Comprehensive test bed for aircraft system

Abstract

The invention provides a comprehensive test bench for an aircraft system, and relates to the technical field of equipment testing. Platform function support is provided through the simulation flight system, the comprehensive control and test auxiliary system, the data acquisition analysis system, the software test system, the airborne system integration module and the fault injection system. Through a platform I / O resource pool, a simulation power supply and distribution system, a test network, a reflection memory network and a wiring and tandem system, different aircraft system test benches are cooperated to carry out a linkage comprehensive experiment. According to the invention, the building of the aircraft system comprehensive test bench is realized among the power device system test bench, the atmospheric inertial navigation system test bench, the passenger cabin information system test bench, the copper bird test bench and the iron bird test bench, so that the linkage test operation requirement is met.

Description

Technical Field

[0001] The invention relates to the technical field of equipment testing, and in particular to an aircraft system integrated test bench. Background Art

[0002] At present, the debugging of aircraft systems is mainly carried out independently. The construction of power plant system test bench, atmospheric inertial navigation system test bench, cabin information system test bench, copper bird test bench and iron bird test bench has been completed. However, there is a lack of an aircraft system integrated test bench that can coordinate with different aircraft system test benches to conduct integrated experiments, which makes it impossible to carry out further integrated test operations.

[0003] Therefore, it is necessary to set up an aircraft system integrated test bench between the power plant system test bench, atmospheric inertial navigation system test bench, cabin information system test bench, copper bird test bench and iron bird test bench to meet the needs of linkage test operations. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides an aircraft system integrated test bench, which is used to coordinate different aircraft system test benches to conduct linkage integrated experiments, including a simulated flight system, an integrated control and test auxiliary system, a data acquisition and analysis system, a software testing 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 tandem system;

[0005] 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;

[0006] 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, respectively, 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;

[0007] Among them, the power plant system test bench is electrically connected to the reflective memory network and the wiring and connection system, the atmospheric inertial navigation system test bench is electrically connected to the reflective memory network and the wiring and connection system, the cabin information system test bench is electrically connected to the reflective memory network and the wiring and connection system, the iron bird test bench is electrically connected to the reflective memory network and the wiring and connection system, the copper bird test bench is electrically connected to the simulated power supply and distribution system and the wiring and connection system, and each sub-operation module of the airborne system test bench is electrically connected to the wiring and connection system.

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

[0009] 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 module; wherein the model dynamic simulation unit is used to perform dynamic simulation control on 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 by injecting or receiving excitation data into each exciter device of the airborne system simulation model;

[0010] The simulation operation platform provides a simulation operation function, 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;

[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 to perform operational interaction 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 perform three-dimensional dynamic display of the simulation operation process of the simulation operation platform.

[0012] As a further solution, 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;

[0013] 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;

[0014] 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;

[0015] The actuator management unit includes 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 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 avionics core system, communication system, navigation system, integrated monitoring system, airborne maintenance system, flight recording system, high lift system and hydraulic system.

[0017] As a further solution, 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.

[0018] As a further solution, the platform I / O resource pool is used to manage the I / O interface resources used in the linkage comprehensive experiment, and the I / O interface resources include 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, bus simulation resources within the flight control system, and bus acquisition resources within the flight control system.

[0019] As a further solution, 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 device 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 power supply logic control, and is electrically connected to the AC main control cabinet and the distribution box unit respectively.

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

[0021] 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 signal circuit break test;

[0022] The junction system includes a separation surface and a wire management box, wherein the wire management box is used to provide a wire harness junction between the real equipment and the test bench, and the separation surface includes a copper bird junction separation module, an iron bird junction separation module, a MiniRig junction separation module and other system junction separation modules;

[0023] Among them, the copper bird connection and separation module is used to connect to the copper bird test bench, the iron bird connection and separation module is used to connect to the iron bird test bench, the MiniRig connection and separation module is used to connect to each sub-operation module, and the other system connection and 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.

[0024] As a further solution, 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.

[0025] As a further solution, 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.

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

[0027] The present invention provides platform function support through a simulated flight system, an integrated control and test auxiliary system, a data acquisition and analysis system, a software testing system, an airborne system integration module and a fault injection system, and realizes coordinated linkage comprehensive experiments with different aircraft system test benches through a platform I / O resource pool, a simulated power supply and distribution system, a test network, a reflective memory network and a wiring and tandem system; the present invention realizes the construction of an aircraft system comprehensive test bench between a power plant system test bench, an atmospheric inertial navigation system test bench, a cabin information system test bench, a copper bird test bench and an iron bird test bench, thereby meeting the linkage test operation requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A schematic diagram of the architecture of an aircraft system integrated test bench provided by the present invention;

[0029] Figure 2 A schematic diagram of the fault injection system architecture provided by the present invention;

[0030] Figure 3 A schematic diagram of a simulated power supply and distribution system provided by the present invention;

[0031] Figure 4 A schematic diagram of the wiring and connection system architecture provided by the present invention;

[0032] Figure 5 A schematic diagram of the functional modules of the integrated wiring software provided by the present invention;

[0033] Figure 6 A schematic diagram of the engineering cockpit architecture provided by the present invention;

[0034] Figure 7 A schematic diagram of the simulation excitation system architecture provided by the present invention;

[0035] Figure 8 A schematic diagram of a dynamic flight simulation architecture provided by the present invention;

[0036] Fig. 9 A schematic diagram of the actuator management software architecture provided by the present invention;

[0037] Fig.10 A schematic diagram of the avionics system integration provided by the present invention;

[0038] Fig.11 A schematic diagram of the integrated test bench and copper bird integration solution provided by the present invention;

[0039] Fig.12 A schematic diagram of the first type of iron bird solution architecture provided by the present invention;

[0040] Fig.13 This is a schematic diagram of the second type of iron bird solution architecture provided by the present invention. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0042] See also Figure 1 The present invention provides an aircraft system integrated test bench, which is used to coordinate different aircraft system test benches to conduct linkage integrated experiments, including a simulated flight system, an integrated control and test auxiliary system, a data acquisition and analysis system, a software testing 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 tandem system;

[0043] 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;

[0044] 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, respectively, 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;

[0045] Among them, the power plant system test bench is electrically connected to the reflective memory network and the wiring and connection system, the atmospheric inertial navigation system test bench is electrically connected to the reflective memory network and the wiring and connection system, the cabin information system test bench is electrically connected to the reflective memory network and the wiring and connection system, the iron bird test bench is electrically connected to the reflective memory network and the wiring and connection system, the copper bird test bench is electrically connected to the simulated power supply and distribution system and the wiring and connection system, and each sub-operation module of the airborne system test bench is electrically connected to the wiring and connection system.

[0046] The comprehensive control and test auxiliary system of this embodiment provides control functions for test-related management for the system comprehensive test bench. It mainly includes: test bench control and its health monitoring, test process management, configuration management, test ICD design management tools, I / O configuration management, remote communication management, and clock management. The test bench control and its health monitoring function can intuitively display the test system status information, and help test personnel manage the entire test environment through easy-to-use operation pages; the test process management function is responsible for planning, organizing and supervising the entire test process to ensure that the test is carried out in an orderly manner as planned; the configuration management function is used to record, track and manage test specimens and various configuration information in the test environment; the test ICD design management function is mainly used to manage ICD data; the I / O configuration management function can identify the system I / O hardware resources and support users to flexibly configure the corresponding relationship between ICD and I / O resources; the remote communication management function can remotely control the test resources and realize one-click control of the start and stop of all service programs; the clock management function synchronizes the clock system of the test bench to ensure that time-sensitive test activities can be carried out accurately.

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

[0048] The IO interface resources are based on the PXI design concept and adopt the interface module plus chassis controller mode. The IO interface module mainly includes the corresponding bus or non-bus physical interface. When selecting the IO interface module for comprehensive testing, the corresponding IO interface resource margin is reserved. At the same time, the IO interface resources adopt an extensible design to support subsequent incremental expansion of test resources and test equipment to meet compatibility requirements.

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

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

[0051] The simulated power supply and distribution system provided in this embodiment is as follows Figure 3 As shown, the simulated power supply and distribution system has high simulation accuracy, flexible power regulation capability, and seamless switching interface with the real power system;

[0052] The AC main control cabinet provides power input for the DC power supply and AC power supply; the DC power supply can convert 380V three-phase AC or 220V single-phase AC into 28V DC to achieve 28V power supply; the DC voltage regulating power supply can achieve 28V power supply voltage regulation (4 channels), with a voltage regulation range of 17V~32V, which meets the flight control test requirements; the AC power supply can convert 380V three-phase AC or 220V single-phase AC into 115V AC to simulate 115V, 380Hz~800Hz variable frequency AC power supply; the AC voltage regulating power supply can convert 380V three-phase AC or 220V single-phase AC into three-phase AC with a rated output voltage of 115V (voltage adjustment range 0-266V) and a wide frequency of 0-2650Hz to simulate the output of PMG on a real aircraft, with a rated output power of 2KVA.

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

[0054] The analog power supply and distribution system supports remote or manual shutdown control of each power supply channel. Remote shutdown method: Introduce a remote control module PLC (programmable logic controller) to receive remote commands and control the circuit breaker in the distribution box. Use network communication technology (Ethernet) to connect the remote control module with the host computer software to achieve remote monitoring and control. Manual shutdown control: Set a manual operation switch on the distribution box to allow on-site personnel to directly operate the circuit breaker for shutdown control. The manual operation switch and the remote control module are interlocked to ensure that manual operation is impossible in remote control mode, or remote control is impossible in manual operation mode.

[0055] For AC power channels that require variable frequency control, a frequency converter is installed in the distribution box. The frequency converter has a remote communication interface (RS485) for receiving remotely set frequency parameters. After receiving the frequency parameters, the frequency converter adjusts the output voltage and frequency according to the parameters to achieve variable speed control of the AC motor.

[0056] Wiring and connection system architecture Figure 4 As shown in the figure, the wiring and tandem system is designed to dynamically configure the test configuration according to different test requirements in the aircraft system comprehensive test. It can meet the test personnel's needs during the test process, and flexibly switch the test object through program control according to actual needs, realizing seamless conversion from real parts to simulated parts, greatly reducing the need for manual intervention in configuration modification.

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

[0058] like Figure 4 As shown in the figure, the wiring and connection system is designed for program-controlled switching between real parts and simulated parts during the comprehensive test of aircraft, and is divided into two parts: wiring and connection system. The wiring system includes advanced wiring switching equipment, which adopts modular design and considers compatibility factors to facilitate users to flexibly configure and expand according to test requirements. At the same time, the supporting wiring switching software provides an intuitive and easy-to-use operation interface, and users can easily achieve fast switching and monitoring of signals, greatly improving test efficiency and accuracy. The wiring system can support the switching of ARINC664 bus signals, ARINC429 bus signals, discrete signals, and analog signals (including AD\LVDT\RVDT\Resolver, etc.) with simulated parts to ensure seamless switching of experimental configurations during the test.

[0059] The tandem system integrates a separation panel, a cable management box, and a circuit breaker test panel, which are used for block processing of lines, signal extraction, orderly organization, and rapid location and troubleshooting of faults during testing, ensuring the integrity and reliability of the test environment and further improving the system's integration and testing capabilities.

[0060] Functional modules are divided into Figure 5As shown, the main function of the integrated wiring software is to realize the program-controlled switching operation of the wiring equipment, provide an HMI interface and operation services for interaction with the user, and be able to perform configuration management and switching of the test configuration. At the same time, it provides cable management functions within the test bench and uniformly manages, revises and queries the cable information in the test environment.

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

[0062] 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 module; wherein the model dynamic simulation unit is used to perform dynamic simulation control on 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 by injecting or receiving excitation data into each exciter device of the airborne system simulation model;

[0063] like Figure 6 As shown, this embodiment achieves a high degree of simulation effect and real-time performance through the cooperation of the engineering cockpit, I / O resource pool, airborne system equipment, experimental network, and visual and simulation control systems. The I / O resource pool is not only connected to the engineering cockpit, but also communicates with the airborne system equipment and the experimental network in real time. Because the real-time data of the airborne system equipment can be directly involved in the simulation process, the engineering cockpit can simulate the real flight environment, thereby improving the accuracy and credibility of the simulation.

[0064] On the test network, the visual and simulation control systems are running. The visual software is responsible for generating realistic flight scenarios, including environmental factors such as terrain, weather, and lighting, to provide operators with an immersive visual experience. The simulation control system includes a high-profile simulation model and an airborne system simulation model, 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 incentive system architecture is as follows Figure 7 As shown in the figure, the simulation excitation system plays a key role in the aircraft system integrated test bench. Its functions include model dynamic simulation, data excitation, accompanying flight and re-injection, and exciter management software, which provide powerful simulation and excitation functions for the aircraft system integrated test bench. The hardware components of the simulation excitation system include: real-time simulation computer, timer board, VMIC reflection board and real-time network switch.

[0066] Through the application of simulation incentive systems, the civil aviation field can more effectively integrate and verify systems during the design, development and operation stages, improve the safety, reliability and performance of aircraft systems, and reduce development costs and time.

[0067] Dynamic flight simulation architecture is shown below Figure 8 As shown in the figure, during the dynamic simulation flight, the aircraft system model can simulate the logical functions and input and output interfaces 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 the onboard equipment to achieve dynamic joint simulation based on the flight mission.

[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 stimulus software is divided into five modules: user management module, project management module, network configuration module, stimulus configuration module, sending sequence configuration module, and system management module. The user management module is used for user information management, user authentication and authorization; the project management module is used to save and manage the test configuration used by data stimulus; the network configuration module is used to configure IO interface parameters and the mapping relationship between ICD documents and IO interfaces; the sending sequence configuration module is used to obtain ICD documents, configure and save instruction set configurations, and the system management module is used for data stimulus log information management and user data stimulus operation guidance; the test configuration contains the real version information and the test environment version information, and the instruction set configuration is used to save the instruction set used by data stimulus.

[0070] The data stimulus software can obtain the ICD and IO configuration information defined by the integrated control and test auxiliary system, and edit the stimulus message based on the ICD format, send the stimulus data to the test network through the synchronous network of the upper and lower computers, and convert it into a bus signal through the interface resources, so as to interact with the real device.

[0071] As the core software of the aircraft system integrated test bench, the data stimulus software has more functions than basic data acquisition and transmission. It can also seamlessly integrate the integrated control and test auxiliary systems, and accurately capture and analyze ICD and IO configuration information.

[0072] Through the collaborative working mechanism of the upper and lower computers, the software can efficiently push the edited stimulus 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 and reliability of data during transmission, laying a solid foundation for subsequent data interaction with real hardware devices (real parts).

[0073] Furthermore, the data stimulus software is adapted to various IO boards installed on the lower computer, including but not limited to ARINC664, ARINC 429, etc., to achieve comprehensive support for data of different interface types. At the data processing level, the software can automatically complete the task of packaging, scheduling and sending application layer data to the specified board, realize the simulation of complex data flows, and effectively reduce the test preparation cycle and cost.

[0074] In addition, the data stimulus software's stimulus status statistics and visualization functions can display key data indicators in real time during the test, helping testers quickly locate problems and evaluate system performance. By integrating fault diagnosis and prediction algorithms, the software can also bypass the stimulus data and provide early warnings when abnormal data appears.

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

[0076] The companion flight and refill software adopts C / S architecture. The upper computer deploys the client software, and the lower computer deploys the server program for underlying data scheduling and communication with the flight simulation model. The client is used to implement simple functional logic, including engineering management, flight scene configuration, flight data monitoring, flight command control, data import, refill control, refill configuration, processing requests and other functions. 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 communicating 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 to store and read and write data of the entire companion flight and refill software.

[0077] The companion flight and recharging system adopts C / S (client / server) architecture design to realize efficient data processing and communication mechanism. In the system, the host computer serves as the control center, deploys client software, provides an intuitive and easy-to-use user interface, and supports a series of core functions, including: project management (project creation, editing and deletion), customized configuration of flight scenes (terrain, weather, obstacles, etc.), real-time flight data monitoring (dynamic display of key parameters such as speed, altitude, attitude, etc.), precise control of flight instructions (take-off, landing, route adjustment, etc.), data import and export functions (supports data files in multiple formats for easy data backup and sharing), and recharging control modules, allowing users to flexibly configure recharging parameters and achieve precise intervention in the simulation environment. In addition, the client also integrates a request processing system to receive user operations and forward 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 and seamless communication with the flight simulation model. The server program can efficiently process execution requests from the upper computer client, dynamically create and manage processes, and ensure the reasonable allocation and recovery of system resources. Its built-in interface management system uses a standardized protocol to achieve two-way communication with the flight simulation model. It can not only inject various control data and parameters into the simulation model in real time, but also receive and parse the output data of the simulation model, providing accurate and timely feedback to the upper computer.

[0079] In order to ensure the integrity and security of data, the system integrates a high-performance database management system to store all data 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, ensuring rapid response to data access and maintenance of data consistency, providing a solid foundation for the 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. By sending control instructions to the exciter and receiving feedback data, it can centrally configure, modify and monitor the working mode, frequency and other signal status of each subsystem exciter. There are two specific usage scenarios:

[0081] When the software is in static configuration mode, the experimenter can manually configure various actuator parameters through the software interface, and send and receive 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 actuator.

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

[0084] The data acquisition and analysis software consists of a data monitoring module, a data storage module and a special protocol analysis module. It can monitor and store data on the ARINC664 bus and ARINC429 bus, and supports ARINC661 protocol analysis and ARINC429 data acquisition and analysis encapsulated in Block messages.

[0085] The data storage module mainly supports the 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 the storage configuration information and control instructions transmitted by the front end, the start and stop control of the bus storage service is realized, and the collected and stored data is stored in the database.

[0086] The special protocol parsing module supports the collection and parsing of ARINC661 protocol and ARINC429 data encapsulated in Block messages.

[0087] The user management module supports the management and maintenance of user information. When logging into the software, you need to enter the user account and password to access it, thereby ensuring data security.

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

[0089] Collaborative testing software (i.e. the "test process automation tool module" in the bidding requirements, hereinafter referred to as collaborative testing software)

[0090] The collaborative testing software has the function of automatically obtaining deployment packages. It can automatically obtain the software packages and codes required for deployment from the specified location. This part is implemented at the bottom layer through the Shell script language. The script will specify the source and target location of the software package.

[0091] This software also has automated operation and maintenance tools, which can perform batch system configuration, batch program deployment, batch command execution, etc. The collaborative testing software has a built-in test report generation function, which can automatically collect the test run results and generate a structured report, which is finally saved in HTML format to the specified output path.

[0092] Network performance monitoring software

[0093] Network performance monitoring software is used to collect, analyze and display network indicators such as the operating status of network devices, response time, network bandwidth, etc. in real time, and generate and display 3D views, line charts, pie charts, curve charts and bar charts to show the network's connectivity status, traffic and bandwidth usage, etc. The software can help developers and operation and maintenance teams to identify problems in a timely manner and conduct effective management and optimization.

[0094] After the test is completed, indicators such as latency, packet loss rate, and jitter will be automatically calculated. 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 specifications based on interface control documents to simulate and verify message transmission 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 generation and sending of simulated data will be carried out according to the ICD, and multiple Pub_Sub test scripts can be executed 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 the target IP address, click a button to execute the Ping command to detect the connectivity and response time of network devices, 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 a graphical user interface, allowing users to view the status and performance of the device in real time.

[0101] like Fig. 9 As shown, 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 testing software (i.e. the "test process automation tool module" in the bidding requirements, hereinafter referred to as the collaborative testing software) serves as an automated testing tool and deployment tool, and mainly realizes functions such as uploading and downloading deployment packages, software deployment, and generating test reports.

[0103] The collaborative testing software has the function of automatically obtaining deployment packages. It can automatically obtain the software packages and codes required for deployment from the specified location. This part is implemented at the bottom layer through the Shell script language. The script will specify the source and target location of the software package.

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

[0105] As an automated testing tool and deployment tool, the collaborative testing software mainly implements functions such as uploading and downloading deployment packages, software deployment, and generating test reports. The software functional modules are divided into remote node management, deployment package upload / download, software deployment, and test report generation. The remote node management 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 to monitor the traffic and bandwidth of the integrated modular avionics (IMA) bus network, and is classified and monitored according to the device type and network topology of the A and B networks. It collects, analyzes and displays network indicators such as the operating status, response time, and network bandwidth of network devices in real time, and generates and displays 3D views, line charts, pie charts, curve charts, and bar charts to show the connectivity status, traffic, and bandwidth usage of the network. This part is implemented using data visualization libraries and tools.

[0107] Network performance monitoring software can help developers and operation and maintenance teams identify problems in a timely manner and conduct effective management and optimization; it can monitor the working status of the device, including the device's online / offline status, normal / abnormal status, and monitor specific events, log messages, and CAS / INFO messages generated by the device; after the test, it will automatically calculate the delay, packet loss rate, jitter, etc., and these indicators can also be obtained in real time during the experiment.

[0108] Pub_Sub test software can automatically generate test scripts that meet the specifications based on the interface control document and the attributes of the Pub_Sub header to simulate and verify the message transmission 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 resources are called to simulate the generation and sending of data, and then the data sent by the acquisition end system is analyzed by calling the platform I / O resources, and finally the analysis content is automatically judged to draw a conclusion on whether the test has passed. The software can execute multiple Pub_Sub test scripts in batches, which can improve the efficiency and automation of the test; finally, a test report is generated to count indicators such as network delay and packet loss rate.

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

[0111] The software supports calling the Ping command of the operating system, sending ICMP requests, and parsing ICMP responses to perform fast connectivity tests and detect the connectivity and response time of network devices. It also provides a user-friendly interface that allows users to execute the Ping command under a certain IP device and view the parsing results of the reply message.

[0112] The software provides SNMP management tools to obtain and set MIB data from the device through the SNMP protocol, including register status, configuration table, pulse port, etc. It provides a graphical user interface to enable customers to easily view and analyze MIB data, and supports real-time data updates to reflect device status changes.

[0113] The ICMP / SNMP test software manages network devices through SNMP and ICMP protocols, and finally displays the feedback MIB parameter values ​​through a graphical user interface, allowing users to view the status and performance of the device in real time. The software is divided into four modules, namely, importing the device list, ICMP tools, SNMP tools, and performance monitoring. Importing the device list means displaying device details. ICMP tools include Ping tools and test result display. SNMP tools include GET commands, SET commands, polling configuration, and MIB library management. Performance monitoring means parameter echo.

[0114] Avionics system integration Fig.10As shown in the figure, the avionics system interface includes a variety of high-performance communication protocols including the ARINC664 standard, as well as traditional ARINC429 and ARINC825 interfaces. In addition, it is also compatible with analog signals, discrete signals, and standard Ethernet interfaces. These diverse interface designs are designed to efficiently and stably drive airborne avionics equipment (RDIU remote data interface unit, ADN remote switch, ARS radio interface device, RIU remote interface unit, etc.) and various avionics equipment 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 equipment, the avionics system uses the ARINC825 interface as the standard communication interface, which not only has high-speed transmission capabilities, but also ensures the real-time and reliability of data transmission. Through this interface, the system can accurately drive the control board components to achieve real-time adjustment and display of flight parameters; at the same time, it also supports signal acquisition and remote control of key equipment such as dimming control power supply, providing pilots with a fully functional and easy-to-operate cockpit environment, thereby improving the safety and efficiency of flight operations.

[0116] Aircraft system tests include copper bird, electric bird and iron bird. The copper bird is used to test the power supply system of the aircraft, such as power generation and distribution. The copper bird test bench restores the real state of the power supply and distribution system on the aircraft in a one-to-one ratio to the real aircraft to install equipment and verify the correctness, integrity and safety of the implementation of each system function. Among them, the system comprehensive test bench and the copper bird integration solution are as follows Fig.11 As shown, the blue area represents the construction scope of the system comprehensive test bench.

[0117] The iron bird is a test of the mechanical system of the aircraft, such as the simulation test of the failure of the landing gear and wings. It is an essential key test facility for the integration of aircraft systems, optimized design, airworthiness certification, delivery and operation, and continuous airworthiness. The iron bird is made of hundreds of steel bars staggered, wired, and welded. It is similar to the appearance of the aircraft it simulates, with the same layout, and is very close to the main load-bearing structures of the aircraft, such as the front beam, rear beam, and frame.

[0118] The first type of solution uses the system integrated test bench avionics and flight simulation system, as well as the iron bird FCE, FSECU, hydraulics, landing gear, brake system, rear-end actuators, rudders, etc. for testing. The system integration architecture is as follows: Fig.12 As shown in the figure; the second type of scheme uses the system integrated test bench avionics real parts, FCE, FSECU, HLRM real parts and flight simulation system, as well as the use of iron bird actuators, rudders, etc. to carry out testing. The system integration architecture is as follows Fig.13 shown.

[0119] The above embodiments only express preferred implementation modes, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention.

Claims

1. An aircraft system integrated test bench, used to coordinate with different aircraft system test benches to conduct linkage integrated experiments, characterized in that: Including 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, respectively, 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 connection system, the atmospheric inertial navigation system test bench is electrically connected to the reflective memory network and the wiring and connection system, the cabin information system test bench is electrically connected to the reflective memory network and the wiring and connection system, the iron bird test bench is electrically connected to the reflective memory network and the wiring and connection system, the copper bird test bench is electrically connected to the simulated power supply and distribution system and the wiring and connection system, and each sub-operation module of the airborne system test bench is electrically connected to the wiring and connection system.

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 module; wherein the model dynamic simulation unit is used to perform dynamic simulation control on 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 by injecting or receiving excitation data into each exciter device of the airborne system simulation model; The simulation operation platform provides a simulation operation function, 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 perform operational interaction 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 perform three-dimensional dynamic display of the simulation operation process of the simulation operation platform.

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 an avionics core system, a communication system, a navigation system, an integrated monitoring system, an airborne maintenance system, a flight recording system, a high lift system and a hydraulic system.

5. The aircraft system integrated test bench according to claim 1, characterized in that: The comprehensive control and test auxiliary 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, and 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 primary distribution unit and a secondary distribution unit; wherein the primary distribution unit is used for busbar power supply simulation, including a primary DC distribution box and a primary AC distribution box; the secondary distribution unit is used for real equipment power supply simulation, including a secondary DC distribution box and a secondary AC distribution box, and the distribution controller is used for 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 connection system includes a wiring system, a circuit breaker test panel and a connection 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 signal circuit break test; The junction system includes a separation surface and a wire management box, wherein the wire management box is used to provide a wire harness junction between the real equipment and the test bench, and the separation surface includes a copper bird junction separation module, an iron bird junction separation module, a MiniRig junction separation module and other system junction separation modules; Among them, the copper bird connection and separation module is used to connect to the copper bird test bench, the iron bird connection and separation module is used to connect to the iron bird test bench, the MiniRig connection and separation module is used to connect to each sub-operation module, and the other system connection and 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 connected to 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. The aircraft system integrated test bench according to claim 1 is 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.

Images