CN117193249A - Complex avionics system test and integrated verification platform - Google Patents
Complex avionics system test and integrated verification platform Download PDFInfo
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Abstract
The invention discloses a complex avionics system test and integrated verification platform, which comprises test equipment, a wiring matrix and a software system, wherein the test equipment comprises workstation computer equipment, bus interface simulation equipment and a comprehensive wiring rack, provides a hardware environment for test total control, realizes the bus communication functions and simulation of ARINC664 and ARINC429, and simultaneously provides a test cable for crosslinking with tested equipment; the wiring matrix comprises a wiring switching subsystem and a signal simulation subsystem, and is used for providing wiring switching of simulation signals and real equipment, including wiring switching of various buses and simulation excitation functions of other signals except ARINC664 and ARINC 429; the software system runs on the test equipment and is used for controlling the test equipment and the wiring matrix to carry out interface test and function verification on the tested equipment. The invention can realize different test configurations of the aircraft avionics system, thereby completing the system verification of different levels of the system.
Description
Technical Field
The invention relates to the field of ground tests of aircraft avionics systems, in particular to a complex avionics system test and integrated verification platform.
Background
Subsystems such as navigation, radio and flight control of modern aircraft gradually develop from independent operation of each function to high integration; meanwhile, the functions of the aircraft avionics system are increasingly complex, and the requirements on the system are increased. The above reasons lead to complex cross-linking and cooperation relationships among systems and increased technical difficulties in system testing and integrated verification. Therefore, the effective test strategy is researched, and the efficient avionics testing and integrated verification platform is established, so that the development and troubleshooting time of the avionics system can be greatly reduced.
Disclosure of Invention
The invention aims to provide a complex avionics system testing and integrated verification platform for realizing the module testing and integrated verification functions in the complex avionics system; providing real equipment access through the comprehensive wiring system, and completing interface test and function verification of a real avionics system through peripheral excitation environment simulation and data acquisition; configuration management and ICD management are provided, and different test configurations of the aircraft avionics system are realized, so that system verification of different levels of the system is completed.
The invention aims at realizing the following technical scheme:
a complex avionics system test and integrated verification platform comprises test equipment, a wiring matrix and a software system, wherein the test equipment comprises workstation computer equipment, bus interface simulation equipment and a comprehensive wiring rack, provides a hardware environment for test total control, realizes the bus communication function and simulation of ARINC664 and ARINC429, and simultaneously provides a test cable for crosslinking with tested equipment; the wiring matrix comprises a wiring switching subsystem and a signal simulation subsystem, and is used for providing wiring switching of simulation signals and real equipment, including wiring switching of various buses and simulation excitation functions of other signals except ARINC664 and ARINC 429; the software system runs on the test equipment and is used for controlling the test equipment and the wiring matrix to carry out interface test and function verification on the tested equipment.
Preferably, the workstation computer device comprises a desktop workstation, a simulation server and a data server; the communication network is composed of a clock network, a control network and a data network which are physically independent;
the control network is responsible for realizing test control and test data transmission between the upper computer and the lower computer; the upper computer is workstation computer equipment and test software, and the lower computer comprises bus interface simulation equipment, a comprehensive wiring rack, a wiring switching subsystem and a signal simulation subsystem;
the clock network is responsible for realizing clock synchronization among all signal excitation devices; the signal excitation equipment comprises a simulation server, bus interface simulation equipment and a signal simulation subsystem, wherein time synchronization between the signal excitation equipment is realized through a master-slave working mode of an IRIG-B interface, and unified time service is carried out by a time synchronization source to complete unified clocks of each bus interface simulation equipment.
The data network is responsible for realizing the business data communication of each bus data between each lower computer and the real tested equipment, thereby completing various experiments.
Preferably, in the control network, the simulation server and the data server are configured by adopting a double network card, the desktop workstation, the simulation server and the data server are in the same local area network, and the simulation server, the data server and the lower computer are in another local area network.
Preferably, in the clock network, a master clock IRIG-B card is installed by the simulation server and is responsible for reading the current system time and distributing the current system time to all bus interface simulation devices and signal simulation subsystems which are connected currently.
Preferably, in a data network, aiming at ARINC664 exchange buses, an ARINC664 simulation board card is configured in a bus interface simulation device to realize data excitation, a cable connector is configured in a comprehensive wiring rack to be used as an ARINC664 bypass switcher for switching ARINC664 signals between a real part and an imitation part, and data is mirrored into an uplink path and a downlink path through a physical PHY chip to be led out for data acquisition;
and a physical parallel connection mode is provided for various low-speed signals, so that the networking of the low-speed signal data network is realized.
Preferably, the software system comprises wiring management software, test master control software, configuration management software, data excitation and monitoring, automatic test software and comprehensive simulation software;
the wiring management software is matched with the comprehensive simulation software to control the wiring switching subsystem to perform real simulation equipment switching, channel mapping and bypass test management;
the test master control software realizes the resource monitoring of the whole wiring matrix, checks the working state of test resources and can control a workstation computer;
configuration management software provides system test configuration, specifically comprises wiring configuration, distribution configuration, IO association and configuration, and ICD import and resource mapping;
the data excitation and monitoring software realizes ICD-based data excitation and monitoring, provides various data excitation modes, and can provide related data statistics results for different buses; in addition, the data server can be controlled to store all acquired data and play back the data;
the automatic test software can realize the management, execution and automatic test report generation of the automatic test cases; the user test case and ICD data import are supported, and the ICD-based automatic test is realized;
the comprehensive simulation software can integrate a simulation model, realize a simulation configuration function, map simulation variables to a real I/O interface, and package the simulation variables according to a real ICD to realize semi-physical simulation; in addition, a monitoring management function comprising model state control, switching and load distribution is also provided.
During single-equipment testing, the tested equipment is connected to the comprehensive wiring rack of the testing equipment; in the software system, the test equipment is set as a real part, the signal simulation subsystem crosslinked with the tested equipment is set as a simulation part to complete wiring switching, and the data excitation, the test case and the simulation model of the related ICD are issued to the tested equipment to complete simulation data excitation transmission, data acquisition and fault injection.
Further, during multi-equipment testing, a plurality of tested equipment are connected into a comprehensive wiring rack of the testing equipment; the method comprises the steps of setting test equipment as a real part in a software system, setting a signal simulation subsystem crosslinked with tested equipment as a simulation part to complete wiring switching, completing data acquisition and testing on a data path between the tested equipment by issuing data excitation, test cases and simulation models of related ICDs to a tested unit, and realizing logic function analysis according to the acquired data.
Further, during system level testing, tested equipment is configured as real equipment in a software system, the configuration of the user ICD is completed by loading, and data analysis is performed through an acquisition channel.
The invention has the beneficial effects that:
1. aiming at the problems of large scale of test equipment and very complex network topology in the development of a large-scale aircraft, the platform adopts three-network physical independent design of a control network, a clock network and a data network. The system stability is improved and the system test accuracy is ensured while the data transmission quality is ensured.
2. The platform is designed based on a network, supports expandability and is convenient for adding modules; the wiring matrix adopts a flexible and easy-to-adjust design, all the contained software is independent of the tested product, and when the wiring relation is changed, the software can be quickly and adaptively adjusted by configuring the system software; for possible ICD changes, no change is needed and only configuration is performed according to the ICD. Based on the design, the platform can realize quick expansion verification.
3. The incremental integration strategy of single-device testing, multi-device testing and system level testing is adopted to realize single-device logic function verification, inter-device logic function analysis and full-system device function testing layer by layer, so that the troubleshooting efficiency is effectively improved, and the device functions are fully verified in the system integration process.
Drawings
FIG. 1 is a system architecture of a complex avionics system test and integrated verification platform.
Fig. 2 is a schematic diagram of the constitution of the test apparatus.
Fig. 3 is a wiring matrix configuration.
FIG. 4 is a wiring matrix sub-module data relationship.
Fig. 5 is a schematic diagram of a tri-net.
FIG. 6 is a flow chart of the system test operation.
Fig. 7 is a schematic diagram of a single device test scenario.
FIG. 8 is a schematic diagram of a multi-device test scenario.
FIG. 9 is a schematic diagram of a multi-device test scenario.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples.
Referring to fig. 1, a complex avionics system testing and integration verification platform shown in this embodiment includes a testing device, a wiring matrix, and a software system.
The test equipment provides module function test and integrated verification functions inside the avionics system, is mainly used for providing a hardware environment for test total control, realizes bus communication functions and simulation of ARINC664 and ARINC429, and provides a test cable for crosslinking with tested equipment. The wiring matrix is primarily used for signal coupling configuration of the simulation device to the real device, which provides for experimental wiring switching, including wiring switching of various buses and simulation excitation functions of signals other than ARINC664, ARINC 429. The software system is used for carrying out interface test and function verification on the tested device. The devices under test include, but are not limited to: the system comprises a core processing system, a display control system, an electromechanical information acquisition system, a situation sensing and video processing system, an L-band comprehensive system, a flight parameter and cabin audio recording system, a high-frequency communication system, a very high-frequency communication system, a satellite communication system, a comprehensive automatic tuning system, an audio comprehensive system, a radio navigation system, a radio altimeter, a Beidou navigation system, an atmospheric data system, an inertial reference system, a navigation posture reference system, a comprehensive backup instrument system, a weather radar system and the like, wherein the situation sensing and video processing system, the L-band comprehensive system, the flight parameter and cabin audio recording system, the high-frequency communication system, the very high-frequency communication system, the satellite communication system, the comprehensive automatic tuning system, the audio comprehensive system, the radio navigation system, the radio altimeter, the Beidou navigation system, the atmospheric data system, the inertial reference system, the navigation posture reference system, the comprehensive backup instrument system, the weather radar system and the like are determined according to the requirements of a verification airplane.
(1) Test equipment
Referring to fig. 2, the test equipment is composed of three subsystems of a bus interface simulation device, a workstation computer device and a comprehensive wiring rack device.
The workstation computer equipment comprises a plurality of desktop workstations, a plurality of simulation servers and a plurality of data servers, the specific number of the desktop workstations can be increased or decreased according to actual use conditions, and the desktop workstations realize data exchange with the simulation servers and the data servers through Ethernet.
The desktop workstation provides a hardware platform for a client of the software system, and the software system CAN send test configuration to the bus simulation interface device through the desktop workstation and control the bus interface simulation device to complete simulation of ARINC664, ARINC429 and CAN bus data;
the system comprises a plurality of simulation servers, a plurality of control servers and a plurality of control servers, wherein the simulation servers are used for providing a service end of a software system and matched with a client end of the software system on a desktop workstation, are mainly responsible for engineering management and resource monitoring (including health management, wiring, power distribution, lower computer control, ICD management and the like), provide a storage function of configuration files of bus interface simulation equipment and configuration files of a wiring matrix, distribute and control signals to the bus interface simulation equipment, and realize the butt joint of the bus simulation interface equipment and avionics system tested equipment; in addition, the simulation server can provide a data access interface through matched software, and report the tested equipment state and data issuing condition of the avionics system to a software system on a desktop workstation.
And a plurality of data servers for storing test data.
The bus interface simulation equipment comprises three types of bus interface simulation equipment, namely ARINC429, ARINC664, CAN and the like, and mainly comprises bus data in an avionics system. The bus interface simulation equipment completes system configuration and configuration issuing through configuration set by a simulation server in the workstation computer equipment or loading stored configuration files, and realizes butt joint of the bus interface simulation equipment and tested equipment through signal distribution and control of the simulation server to complete data test.
The comprehensive wiring rack equipment comprises equipment installation racks, test cables, equipment cabinets, switches and the like, wherein the installation racks are used for deploying all tested equipment of the avionics system, the test cables are used for crosslinking the test equipment and the tested equipment (all avionics equipment), and the equipment cabinets and the switches provide signal adaptation of equipment interfaces and construction of a control network.
In the three parts, the workstation computer equipment is interconnected with the bus interface simulation equipment through the Ethernet; the bus interface simulation device is matched with the comprehensive wiring rack device through an avionics bus interface, and exchanges test data (664/429/CAN and the like) with tested devices of an avionics system arranged in the comprehensive wiring rack.
(2) Wiring matrix
The wiring matrix is mainly used for signal connection configuration of simulation signals and real equipment, and the core functions comprise: the signal access of the tested product, the program control switching of the true part signal and the simulation of the avionic interface are provided. As shown in fig. 3, the wiring matrix includes a wiring switching subsystem and a signal simulation subsystem. The wiring switching subsystem is responsible for realizing true simulation switching of signals including ARINC664, ARINC429, ARINC818, ARINC717, RS422/RS485, discrete quantity, analog quantity and the like, signal wiring and interface adaptation, and completing corresponding signal conditioning for the discrete quantity and the analog quantity. The signal simulation subsystem needs to provide data transceiving functions of ARINC818, ARINC717, RS422/RS485, discrete quantity, analog quantity and the like.
The wiring switching subsystem comprises two types of wirings, namely high-speed signals and low-speed signals, provides functions of signal switching, signal bypass and the like, and completes physical switching of test configuration, mapping of a physical signal channel and an aircraft domain channel and interface adaptation. The high-speed bus signal wiring is aimed at an ARINC664 bus, and system configuration switching and bypass acquisition are realized on the premise of ensuring normal signal communication; the low-speed signal wiring realizes system configuration switching and bypass acquisition on the premise of ensuring normal communication of ARINC429, ARINC717, RS422/485 and discrete quantity signals.
The signal simulation subsystem provides all signal simulation except ARINC664, ARINC429 and CAN signals, including ARINC717, ARINC818, RS422/485, discrete quantity (OPEN/GND, 28VDC/OPEN, 28 VDC/GND) and analog quantity and the like, mainly comprises a flight data recorder (black box), video data and the like, and the data interaction with tested equipment needs to be converted into ARINC429 or ARINC664 data through the wiring switching subsystem, so that ICD-based data transceiving and online analysis are realized, and the signal simulation subsystem provides simulation and acquisition of other buses except the 3 buses.
(3) Software system
The software system relies on a workstation computer to control the test equipment to provide ARINC664 and ARINC429 signal simulation and collection, and the control signal simulation subsystem provides other simulation signals. The software system is divided into a client and a server, the client is responsible for providing a graphical operation interface for a user on a desktop workstation for the user to perform test operation and monitoring, and the server is used for completing actual test operation and monitoring on a simulation server.
The software system comprises modules such as wiring management software, test master control software, configuration management software, data excitation and monitoring, automatic test software, comprehensive simulation software and the like, and adopts a modularized design concept, so that the system architecture is clearer and easier to understand, and meanwhile, the system architecture can be easier to manage in the later implementation process, and the time and quality controllability of projects is enhanced. The method is concretely realized as follows:
the wiring management software is matched with the comprehensive simulation software to control the wiring switching subsystem to perform real simulation equipment switching, channel mapping and bypass test management. The simulated object comprises the avionics system equipment to be tested and avionics system external equipment. When the avionics system device under test is used as a simulation object, it is typically used as input to other avionics systems under test or to verify the correctness of the ICD; when the avionics system external equipment is used as a simulation object, the integrated verification of the tested avionics system is supported for simulating the input outside the avionics system.
The test master control software realizes the resource monitoring of the whole wiring matrix, checks the working state of test resources, and can control the workstation computer by one key. Furthermore, the laboratory layout is provided graphically.
Configuration management software provides system test configuration, including in particular wiring configuration, power distribution configuration, IO association and configuration, and ICD import and resource mapping.
The data excitation and monitoring software realizes ICD-based data excitation and monitoring, provides various data excitation modes, and can provide related data statistics results for different buses; furthermore, the data server can be controlled to store all collected data as well as data playback.
The automatic test software can realize the management, execution and automatic test report generation of the automatic test cases; the user test case and ICD data import are supported, and the ICD-based automatic test is realized;
the comprehensive simulation software can integrate simulation models (an airplane subsystem, environment simulation, a flight simulation model and the like), realize a simulation configuration function, map simulation variables to a real I/O interface, and package according to a real ICD to realize semi-physical simulation. In addition, a monitoring management function such as model state control, switching and load distribution is provided.
The user realizes wiring switching, system configuration, ICD configuration and data excitation and acquisition configuration through a software system, then the configuration is issued to a signal simulation subsystem, all hardware devices in the signal simulation subsystem are connected to the tested device through the wiring switching subsystem, data excitation and acquisition are performed according to the issued ICD configuration, and data monitoring is realized through online analysis. The tested system realizes physical connection through an interface adaptation and signal conditioning module in the wiring switching subsystem.
In addition, the wiring control switching command and the switching state in the software system are directly transmitted through the RS485 bus of the wiring switching subsystem.
And (3) carrying out relation confirmation between test data and received data through the testing process of the human testing equipment in the ring, thereby completing the functional verification of the tested system.
Because the platform is oriented to the large-scale aircraft avionics system, the scale of the test equipment and the wiring matrix is large, the network topology is very complex, and the stability of the system directly determines the effect of completing the integrated verification test of the avionics system by a user. In order to improve the stability of the system and ensure the accuracy of the system test, referring to fig. 5, the complex avionics system test and integrated verification platform is specially designed with three-network physical independent design. The communication network is composed of a clock network, a control network and a data network which are physically independent, so that the data cannot be affected mutually.
The control network is responsible for realizing test control and test data transmission between the upper computer and the lower computer. The upper computer is a workstation computer device and test software, and the lower computer comprises a bus interface simulation device, a comprehensive wiring rack and wiring switching subsystem and a signal simulation subsystem. The upper computer controls the lower computer through the control network, and meanwhile, because the system on-line monitoring is required to be completed, test data is required to be transmitted to the lower computer. In order to ensure that data can be stored in real time in the test process, the switch grouping design is realized through the double network card configuration of the simulation server and the data server. The desktop workstation, the simulation server and the data server are in the same local area network, and the simulation server, the data server and the lower computer are in another local area network, so that the blocking influence on the data checking of the upper computer is avoided when a large amount of data transmission is performed between the server and the lower computer.
The clock network is responsible for realizing clock synchronization among all signal excitation devices, so that the multi-node collaborative simulation external environment can be effectively realized. The signal excitation device comprises a simulation server, a bus interface simulation device and a signal simulation subsystem. The time synchronization between the signal excitation devices is realized through the master-slave working mode of the IRIG-B interface, and the time synchronization source performs unified time service to complete the unified clock of each bus simulation interface device. The simulation server is provided with a master clock IRIG-B card and is responsible for reading the current system time and distributing the current system time to all slave IRIG-B devices which are connected currently. The clock network synchronous frequency is 1 minute once, and provides an API to realize that a user can synchronize the system clock at any time according to actual needs.
The data network is responsible for realizing the business data communication of bus data such as ARINC664, ARINC429, CAN, discrete quantity, RS422/485 and the like between each lower computer and the real tested equipment, thereby completing various tests. The data network realizes respective networking among different buses through ARINC664 board card, ARINC429 board card and the like of the bus interface simulation equipment.
ARINC664 is high-speed signal, and provides special highly integrated terminal system equipment for ARINC664 exchange bus to realize data excitation; meanwhile, a wire arranging cabinet of the test cable in the comprehensive wiring rack and the cable connector are used as ARINC664 bypass switchers for switching ARINC664 signals between the real piece and the imitated piece, and data are mirrored into an uplink path and a downlink path through a physical PHY chip to be led out for data acquisition. In the ARINC664 data network, all devices are individually networked as they are connected through switches in the avionics system; for system testing, the data networking is realized by matching with a wiring matrix, and the configuration switching of simulation equipment and real equipment is completed.
For low-speed signals such as ARINC429, ARINC717, RS422/485, discrete quantity and analog quantity, a physical parallel connection mode is provided to realize the networking of the low-speed signal data network because the low-speed signals are not exchange buses.
The incremental integrated test method is adopted: the system test adopts an incremental integration strategy of single-device test, multi-device test and system level test, and verifies that the tested device is realized under the conditions of single-system functional requirement realization, interface and logic matching among subsystems, full-system function and function realization under the actual use scene.
The system test adopts an incremental integration strategy of single device test-multi-device test-system level test.
The system testing process mainly receives the data of the tested equipment by inputting the excitation data of the external simulation environment into the tested equipment, and completes the function verification of the tested equipment.
The system test flow is shown in fig. 6:
(1) Single device testing
The single-device test mainly aims at a certain tested device, establishes a peripheral simulation environment and realizes interface test and logic function verification of the single tested device. The single-device test is a functional black box test, and when a single device is tested, the peripheral device crosslinked with the single device is realized through a bus interface simulation device and a signal simulation subsystem, and simulation excitation data realizes data interaction with the tested device through a physical I/O bus. The test equipment is required to be connected with a real equipment table of test equipment (SUT); the wiring management software in the software system sets the test equipment as a real part, the signal simulation subsystem crosslinked with the tested equipment as a simulation part, and the wiring switching subsystem is configured through the data excitation and monitoring software, the automatic test software and the comprehensive simulation software, so that the settings of issuing relevant ICDs and the like to the tested equipment are realized. The test scenario is as in fig. 7:
the tested equipment is single system equipment, and because the sources of the received data of different tested equipment are different, the data which is required to be simulated and issued when the data is sourced from the same equipment are different, the test cases and the signal simulation subsystem in the test system are correspondingly different according to the different tested equipment. The simulation of the peripheral cross-linking environment of the tested equipment is realized through the comprehensive simulation software and the test total control software, simulation excitation data are sent, the bus interface function and performance of the tested equipment are tested, and the logic function verification of the tested equipment can be realized through the input script of the automatic test software.
The main functions of single system test and verification comprise three functions of simulation data excitation transmission, data acquisition, fault injection and the like, and multiple tests such as network access, interface function verification, performance evaluation and the like of tested equipment are realized.
At this time, aiming at the internal input (A429/A664) of the avionics system received by the tested equipment, the internal input is issued to a wiring switching subsystem of a wiring matrix through bus interface simulation equipment of the test equipment and is input to the tested equipment; other data (A717/A818/RS 422/485) and discrete quantity and the like are sent to a wiring switching subsystem and input to the tested equipment through a wiring matrix signal simulation subsystem. For bus interface test of real equipment, the following test contents can be mainly realized:
a) Configuring normal signal output of an excitation-side bus;
b) Configuring excitation side bus fault signal output: the method comprises the steps of application layer fault data and protocol layer fault injection;
c) Current physical link data acquisition: the method comprises the steps of data storage, online monitoring, data playback and offline analysis;
for single device testing, signal excitation is required for a certain physical port of the device, and then data of the certain physical port is received, so that whether the logic function of the device meets the set design requirements is verified, and specifically, the single device testing comprises device testing based on source frames and engineering value testing based on ICDs.
(2) Multi-device testing
The multi-device test belongs to a second level of test, and mainly tests the real data interaction situation among a plurality of devices. Because the single-device test in the first stage uses the bus interface simulation device and the signal simulation subsystem to interact with a single tested device, the simulation data generated by the bus interface simulation device and the signal simulation subsystem can not completely replace the real system data, so that the use of the real system for functional test is an important ring in the test scheme. In addition, because of the insufficiency of the system equipment, the peripheral simulation excitation environment of a plurality of tested devices is also needed. A real equipment table for accessing a plurality of tested equipment (SUT) into the testing equipment during testing; setting the test equipment as a real part in the wiring management software, setting the signal simulation subsystem crosslinked with the tested equipment as a simulated part, and issuing relevant ICDs and the like to the tested unit through the data excitation and monitoring software, the automatic test software and the comprehensive simulation system. The test scenario is shown in fig. 8:
in the multi-device cross-linking test process, each device provides a peripheral simulation excitation environment of the tested device through the bus interface simulation device and the signal simulation subsystem, a data acquisition function is used for carrying out data acquisition and test on a data path between the tested devices, and logic function analysis is realized according to the acquired data.
The user inputs a certain excitation value into the tested equipment through the data excitation and monitoring software, and then needs to check the alarm of another physical channel, the alarm needs to be sent to the monitoring interface in time and cannot be seen or delayed in the monitoring interface (within 1s from the start of receiving alarm data), and the data exceeding the threshold value needs to be displayed in red according to the data threshold value set by the user in the interface (namely, data filtering is provided).
A real system network is formed between tested devices, for low-speed signals, the tested devices are connected into the tested network in a physical bypass mode of a BOB circuit breaking test box, and all data on a designated physical channel can be collected; for high-speed signals, the test equipment realizes data acquisition on the physical channel through the ARINC664 bypass switcher.
Because the multi-device test mainly performs the data acquisition test, the test process is consistent with the data acquisition test flow in the previous section. For the internal input (ARINC 429/AARINC 664) of the avionics system accepted by a plurality of tested devices, the internal input is issued to a wiring switching subsystem of a wiring matrix through bus interface simulation equipment of the test equipment, and the internal input is input to the tested devices; other data (A717/A818/RS 422/485) and discrete quantity and the like are sent to a wiring switching subsystem and input to the tested equipment through a wiring matrix signal simulation subsystem. The data transmission among the multiple devices is transmitted back to the data excitation and monitoring software through the wiring switching subsystem for monitoring analysis.
(3) System level testing
The system level cross-linking test belongs to a third level of test, and mainly tests the data interaction condition among all real tested devices. In the test process of the stage, simulation excitation equipment (except peripheral input of a tested system) is not provided, and the test process adopts a data acquisition mode to test. The test scenario is shown in fig. 9:
in the system level test process, a user configures an avionics system as real equipment in configuration management software, loads a user ICD in the configuration management software, and analyzes data through an acquisition channel; the external system inputs data (A717/A818/RS 422/485) of the avionic system and discrete quantity and the like to be sent to a wiring switching subsystem and input tested equipment through a wiring matrix signal simulation subsystem; in the data monitoring process, the user configures the physical channels, signal types, and data of interest to be viewed in the data excitation and monitoring software (data filtering).
In the system level test process, the data types to be monitored are many, so that software is required to support a plurality of users to use test software simultaneously, and data test is carried out on ICDs on different upper computers (resources are required to be mutually exclusive for the same engineering value, but different users are required to monitor simultaneously for different engineering values).
It will be understood that equivalents and modifications will occur to those skilled in the art in light of the present invention and their spirit, and all such modifications and substitutions are intended to be included within the scope of the present invention as defined in the following claims.
Claims (9)
1. A complex avionics system test and integrated verification platform comprises test equipment, a wiring matrix and a software system, and is characterized in that the test equipment comprises workstation computer equipment, bus interface simulation equipment and a comprehensive wiring rack, provides a hardware environment for test total control, realizes the bus communication functions and simulation of ARINC664 and ARINC429, and simultaneously provides a test cable for crosslinking with tested equipment; the wiring matrix comprises a wiring switching subsystem and a signal simulation subsystem, and is used for providing wiring switching of simulation signals and real equipment, including wiring switching of various buses and simulation excitation functions of other signals except ARINC664 and ARINC 429; the software system runs on the test equipment and is used for controlling the test equipment and the wiring matrix to carry out interface test and function verification on the tested equipment.
2. A complex avionics system testing and integration verification platform according to claim 1, wherein the workstation computer device comprises a desktop workstation and a simulation server, a data server; the communication network is composed of a clock network, a control network and a data network which are physically independent;
the control network is responsible for realizing test control and test data transmission between the upper computer and the lower computer; the upper computer is workstation computer equipment and test software, and the lower computer comprises bus interface simulation equipment, a comprehensive wiring rack, a wiring switching subsystem and a signal simulation subsystem;
the clock network is responsible for realizing clock synchronization among all signal excitation devices; the signal excitation equipment comprises a simulation server, bus interface simulation equipment and a signal simulation subsystem, wherein the time synchronization between the signal excitation equipment is realized through a master-slave working mode of an IRIG-B interface, and the time synchronization source is used for carrying out unified time service to complete the unified clock of each bus interface simulation equipment;
the data network is responsible for realizing the business data communication of each bus data between each lower computer and the real tested equipment, thereby completing various experiments.
3. The complex avionics system testing and integrated verification platform of claim 2, wherein in the control network, the simulation server and the data server are configured with dual network cards, the desktop workstation and the simulation server and the data server are in the same local area network, and the simulation server, the data server and the lower computer are in another local area network.
4. The complex avionics system testing and integrated verification platform of claim 2, wherein a master clock IRIG-B card is installed by a simulation server in the clock network, responsible for reading the current system time and distributing to all bus interface simulation devices and signal simulation subsystems currently connected.
5. The complex avionics system testing and integrated verification platform of claim 2, characterized in that in the data network, for ARINC664 exchange buses, ARINC664 simulation boards are configured in bus interface simulation equipment to realize data excitation, cable connectors are configured in the comprehensive wiring rack as ARINC664 bypass switches for switching ARINC664 signals between real parts and simulation parts, and data are mirrored into an uplink path and a downlink path through a physical PHY chip to be led out for data acquisition;
and a physical parallel connection mode is provided for various low-speed signals, so that the networking of the low-speed signal data network is realized.
6. The complex avionics system testing and integrated verification platform of claim 1, wherein the software system comprises wiring management software, test master control software, configuration management software, data excitation and monitoring, automated testing software and comprehensive simulation software;
the wiring management software is matched with the comprehensive simulation software to control the wiring switching subsystem to perform real simulation equipment switching, channel mapping and bypass test management;
the test master control software realizes the resource monitoring of the whole wiring matrix, checks the working state of test resources and can control a workstation computer;
configuration management software provides system test configuration, specifically comprises wiring configuration, distribution configuration, IO association and configuration, and ICD import and resource mapping;
the data excitation and monitoring software realizes ICD-based data excitation and monitoring, provides various data excitation modes, and can provide related data statistics results for different buses; in addition, the data server can be controlled to store all acquired data and play back the data;
the automatic test software can realize the management, execution and automatic test report generation of the automatic test cases; the user test case and ICD data import are supported, and the ICD-based automatic test is realized;
the comprehensive simulation software can integrate a simulation model, realize a simulation configuration function, map simulation variables to a real I/O interface, and package the simulation variables according to a real ICD to realize semi-physical simulation; in addition, a monitoring management function comprising model state control, switching and load distribution is also provided.
7. The complex avionics system testing and integration verification platform of claim 1, wherein the device under test is accessed to the comprehensive wiring rack of the testing device during single device testing; in the software system, the test equipment is set as a real part, the signal simulation subsystem crosslinked with the tested equipment is set as a simulation part to complete wiring switching, and the data excitation, the test case and the simulation model of the related ICD are issued to the tested equipment to complete simulation data excitation transmission, data acquisition and fault injection.
8. The complex avionics system testing and integration verification platform of claim 7, wherein multiple devices under test are connected to the comprehensive wiring rack of the testing device during multi-device testing; the method comprises the steps of setting test equipment as a real part in a software system, setting a signal simulation subsystem crosslinked with tested equipment as a simulation part to complete wiring switching, completing data acquisition and testing on a data path between the tested equipment by issuing data excitation, test cases and simulation models of related ICDs to a tested unit, and realizing logic function analysis according to the acquired data.
9. The complex avionics system testing and integration verification platform of claim 8, wherein during system level testing, the tested devices are configured as real devices in the software system, and the user ICD is loaded to complete configuration, and data analysis is performed through the acquisition channel.
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| CN117939434A (en) * | 2024-03-25 | 2024-04-26 | 中国民航大学 | Centralized control method for excitation signals of cloud box of aircraft |
| CN117939434B (en) * | 2024-03-25 | 2024-05-17 | 中国民航大学 | Centralized control method for excitation signals of cloud box of aircraft |
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