out.

[0003] Therefore, it is necessary to build an aircraft system comprehensive test bench between the power plant system test bench, the atmospheric inertial navigation system test bench, the cabin information system test bench, the copper bird test bench and the iron bird test bench to meet the linkage test operation requirements. SUMMARY

[0004] To solve the above technical problems, the present application provides an aircraft system comprehensive test bench for cooperative linkage comprehensive experiments of different aircraft system test benches, comprising a simulated flight system, a comprehensive control and test auxiliary system, a data acquisition and analysis system, a software test system, a platform I / O resource pool, an airborne system integration module, a fault injection system, a simulated power supply and distribution system, a test network, a reflective memory network and a wiring and junction system.

[0005] The simulated power supply and distribution system is electrically connected with the test network, the wiring and junction system, the airborne system integration module and the simulated flight system, respectively. The test network is electrically connected with the simulated flight system, the comprehensive control and test auxiliary system, the data acquisition and analysis system, the software test system, the platform I / O resource pool and the fault injection system, respectively. The reflective memory network is electrically connected with the simulated flight system. The wiring and junction system is electrically connected with the simulated flight system, the platform I / O resource pool, the airborne system integration module and the fault injection system, respectively.

[0006] The aircraft system test bench is electrically connected with the simulated power supply and distribution system, the test network, the reflective memory network and / or the wiring and junction system, and comprises a power plant system test bench, an atmospheric inertial navigation system test bench, a cabin information system test bench, an airborne system test bench, an iron bird test bench and a copper bird test bench.

[0007] The power device system test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the atmospheric inertial navigation system test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the cabin information system test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the iron bird test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the copper bird test bench is electrically connected with the analog power supply and distribution system and the wiring and junction system respectively, and each sub-operation module of the airborne system test bench is electrically connected with the wiring and junction system.

[0008] As a further solution, the simulation flight system comprises a simulation control system, a simulation running platform and an engineering cockpit; wherein,

[0009] The simulation control system provides simulation management functions, including a model dynamic simulation unit, a companion flying and backfill unit, a data excitation unit and an exciter management module; wherein, the model dynamic simulation unit is used for dynamic simulation control of each flight phase of flight simulation running; the companion flying and backfill unit is used for providing flight environment configuration, data recording and playback functions; the data excitation unit is used for generating excitation data, executing injection or receiving excitation data; the exciter management unit realizes centralized configuration, modification and monitoring of the working state of each exciter device by setting injection or receiving excitation data to each exciter of the airborne system simulation model;

[0010] The simulation running platform provides simulation running functions, including a flight simulation system, an aircraft body simulation model library and an airborne system simulation model library; wherein, the aircraft body simulation model library is used for storing aircraft body simulation models, the airborne system simulation model library is used for storing airborne system simulation models, and the flight simulation system is used for flight simulation running according to dynamic simulation control;

[0011] The engineering cockpit provides simulation interaction functions, including a flight control component, an instrument display system and a visual system; wherein, the flight control component is used for operation interaction with the simulation running platform, the instrument display system is used for displaying various index data of the simulation running platform, and the visual system is used for three-dimensional dynamic display of the simulation running process of the simulation running platform.

[0012] As a further solution, the model dynamic simulation unit comprises an initialization module, a simulation management module, a flight simulation management module, a real-time simulation module, a model integration module, a flight environment simulation module and an interface model;

[0013] The data excitation unit is used for generating excitation data according to network configuration and transmission sequence configuration, including a user management module, an engineering management module, a network configuration module, an excitation configuration module, a transmission sequence configuration module and a system management module.

[0014] The accompanying flight and recharge unit comprises an accompanying flight module and a recharge module; wherein the accompanying flight module comprises a flight scene configuration module, a flight instruction control module and a flight data monitoring module; the recharge module comprises a data import module, a recharge configuration module and a recharge control module;

[0015] The exciter management unit comprises a device monitoring module, a configuration management module and a state control module.

[0016] As a further solution, the airborne system integration module is provided with a real avionics system integration unit and a simulated avionics system integration unit; wherein the real avionics system integration unit is used for interfacing with each real avionics system, and the simulated avionics system integration unit is used for providing avionics system function simulation; wherein the avionics system function simulation comprises an avionics core system, a communication system, a navigation system, an integrated monitoring system, an airborne maintenance system, a flight record system, a high-lift system and a hydraulic system.

[0017] As a further solution, the integrated control and test auxiliary system comprises a test health master control module, an I / O configuration management module, a configuration recording tool, an offline data analysis tool, an ICD design management tool, a test program development tool, a fault injection software and an environment monitoring module.

[0018] As a further solution, the platform I / O resource pool is used for managing I / O interface resources used by the integrated experiment, and the I / O interface resources comprise ARINC664 simulation resources, ARINC664 acquisition resources, ARINC 429 simulation resources, ARINC 429 acquisition resources, ARINC 825 simulation resources, ARINC 825 acquisition resources, discrete quantity simulation resources, discrete quantity acquisition resources, analog quantity simulation resources, analog quantity acquisition resources, in-flight control system bus simulation resources and in-flight control system bus acquisition resources.

[0019] As a further solution, the analog power supply and distribution system comprises an alternating current master control cabinet, a power distribution box unit and a power distribution controller; wherein the alternating current master control cabinet comprises a device for providing alternating current energy input and direct current energy input, comprising a direct current power supply, a direct current voltage regulating power supply, an alternating current power supply and an alternating current voltage regulating power supply; the power distribution box unit comprises a primary power distribution unit and a secondary power distribution unit; wherein the primary power distribution unit is used for busbar power supply simulation, comprising a primary direct current power distribution box and a primary alternating current power distribution box; the secondary power distribution unit is used for real device power supply simulation, comprising a secondary direct current power distribution box and a secondary alternating current power distribution box, and the power distribution controller is used for power supply logic control, and is electrically connected with the alternating current master control cabinet and the power distribution box unit.

[0020] As a further solution, the wiring and junction system comprises a wiring system, a circuit test panel and a junction system; wherein,

[0021] The wiring system is used for providing I / O interface resource hardware wiring, comprising ARINC664 wiring equipment, ARINC429 wiring equipment, discrete quantity wiring equipment and analog quantity wiring equipment; the circuit test panel is composed of a plurality of terminal boxes and is arranged between the signal junction system and the wiring system and is used for providing circuit test points for signal circuit test;

[0022] The junction system comprises a separation surface and a wire distribution box, the wire distribution box is used for providing wire harness junction between real equipment and test benches, and the separation surface comprises a copper bird junction separation module, an iron bird junction separation module, a MiniRig junction separation module and other system junction separation modules;

[0023] The copper bird junction separation module is used for connecting a copper bird test bench, the iron bird junction separation module is used for connecting an iron bird test bench, the MiniRig junction separation module is used for connecting each sub-operation module, and the other system junction separation module is used for connecting an atmospheric inertial navigation system test bench, a passenger cabin information system test bench and a power device system test bench.

[0024] As a further solution, the software test system comprises a cooperative test module, a network performance monitoring module, an ICMP / SNMP test module and a Pub_Sub test module; wherein, the cooperative test module, the network performance monitoring module and the ICMP / SNMP test module are respectively connected with an analog flight system, an integrated control and test auxiliary system, a data acquisition and analysis system and a fault injection system through a test network, and the Pub_Sub test module directly tests platform I / O resource pool and analog power supply and distribution system as downstream systems.

[0025] As a further solution, the sub-operation module comprises a fuel operation module, a cabin door control operation module, a hydraulic operation module, a landing gear operation module, a brake operation module, an air management operation module, a fire prevention operation module, an APU power supply operation module and an auxiliary fuel system operation module.

[0026] Compared with the prior art, the aircraft system integrated test bench provided by the present application has the following advantages:

[0027] The application provides platform function support through a simulation flight system, a comprehensive control and test auxiliary system, a data acquisition and analysis system, a software test system, an airborne system integration module and a fault injection system, and realizes linkage comprehensive experiments of different aircraft system test benches through a platform I / O resource pool, a simulation power supply and distribution system, a test network, a reflective memory network and a wiring and junction system; the application realizes the erection of an aircraft system comprehensive test bench between a power device system test bench, an atmospheric inertial navigation system test bench, a passenger cabin information system test bench, a copper bird test bench and an iron bird test bench, thereby meeting the linkage test operation demand. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 An aircraft system comprehensive test bench architecture provided by the application is shown in the figure;

[0029] Figure 2 A fault injection system architecture provided by the application is shown in the figure;

[0030] Figure 3 A simulation power supply and distribution system provided by the application is shown in the figure;

[0031] Figure 4 A wiring and junction system architecture provided by the application is shown in the figure;

[0032] Figure 5 A comprehensive wiring software function module division provided by the application is shown in the figure;

[0033] Figure 6 An engineering cockpit architecture provided by the application is shown in the figure;

[0034] Figure 7 A simulation excitation system architecture provided by the application is shown in the figure;

[0035] Figure 8 A dynamic simulation flight architecture provided by the application is shown in the figure;

[0036] Figure 9 An exciter management software architecture provided by the application is shown in the figure;

[0037] Figure 10 An avionics system integration provided by the application is shown in the figure;

[0038] Figure 11 An integrated comprehensive test bench and copper bird integration scheme provided by the application is shown in the figure;

[0039] Figure 12 An iron bird first type scheme architecture provided by the application is shown in the figure;

[0040] Figure 13 An iron bird second type scheme architecture provided by the application is shown in the figure. DETAILED DESCRIPTION

[0041] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present application with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. The components of the embodiments of the present application described and shown in the drawings can be arranged and designed in various different configurations.

[0042] Referring to Figure 1 The present application provides an aircraft system comprehensive test bench, which is used for cooperative linkage comprehensive experiment with different aircraft system test benches, and comprises a simulated flight system, a comprehensive control and test auxiliary system, a data acquisition and analysis system, a software test system, a platform I / O resource pool, an airborne system integration module, a fault injection system, a simulated power supply and distribution system, a test network, a reflective memory network and a wiring and junction system.

[0043] The simulated power supply and distribution system is electrically connected with the test network, the wiring and junction system, the airborne system integration module and the simulated flight system respectively, the test network is electrically connected with the simulated flight system, the comprehensive control and test auxiliary system, the data acquisition and analysis system, the software test system, the platform I / O resource pool and the fault injection system respectively, the reflective memory network is electrically connected with the simulated flight system, and the wiring and junction system is electrically connected with the simulated flight system, the platform I / O resource pool, the airborne system integration module and the fault injection system respectively.

[0044] The aircraft system test bench is electrically connected with the simulated power supply and distribution system, the test network, the reflective memory network and / or the wiring and junction system, and comprises a power device system test bench, an atmospheric inertial navigation system test bench, a cabin information system test bench, an airborne system test bench, an iron bird test bench and a copper bird test bench.

[0045] The power device system test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the atmospheric inertial navigation system test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the cabin information system test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the iron bird test bench is electrically connected with the reflective memory network and the wiring and junction system respectively, the copper bird test bench is electrically connected with the simulated power supply and distribution system and the wiring and junction system respectively, and each sub-operation module of the airborne system test bench is electrically connected with the wiring and junction system.

[0046] The integrated control and test auxiliary system of the embodiment provides test-related management control functions for a system integrated test bench. Mainly includes: test bench control and its health monitoring, test process management, configuration management, test ICD design management tool, I / O configuration management, remote communication management, clock management. The test bench control and its health monitoring function can intuitively display the test system state information, and help the test personnel manage the entire test environment through the easy-to-use operation page; the test process management function is responsible for planning, organizing and supervising the entire test process, ensuring that the test is carried out in an orderly manner according to the plan; the configuration management function is used to record, track and manage various configuration information in the test test piece and test environment; the test ICD design management function is mainly used to manage ICD data; the I / O configuration management function can identify system I / O hardware resources, and support users to flexibly configure the correspondence between ICD and I / O resources; the remote communication management function can remotely control test resources, and realize one-key control of starting and stopping of all service programs; the clock management function synchronizes the clock system of the test bench, ensuring that time-sensitive test activities can be accurately performed.

[0047] As shown in Figure 2 , the fault injection resources of the fault injection system adopt independent fault injection devices, and the fault injection device types include low-speed bus, high-speed bus, optical fiber bus and non-bus signal type. It can realize fault injection on the physical layer, electrical layer and protocol layer of various buses or non-bus signals, and can independently control each fault to support fault sequence testing. Each fault injection device adopts a unified product architecture, which is convenient for modular control and processing.

[0048] The IO interface resource adopts the interface module plus chassis controller mode according to the PXI design idea. The IO interface module mainly includes the physical interface of the corresponding bus or non-bus. When the IO interface module is selected for integrated testing, the corresponding IO interface resource margin is reserved. At the same time, the IO interface resource adopts an extensibility design, supporting subsequent incremental expansion of test resources and test equipment to meet compatibility requirements.

[0049] The IO interface resource mainly includes the following simulation resource types: inboard bus simulation resource of the flight control system, analog single-ended simulation resource, analog differential simulation resource, current analog simulation resource, discrete quantity simulation resource, LVDT / RVDT simulation resource, A429 simulation resource, RTD simulation resource, Resolver simulation resource, A825 simulation resource and A664 simulation resource.

[0050] The IO interface resources mainly include the following types of acquisition resources: bus acquisition resources in a flight control system, single-ended analog acquisition resources, differential analog acquisition resources, current analog acquisition resources, discrete quantity acquisition resources, LVDT / RVDT acquisition resources, A429 acquisition resources, Resolver acquisition resources, A825 acquisition resources, A664 acquisition resources, and Ethernet acquisition devices.

[0051] The analog power supply and distribution system provided by the embodiment has high simulation accuracy, flexible power regulation capability, and a seamless switching interface with a real power system. Figure 3

[0052] The AC master control cabinet provides power input for the DC power supply and the AC power supply. The DC power supply can convert 380V three-phase AC power or 220V single-phase AC power into 28V DC power to realize 28V power supply. The DC voltage regulating power supply can realize 28V power supply voltage regulation (4 channels) with a regulation range of 17V-32V to meet the needs of flight control tests. The AC power supply can convert 380V three-phase AC power or 220V single-phase AC power into 115V AC power to realize the supply of simulated 115V, 380Hz-800Hz variable-frequency AC power. The AC voltage regulating power supply can convert 380V three-phase AC power or 220V single-phase AC power into three-phase AC power with a rated output voltage of 115V (voltage regulation range 0-266V) and a wide frequency range of 0-2650Hz to simulate the output of a PMG on a real aircraft. The rated output power is 2KVA.

[0053] The primary distribution box and the secondary distribution box allocate power resources, and can reasonably allocate power according to the needs of electrical equipment. The distribution box realizes control functions of the circuit through internal switches, contactors and other elements. This includes circuit connection, disconnection, conversion and protection operations. When abnormal conditions such as overcurrent, overload, short circuit, and leakage occur in the circuit, the distribution box can quickly cut off the power supply to protect the test bench, electrical equipment and personnel safety. The distribution box also provides display and monitoring of related parameters such as voltage, current, frequency, power-on / off timing, etc. of the current power supply channel, facilitating test personnel to check the power supply state.

[0054] The analog power supply and distribution system supports remote or manual shutdown control of each power supply channel. Remote shutdown mode: a remote control module PLC (Programmable Logic Controller) is introduced to receive remote instructions and control the circuit breakers in the distribution box. The remote control module is connected to the upper computer software using network communication technology (Ethernet) to realize remote monitoring and control. Manual shutdown control: a manual operation switch is provided on the distribution box to allow on-site personnel to directly operate the circuit breakers for shutdown control. The manual operation switch and the remote control module are interlocked to ensure that manual operation is not possible in remote control mode or remote control is not possible in manual operation mode.​

[0055] For AC power channel which needs frequency conversion control, frequency converter is installed in the distribution box. Frequency converter has remote communication interface (RS485) for receiving frequency parameters set remotely. After receiving frequency parameters, frequency converter adjusts output voltage and frequency according to the parameters to realize speed control of AC motor.

[0056] The wiring and junction system architecture is shown in Figure 4 The wiring and junction system is designed to meet the dynamic configuration of test configurations according to different test requirements in aircraft system integration testing. It can meet the actual needs of test personnel during testing, and can flexibly switch the measured object through program control, realizing seamless conversion from real parts to simulation parts, greatly reducing the need for manual intervention to modify the configuration.

[0057] Traditionally, switching from real parts to simulation parts often requires complex physical operations and tedious documentation, while the program-controlled switching function of the wiring and junction system automates these steps, ensuring the accuracy and efficiency of the switch. In addition, the wiring and junction system also significantly shortens the test preparation time. Test personnel no longer need to spend a lot of time on manual switching and configuring the test environment, but can focus more on developing test strategies and analyzing test results. This not only improves test efficiency, but also makes the test process more coherent, helping to quickly identify and solve problems, thereby accelerating the integration and verification process of aircraft systems.

[0058] As shown in Figure 4 The wiring and junction system is designed for program-controlled switching between real parts and simulation parts during aircraft integration testing, and is divided into two parts with the junction system. The wiring system contains advanced wiring switching equipment, designed in a modular manner, taking into account compatibility factors to facilitate user flexibility in configuring and expanding according to test requirements. At the same time, the supporting wiring switching software provides an intuitive and easy-to-use interface, allowing users to easily achieve fast switching and monitoring of signals, greatly improving test efficiency and accuracy. The wiring system can support switching of ARINC664 bus signals, ARINC429 bus signals, discrete signals, and analog signals (including AD, LVDT, RVDT, Resolver, etc.) to simulation parts, ensuring seamless switching of experimental configurations during testing.

[0059] The junction system integrates separation panels, wire management boxes, and circuit test panels for block processing, signal extraction, orderly arrangement, and quick positioning and troubleshooting during testing, ensuring the integrity and reliability of the test environment and further improving the integration and testing capabilities of the system.

[0060] The functional module division is shown in Figure 5As shown, the main functions of the comprehensive wiring software are to realize the program-controlled switching operation of the wiring equipment, provide the HMI interface and operation services for user interaction, and be capable of configuration management and switching of the test configuration, while providing the management function of the cables in the test bench for unified management, revision and query of the cable information in the test environment.

[0061] As a further solution, the simulation flight system comprises a simulation control system, a simulation running platform and an engineering cockpit; wherein,

[0062] The simulation control system provides simulation management functions, including a model dynamic simulation unit, a companion flying and back-feeding unit, a data excitation unit and an exciter management module; wherein, the model dynamic simulation unit is used for dynamic simulation control of each flight phase of the flight simulation running; the companion flying and back-feeding unit is used for providing flight environment configuration, data recording and playback functions; the data excitation unit is used for generating excitation data and executing injection or receiving of the excitation data; and the exciter management unit realizes centralized configuration, modification and monitoring of the working state of each exciter device by setting injection or receiving of the excitation data to each exciter of the airborne system simulation model;

[0063] As shown, Figure 6 The embodiment realizes high simulation effect and real-time performance through cooperation of the engineering cockpit, the I / O resource pool, the airborne system device, the experimental network, the visual scene and the simulation control system. The I / O resource pool is connected with the engineering cockpit and simultaneously communicates with the airborne system device and the experimental network in real time. Because the real-time data of the airborne system device can directly participate in the simulation process, the engineering cockpit can simulate the real flight environment, and the accuracy and reliability of the simulation are improved.

[0064] On the test network, the visual scene and the simulation control system are running. The visual scene software is responsible for generating realistic flight scenes, including terrain, weather, lighting and other environmental factors, to provide an immersive visual experience for the operator. The simulation control system contains high-fidelity simulation models and airborne system simulation models, which can simulate the flight characteristics and system responses of the aircraft in different environments, providing reliable data support for testing and verification.

[0065] The simulation excitation system architecture is as shown in Figure 7 The simulation excitation system plays a key role in the aircraft system comprehensive test bench, and its functions include model dynamic simulation, data excitation, companion flying and back-feeding, and exciter management software. These functions provide powerful simulation and excitation functions for the aircraft system comprehensive test bench. The hardware components of the simulation excitation system include a real-time simulation computer, a timer board card, a VMIC reflection board card and a real-time network switch.

[0066] Through the application of simulation excitation system, the civil aviation field can more effectively integrate and verify the system during the design, development and operation stage, improve the safety, reliability and performance of the aircraft system, and also reduce the development cost and time.

[0067] Dynamic simulation flight architecture Figure 8 As shown, during dynamic simulation flight, the aircraft system model can simulate the logical function and input-output interface of the actual aircraft system. The interface model converts the input and output of the model into bus data streams according to the definition of the interface control document (ICD). These bus data streams can interact with on-board devices to achieve dynamic joint simulation based on flight tasks.

[0068] In this way, dynamic joint simulation can effectively simulate various complex scenarios and operations in the aircraft. This simulation can not only be used for pilot training and flight performance evaluation, but also for system design and verification to ensure the reliability and safety of the aircraft in various situations.

[0069] The data excitation software divides the function into five modules, including user management module, engineering management module, network configuration module, excitation configuration module, sending sequence configuration module, and system management module. Among them, the user management module is used for user information management, user authentication and authorization; the engineering management module is used for saving and managing the test configuration used by the data excitation; the network configuration module is used for configuring IO interface parameters and mapping relationship between ICD document and IO interface; the sending sequence configuration module is used for obtaining ICD document, configuring and saving instruction set configuration, and the system management module is used for data excitation log information management and user data excitation operation guidance; wherein the test configuration contains true version information and test environment version information, and the instruction set configuration is used to save the instruction set used by the data excitation.

[0070] The data excitation software can obtain the ICD and IO configuration information defined by the integrated control and test auxiliary system, and on the basis of the ICD format, edit the excitation message, send the excitation data to the test network through the synchronous network of the upper and lower computers, and convert the bus signal through the interface resource, and then interact with the true piece.

[0071] As the core software of the aircraft system integrated test bench, the data excitation software has functions beyond basic data acquisition and sending. It can seamlessly integrate the integrated control and test auxiliary system, accurately capture and analyze ICD and IO configuration information.

[0072] Through the mechanism of cooperation between the upper and lower computers, the software can efficiently push the edited stimulation data to the test network, and convert the data into corresponding bus signals using rich interface resources (ARINC664, ARINC 429, etc.). This process ensures the accuracy, real-time performance and reliability of the data during transmission, and lays a solid foundation for subsequent data interaction with real hardware devices (real parts).

[0073] Further, the data stimulation software is adapted to a plurality of IO board cards installed in the lower computer, including but not limited to ARINC664, ARINC 429, etc., to comprehensively support different interface types of data. At the data processing level, the software can automatically complete the tasks of packaging, scheduling and sending the application layer data to the designated board card, realize the simulation of complex data flow, and effectively reduce the test preparation period and cost.

[0074] In addition, the data stimulation software stimulation state statistics and visualization function can display the key data indicators in the test process in real time, help the test personnel quickly locate the problem and evaluate the system performance. By integrating fault diagnosis and prediction algorithms, the software can also provide early warning when abnormal data occurs by bypassing the stimulated data

[0075] The flight accompanying and backfilling software is divided into two parts: flight accompanying and backfilling. The flight accompanying system is responsible for flight simulation, monitoring and control of the test aircraft, while the backfilling system is responsible for processing and analyzing the flight data collected during the flight accompanying process and feeding back the processing results to the flight accompanying system to form a closed loop flight test and analysis system.

[0076] The flight accompanying and backfilling software is a C / S architecture, with the upper computer deploying the client software and the lower computer deploying the server program for underlying data scheduling and communication with the flight simulation model. The client is used for simple logic implementation, including engineering management, flight scene configuration, flight data monitoring, flight instruction control, data import, backfilling control, backfilling configuration, processing request, etc. The server is used to process the execution request sent by the upper computer client, and to establish and recycle the process. The interface management is responsible for communication with the flight simulation model, injecting data into the flight simulation model and obtaining the output data of the flight simulation model. The database is used for storing and reading and writing operations of the data of the entire flight accompanying and backfilling software.

[0077] The companion flight and recharging system adopts a C / S (Client / Server) architecture design, achieving efficient data processing and communication mechanisms. In the system, the upper computer serves as the control center, deploying client software and providing an intuitive and user-friendly user interface, supporting a series of core functions, including: project management (project creation, editing and deletion), flight scene customization configuration (terrain, weather, obstacle setting, etc.), real-time flight data monitoring (dynamic display of key parameters such as speed, altitude, attitude, etc.), precise control of flight instructions (takeoff, landing, route adjustment, etc.), data import and export functions (supporting multiple formats of data files, facilitating data backup and sharing), and recharging control module, allowing users to flexibly configure recharging parameters to achieve precise intervention on the simulation environment. In addition, the client also integrates a request processing system for receiving user operations and forwarding them to the server for processing.

[0078] The lower computer plays an important role as the server, deploying a powerful server program that focuses on the scheduling and processing of underlying data, as well as seamless communication with the flight simulation model. The server program can efficiently handle execution requests from the upper computer client, dynamically create and manage processes, and ensure reasonable allocation and recovery of system resources. Its built-in interface management system uses standardized protocols to achieve bidirectional communication with the flight simulation model, not only injecting various control data and parameters into the simulation model in real time, but also receiving and analyzing the output data from the simulation model to provide accurate and timely feedback to the upper computer.

[0079] To ensure data integrity and security, the system integrates a high-performance database management system to store all data generated during the operation of the companion flight and recharging software, including user configuration information, flight records, simulation results, etc. The database supports efficient read and write operations to ensure fast response to data access and maintenance of data consistency, providing a solid foundation for stable operation of the system and subsequent data analysis.

[0080] The exciter management software can centrally configure and control all exciter devices in the system. Through the functions of sending control instructions and receiving feedback data, it can centrally configure, modify and monitor the working mode, frequency and other signal states of the exciter in each subsystem. Specifically, there are two usage scenarios:

[0081] When the software is in static configuration mode, experimenters can manually configure various exciter parameters through the software interface, and realize the transmission and reception of instructions through the dynamic parameter configuration function;

[0082] When the software is in dynamic configuration mode, the data access interface of the software can obtain the interface parameters of the flight simulation model to automatically adjust the settings of the exciter.

[0083] The data monitoring module mainly supports interface data monitoring of ARINC664 bus and ARINC429 bus, and supports importing ICD files. The module supports ICD monitoring, IO device monitoring, graphic monitoring and customized interface monitoring and other monitoring modes.

[0084] The data acquisition and analysis software is composed of a data monitoring module, a data storage module and a special protocol analysis module, realizes monitoring and storage of ARINC664 bus and ARINC429 bus data, supports ARINC661 protocol analysis and ARINC429 data acquisition and analysis encapsulated in Block messages.

[0085] The data storage module mainly supports recording and processing of ARINC664 bus and ARINC429 bus data, including storage configuration and management, data analysis and viewing and data export management. By receiving storage configuration information and control instructions transmitted by the front end, the start and stop control of the storage service of the bus is realized, and the data stored after acquisition is stored into the database.

[0086] The special protocol analysis module supports ARINC661 protocol and ARINC429 data encapsulated in Block messages for acquisition and analysis.

[0087] The user management module supports management and maintenance of user information, and requires input of user account and password for software login to access, thereby ensuring data security.

[0088] In order to realize the function of avionics network performance and health state analysis, the system uses special network performance test tools and technologies for testing:

[0089] Collaborative test software (i.e. "test flow automatic tool module" required in the bidding, hereinafter referred to as collaborative test software)

[0090] The collaborative test software has the function of automatically obtaining deployment package, and can automatically obtain software package and code required for deployment from a specified location. This part of the bottom layer is realized through Shell script language, and the script specifies the source and target location of the software package.

[0091] The software also has an automatic operation and maintenance tool, which can perform batch system configuration, batch program deployment and batch command running. The collaborative test software has the function of generating test reports, can automatically collect test running results, and generate structured reports, and finally save them to the specified output path in HTML format.

[0092] Network performance monitoring software

[0093] Network performance monitoring software is used to collect, analyze and display network device running status, response time, network bandwidth and other network indicators in real time, generate and display 3D view, line chart, pie chart, curve chart and column chart to show the network connectivity, traffic and bandwidth usage and other conditions. The software can help developers and operation and maintenance team to find problems in time and carry out effective management and optimization.

[0094] After the test is completed, the delay, packet loss rate, jitter and other indicators will be automatically calculated, and these indicators can also be obtained in real time during the experiment.

[0095] Pub_Sub test software

[0096] Pub_Sub test software can automatically generate test scripts that meet the specifications based on the interface control document, simulate and verify message passing between systems. It can also load different versions of ICD files and test bench configurations to configure and execute according to different test requirements.

[0097] After configuring the required information, the software will simulate and send data according to the ICD, and can execute multiple Pub_Sub test scripts in batches, which can improve the efficiency and automation of the test.

[0098] ICMP / SNMP test software

[0099] This software provides a user-friendly interface that allows users to select target IP addresses and click buttons to execute Ping commands to detect network device connectivity and response time, and display the returned response time, packet loss rate and other information in a graphical interface.

[0100] It can manage network devices through SNMP and ICMP protocols, and finally display the feedback MIB parameter values through the graphical user interface, so that users can view the status and performance of the device in real time.

[0101] As shown in Figure 9 The four software modules are interconnected with the simulated flight system, integrated control and test auxiliary system, data acquisition and analysis system, fault injection system, platform I / O resources, and simulated power supply and distribution system. The Pub_Sub test module directly tests the platform I / O resources and simulated power supply and distribution system as downstream systems.

[0102] The collaborative test software (i.e. the "test flow automatic tool module" required by the tender, hereinafter referred to as the collaborative test software) as an automated test tool and deployment tool, mainly realizes the functions of uploading and downloading deployment packages, software deployment, generating test reports and other functions.

[0103] The collaborative test software has the function of automatically obtaining the deployment package, and can automatically obtain the software package and code required for deployment from the specified location. The underlying part is implemented through a Shell script language, which specifies the source and target location of the software package.

[0104] The software also has an automated operation and maintenance tool that can perform batch system configuration, batch program deployment, and batch command execution. The collaborative test software has a built-in test report generation function that can automatically collect test run results and generate structured reports, which are finally saved in HTML format to the specified output path.

[0105] The collaborative test software, as an automated test tool and deployment tool, mainly implements functions such as deployment package upload and download, software deployment, and test report generation. The software function modules are divided into managing remote nodes, uploading / downloading deployment packages, software deployment, and generating test reports. The management of remote nodes module includes configuring node information and establishing SSH connections; the deployment package upload / download module includes viewing files, uploading deployment packages, and downloading deployment packages; the software deployment module includes installing software and running software; and the test report generation module includes viewing scripts and software deployment statistics.

[0106] The network performance monitoring software is used for traffic and bandwidth monitoring of the integrated modular avionics (IMA) bus network. It classifies and monitors the network topology and device types of A and B networks. It collects, analyzes, and displays network indicators such as device running status, response time, and network bandwidth in real time. It generates and displays 3D views, line charts, pie charts, curve charts, and bar charts to show network connectivity status, traffic, and bandwidth usage. This part uses data visualization libraries and tools to achieve this.

[0107] The network performance monitoring software can help developers and operation and maintenance teams to timely discover problems and effectively manage and optimize them. It can monitor the working status of devices, including online / offline status, normal / abnormal status, specific events, log messages, and CAS / INFO messages generated by the device. After the test is completed, it automatically calculates the delay, packet loss rate, and jitter. These indicators can also be obtained in real time during the experiment.

[0108] The Pub_Sub test software can generate test scripts that meet the specifications based on the interface control document and the properties of the Pub_Sub table header. It can simulate and verify message passing between systems. It can also load different versions of ICD files and test bench configurations to configure and execute according to different test requirements.

[0109] After setting the required information, the platform I / O resource is called to simulate data generation and sending, and then the data sent by the terminal system is collected through the platform I / O resource to perform ICD analysis, and finally automatic interpretation is performed according to the analysis content to obtain the conclusion of whether the test is passed. The software can batch execute multiple Pub_Sub test scripts, which can improve the efficiency and automation degree of the test; finally, a test report is generated to count network delay, packet loss rate and other indicators.

[0110] The ICMP / SNMP test software can import the XML file scanned and generated by the network performance monitoring software into the ICMP / SNMP test software as a configuration file to obtain the device configuration.

[0111] The software supports calling the Ping command of the operating system, sending an ICMP request, and analyzing the ICMP response to perform a rapid connectivity test and detect the connectivity and response time of the network device. At the same time, a user-friendly interface is provided, so that the user can execute the Ping command under a certain IP device and view the analysis result of the response message.

[0112] The software provides an SNMP management tool to obtain and set MIB data from the device through the SNMP protocol, including register status, configuration table, pulse port, etc. A graphical user interface is provided to enable the customer to conveniently view and analyze the MIB data, and real-time updating of the data is supported to reflect the state change of the device.

[0113] The ICMP / SNMP test software manages the network device through the SNMP and ICMP protocols, and finally displays the feedback MIB parameter value through the graphical user interface to enable the user to view the state and performance of the device in real time. The software is divided into four modules, namely, importing device list, ICMP tool, SNMP tool, and performance monitoring. The importing device list displays device details, the ICMP tool includes Ping tool and test result display, the SNMP tool includes GET command, SET command, polling configuration, and MIB library management, and the performance monitoring is parameter echoing.

[0114] Avionics system integration such as Figure 10As shown, the avionics system interface includes various high-performance communication protocols such as the ARINC 664 standard, as well as traditional ARINC 429 and ARINC 825 interfaces, and is also compatible with analog signals, discrete signals, and standard Ethernet interfaces. These diversified interface designs are designed to efficiently and stably drive onboard avionics devices (RDIU remote data interface unit, ADN remote switch, ARS radio interface device, RIU remote interface unit, etc.) and various avionics devices in the cockpit (TCP tuning control board, ACP audio control board, RCP radio communication panel, DCP display control board, CCD cursor control board, etc.), ensuring accurate information transmission and coordinated operation of the system.

[0115] For cockpit devices, the avionics system uses the ARINC 825 interface as the standard communication interface, which not only has high-speed transmission capability but also ensures real-time and reliable data transmission. Through this interface, the system can accurately drive the control panel components to realize real-time adjustment and display of flight parameters; at the same time, it also supports signal acquisition and remote control of key devices such as dimming control power supply, providing a cockpit environment that is comprehensive in function and convenient to operate for pilots, thereby improving the safety and efficiency of flight operations.

[0116] The test of the aircraft system includes copper bird, electric bird and iron bird, wherein the copper bird refers to the test of the power supply system of the aircraft such as power generation and power distribution. The copper bird test bench installs the equipment according to the real state of the power supply and distribution system on the real aircraft in a one-to-one scale, verifies the correctness, integrity and safety of the implementation of the functions of each system; wherein the system comprehensive test bench and the copper bird integration scheme are as shown in Figure 11 , wherein the blue part is the construction range of the system comprehensive test bench.

[0117] The iron bird refers to the test of the mechanical system of the aircraft, such as the simulation test of landing gear, wing and other faults, which is an essential key test facility for aircraft system integration, optimization design, airworthiness certification and delivery operation, and continuous airworthiness. The iron bird is made of hundreds of steel materials, which are staggered, wired and welded, similar to the aircraft shape it simulates, with the same layout and very close to the main load-bearing structures of the aircraft such as front beam, rear beam and frame.

[0118] The first type of scheme uses the avionics real device of the system comprehensive test bench and the flight simulation system, and uses the iron bird FCE, FSECU, hydraulic, landing gear, brake system and rear actuator, rudder surface, etc. to carry out the test, and the system integration architecture is as shown in Figure 12 ; the second type of scheme uses the avionics real device of the system comprehensive test bench, FCE, FSECU, HLRM real device and flight simulation system, and uses the iron bird actuator, rudder surface, etc. to carry out the test, and the system integration architecture is as shown in Figure 13 .

[0119] The above examples only express the preferred embodiments, which are described in a more specific and detailed manner, but they cannot be interpreted as limiting the scope of the patent. It should be noted that, for those skilled in the art, several modifications and improvements can be made without departing from the inventive concept, and these are all within the scope of protection of the present application.

Claims

1. An aircraft system integrated test bench, used to coordinate with different aircraft system test benches to conduct coordinated integrated experiments, characterized in that: It includes flight simulation system, integrated control and test auxiliary system, data acquisition and analysis system, software testing system, platform I / O resource pool, airborne system integration module, fault injection system, simulated power supply and distribution system, test network, reflective memory network and wiring and tandem system; The simulated power supply and distribution system is electrically connected to the test network, the wiring and tandem system, the airborne system integration module, and the simulated flight system respectively; the test network is electrically connected to the simulated flight system, the integrated control and test auxiliary system, the data acquisition and analysis system, the software testing system, the platform I / O resource pool, and the fault injection system respectively; the reflective memory network is electrically connected to the simulated flight system; the wiring and tandem system is electrically connected to the simulated flight system, the platform I / O resource pool, the airborne system integration module, and the fault injection system respectively; The aircraft system test bench is electrically connected to the simulated power supply and distribution system, the test network, the reflective memory network and / or the wiring and tandem system, and includes a power plant system test bench, an atmospheric inertial navigation system test bench, a cabin information system test bench, an airborne system test bench, an iron bird test bench and a copper bird test bench; Among them, the power plant system test bench is electrically connected to the reflective memory network and the wiring and junction system respectively, the atmospheric inertial navigation system test bench is electrically connected to the reflective memory network and the wiring and junction system respectively, the cabin information system test bench is electrically connected to the reflective memory network and the wiring and junction system respectively, the iron bird test bench is electrically connected to the reflective memory network and the wiring and junction system respectively, the copper bird test bench is electrically connected to the simulated power supply and distribution system and the wiring and junction system respectively, and each sub-operation module of the airborne system test bench is electrically connected to the wiring and junction system respectively.

2. The aircraft system integrated test bench according to claim 1, characterized in that: The simulated flight system includes a simulation control system, a simulation operation platform and an engineering cockpit; wherein, The simulation control system provides simulation management functions, including a model dynamic simulation unit, a flight companion and re-injection unit, a data excitation unit, and an exciter management unit. The model dynamic simulation unit is used to dynamically simulate and control each flight phase of the flight simulation operation; the flight companion and re-injection unit is used to provide flight environment configuration, data recording and playback functions; the data excitation unit is used to generate excitation data and execute injection or reception of excitation data; the exciter management unit realizes centralized configuration, modification, and monitoring of the working status of each exciter device in the airborne system simulation model by injecting or receiving excitation data into or from each exciter device. The simulation operation platform provides simulation operation functions, including a flight simulation system, an aircraft body simulation model library, and an airborne system simulation model library; wherein the aircraft body simulation model library is used to store aircraft body simulation models, the airborne system simulation model library is used to store airborne system simulation models, and the flight simulation system is used to perform flight simulation operation according to dynamic simulation control; The engineering cockpit provides simulation interaction functions, including a flight control component, an instrument display system and a visual system; wherein the flight control component is used to interact with the simulation operation platform, the instrument display system is used to display various indicator data of the simulation operation platform, and the visual system is used to dynamically display the simulation operation process of the simulation operation platform in three dimensions.

3. The aircraft system integrated test bench according to claim 2, characterized in that: The model dynamic simulation unit includes an initialization module, a simulation management module, a flight simulation management module, a real-time simulation module, a model integration module, a flight environment simulation module and an interface model; The data excitation unit is used to generate excitation data according to the network configuration and the transmission sequence configuration, and includes a user management module, a project management module, a network configuration module, an excitation configuration module, a transmission sequence configuration module and a system management module; The accompanying flight and recharging unit includes an accompanying flight module and a recharging module; wherein the accompanying flight module includes a flight scene configuration module, a flight command control module and a flight data monitoring module; the recharging module includes a data import module, a recharging configuration module and a recharging control module; The actuator management unit includes a device monitoring module, a configuration management module and a state control module.

4. The aircraft system integrated test bench according to claim 1, characterized in that: The airborne system integration module is provided with an avionics system real component integration unit and an avionics system simulation integration unit; wherein, the avionics system real component integration unit is used to connect to each avionics system real component, and the avionics system simulation integration unit is used to provide avionics system function simulation; wherein, the avionics system function simulation includes the avionics core system, communication system, navigation system, integrated monitoring system, airborne maintenance system, flight recording system, high lift system and hydraulic system.

5. The aircraft system integrated test bench according to claim 1, characterized in that: The integrated control and test assistance system includes a test health master control module, an I / O configuration management module, a configuration recording tool, an offline data analysis tool, an ICD design management tool, a test program development tool, a fault injection software, and an environmental monitoring module.

6. The aircraft system integrated test bench according to claim 1, characterized in that: The platform I / O resource pool is used to manage the I / O interface resources used in the linkage comprehensive experiment. The I / O interface resources include ARINC664 simulation resources, ARINC664 acquisition resources, ARINC 429 simulation resources, ARINC 429 acquisition resources, ARINC 825 simulation resources, ARINC825 acquisition resources, discrete quantity simulation resources, discrete quantity acquisition resources, analog quantity simulation resources, analog quantity acquisition resources, flight control system bus simulation resources and flight control system bus acquisition resources.

7. The aircraft system integrated test bench according to claim 1, characterized in that: The simulated power supply and distribution system includes an AC main control cabinet, a distribution box unit and a distribution controller; wherein, the AC main control cabinet includes a unit for providing AC power input and DC power input, including a DC power supply, a DC voltage regulating power supply, an AC power supply and an AC voltage regulating power supply; the distribution box unit includes a first-level distribution unit and a second-level distribution unit; wherein, the first-level distribution unit is used for busbar power supply simulation, including a first-level DC distribution box and a first-level AC distribution box; the second-level distribution unit is used for real equipment power supply simulation, including a second-level DC distribution box and a second-level AC distribution box, and the distribution controller is used for performing power supply logic control, and is electrically connected to the AC main control cabinet and the distribution box unit respectively.

8. The aircraft system integrated test bench according to claim 1, characterized in that: The wiring and tandem system includes a wiring system, a circuit breaker test panel and a tandem system; wherein, The wiring system is used to provide I / O interface resource hardware wiring, including ARINC664 wiring equipment, ARINC429 wiring equipment, discrete wiring equipment and analog wiring equipment; the circuit break test panel is composed of a plurality of terminal boxes, deployed between the signal tandem system and the wiring system, and is used to provide a circuit break test point for performing signal circuit break tests; The tandem system includes a separation surface and a wire management box. The wire management box is used to provide wire harness tandem between the real equipment and the test bench. The separation surface includes a copper bird tandem separation module, an iron bird tandem separation module, a MiniRig tandem separation module and other system tandem separation modules. Among them, the copper bird tandem separation module is used to connect to the copper bird test bench, the iron bird tandem separation module is used to connect to the iron bird test bench, the MiniRig tandem separation module is used to connect to each sub-operation module, and the other system tandem separation module is used to connect to the atmospheric inertial navigation system test bench, the cabin information system test bench and the power plant system test bench.

9. The aircraft system integrated test bench according to claim 1, characterized in that: The software testing system includes a collaborative testing module, a network performance monitoring module, an ICMP / SNMP testing module and a Pub_Sub testing module; wherein the collaborative testing module, the network performance monitoring module and the ICMP / SNMP testing module are respectively communicated with the simulated flight system, the integrated control and test auxiliary system, the data acquisition and analysis system and the fault injection system through the test network, and the Pub_Sub testing module directly tests the platform I / O resource pool and the simulated power supply and distribution system as downstream systems.

10. The aircraft system integrated test bench according to claim 1, characterized in that: The sub-operation modules include a fuel operation module, a door control operation module, a hydraulic operation module, a landing gear operation module, a brake operation module, an air management operation module, a fire protection operation module, an APU power supply operation module and an auxiliary fuel system operation module.

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