CN114707242A - Universal airborne data bus monitoring and testing software framework design method - Google Patents
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Abstract
The invention discloses a universal airborne data bus monitoring and testing software framework design method in the technical field of avionics, which comprises the following steps: the field analysis of the airborne bus test system: analyzing the test procedures of various airborne bus systems to obtain the common operation and universal test of all airborne bus test systems; the field framework design of the airborne bus test system comprises the following steps: under the guidance of a universal design principle, the method adopts a field engineering method and a software product line method, solves the problem that the current airborne data bus monitoring and testing system is poor in universality and reusability, adopts the field engineering method and the software product line method to carry out universal design, and can meet the development requirements of various different types of airborne data bus monitoring and testing systems.
Description
Technical Field
The invention relates to the technical field of avionics, in particular to a design method of a universal airborne data bus monitoring and testing software framework.
Background
The airborne data bus technology plays an important role in the avionic system, and in an avionic simulation system test, strict comprehensive test and real-time information monitoring must be carried out on data transmitted on a bus, so that scientific researchers can carry out fault location and statistical analysis conveniently, and systematically evaluate and verify whether various performance indexes and functions of the avionic simulation system and related avionic subsystems meet design requirements or not, and a basis is provided for evaluation and improvement of a design scheme.
The existing airborne data bus has various types, and has great differences in aspects such as electrical characteristics, topological structure, data transmission format and the like. Meanwhile, the same type of onboard data buses are often developed by different units, and although the onboard data buses conform to the corresponding bus communication specifications together, the specific communication processes are different, and each type of bus has different hardware interfaces. This requires a dedicated bus monitoring and testing system to be designed for each bus, creating a phenomenon of repeated development. Further, in the cross-coordination test of the hybrid onboard bus system, it is difficult to coordinate various dedicated test systems, and thus, it is impossible to accurately locate the fault. For example, the prior patents "Mil-std-1553 b bus monitoring and data analysis system" and "arinc 429 data bus simulation test system" in China are all simulation test systems developed for special buses, and cannot meet the simulation test requirements of various types of buses. Therefore, a universal airborne data bus monitoring and testing technology is urgently needed to be researched to deal with the complexity of the current avionic integrated testing system, improve the accuracy of aviation bus testing, improve the reliability of an airborne data bus, reduce testing cost and shorten project cycle.
Disclosure of Invention
The invention aims to provide a universal airborne data bus monitoring and testing software framework design method, which aims to solve the problems that the universal airborne data bus monitoring and testing technology is urgently needed to be researched in the background technology so as to deal with the complexity of the current avionic integrated testing system, the accuracy of aviation bus testing is improved, the reliability of an airborne data bus is improved, the testing cost is reduced, and the project cycle is shortened.
In order to achieve the purpose, the invention provides the following technical scheme: a design method for a universal airborne data bus monitoring and testing software framework comprises the following steps:
s1: the field analysis of the airborne bus test system: analyzing the test procedures of various airborne bus systems to obtain the common operation and universal test of all airborne bus test systems;
s2: the field framework design of the airborne bus test system is as follows: under the guidance of a general design principle, a field engineering method and a software product line method are adopted, and an extensible field framework supporting the reused airborne data bus test system is designed, and the framework can be extended and reused according to different user requirements, so that airborne bus monitoring and test systems of different types and different purposes can be quickly built;
s3: the field component design of an airborne bus test system is as follows: extracting various universal field components according to the common operation of the airborne bus test system;
s4: the universal airborne bus monitoring and testing system is applied and verified: in order to verify the universality of the universal airborne bus testing system and the monitoring system, prototype software of the universal airborne data bus testing and monitoring system is built, and the prototype system consists of a core part and an extension part: the core part comprises universal bus interface monitoring software, data analysis software and universal test system framework software; the extension part comprises adaptive interface software aiming at various typical onboard data buses, and the function verification of the prototype system is completed by utilizing the prototype system to test and monitor the ARINC429 bus data, the 1553B bus data and the AFDX bus data respectively.
Preferably, the method for testing commonality and commonality of the onboard bus test system in step S1 includes the following steps:
a1: data acquisition: acquiring data to be transmitted from an airplane and flight environment simulation software;
a2: data processing: the exciter carries out certain processing on the acquired data to obtain data to be sent, and the data is in a computer representation format;
a3: data packaging: the airborne bus ICD packaging and analyzing program packages the data in the computer format into ICD format data;
a4: data transmission: the ICD format data is sent to an airborne data bus, and at the moment, the monitoring module can also be used for monitoring the data before sending so as to compare the data with the data received by a receiver and perform time delay analysis;
a5: data reception: the receiving end receives the ICD format data from the bus, and the monitoring module can be used for monitoring the received data for comparison;
a6: unpacking the data: the airborne bus ICD packaging and analyzing program analyzes the bus data in the ICD format into data in a computer format;
a7: and (3) displaying data: and displaying various data through the monitoring interface.
Preferably, the general field components in step S3 include: the universal data source component, the universal buffer data area component, the universal exciter component, the universal data packing/analyzing component and the universal data monitoring and displaying component.
Compared with the prior art, the invention has the beneficial effects that: the invention solves the problem of poor universality and reusability of the current airborne data bus monitoring and testing system, adopts a field engineering method and a software product line method to carry out universal design, can meet the development requirements of various different types of airborne data bus monitoring and testing systems, utilizes a field framework and field components designed by the invention, and can conveniently carry out self-defined component assembly and system construction when a user compiles airborne bus monitoring and testing system software. The method mainly realizes universality from two aspects: firstly, abstracting data flow in a bus test system, realizing unified management, unified storage and automatic analysis of data in different bus types and different ICDs (interface control document) formats, thereby realizing the generalization of test data, secondly, generalizing the system architecture for transmitting the test data, constructing a field framework of a universal bus test system by using abstract components and abstract flows, enabling a user to expand and reuse the framework according to different requirements, quickly constructing airborne bus monitoring and test systems of different types and different purposes, and finally, constructing two special bus test systems and a prototype of a mixed type bus test system by using the universal framework, wherein verification results show that the ICD unified management technology and the universal airborne bus test system framework provided by the subject have good expandability, the system can complete the construction of various special and mixed bus test systems with minimum cost, and is compatible with various new buses to be put on the market in the future.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic diagram of a general testing process of the airborne bus testing system according to the present invention;
FIG. 3 is a diagram illustrating components of a general field of the airborne bus test system of the present invention;
FIG. 4 is a diagram of a software architecture of a universal airborne data bus test system according to the present invention;
FIG. 5 is a schematic diagram of a data source subsystem according to the present invention;
FIG. 6 is a schematic diagram of a data distribution subsystem of the present invention;
FIG. 7 is a schematic diagram of a unified data storage subsystem of the present invention;
FIG. 8 is a schematic diagram of the internal structure of the unified data storage subsystem according to the present invention;
FIG. 9 is a schematic diagram of the system data organization of the present invention;
FIG. 10 is a diagram illustrating data consistency maintenance in the system of the present invention;
FIG. 11 is a diagram illustrating an interface and implementation provided by an index layer according to the present invention;
FIG. 12 is a schematic view of exciter subsystem classes in accordance with the present invention;
FIG. 13 is a schematic diagram of the exciter dispatch framework of the present invention;
FIG. 14 is a schematic diagram of a data parsing subsystem in accordance with the present invention;
FIG. 15 is a diagram illustrating a process of parsing rule registration according to the present invention;
FIG. 16 is a schematic diagram of an ICD parsing/packaging process according to the present invention;
FIG. 17 is a schematic view of a data display subsystem in accordance with the present invention;
FIG. 18 is a schematic diagram of a prototype building of an AFDX bus test system according to the present invention;
FIG. 19 is a schematic diagram of a prototype building of an ARINC429 bus test system of the invention;
fig. 20 is a schematic diagram of prototype construction of the hybrid bus test system according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a universal onboard data bus monitoring and testing software frame design method, which solves the problem of poor universality and reusability of the current onboard data bus monitoring and testing system, adopts a field engineering method and a software product line method to carry out universal design, can meet the development requirements of various types of onboard data bus monitoring and testing systems, and please refer to figure 1, wherein the universal onboard data bus monitoring and testing software frame design method comprises the following steps:
s1: the field analysis of the airborne bus test system: through the analysis of the test flows of various airborne bus systems, the common operation and the universal test flow of all airborne bus test systems are obtained:
a1: data acquisition: acquiring data to be transmitted from an airplane and flight environment simulation software;
a2: data processing: the exciter carries out certain processing on the acquired data to obtain data to be sent, and the data is in a computer representation format;
a3: data packaging: the airborne bus ICD packaging and analyzing program packages the data in the computer format into ICD format data;
a4: data transmission: the ICD format data is sent to an airborne data bus, and at the moment, the monitoring module can also be used for monitoring the data before sending so as to compare the data with the data received by a receiver and perform time delay analysis;
a5: data reception: the receiving end receives the ICD format data from the bus, and the monitoring module can be used for monitoring the received data for comparison;
a6: unpacking the data: the airborne bus ICD packaging and analyzing program analyzes the bus data in the ICD format into data in a computer format;
a7: and (3) displaying data: displaying various data by the monitoring interface;
s2: the field framework design of the airborne bus test system is as follows: under the guidance of a general design principle, a field engineering method and a software product line method are adopted, and an extensible field framework supporting the reuse of the airborne data bus test system is designed, and the framework can be expanded and reused according to different user requirements, so that airborne bus monitoring and test systems of different types and different purposes can be quickly built;
s3: the field component design of an airborne bus test system is as follows: various general field components are extracted according to the common operation of the airborne bus test system, and the general field components comprise: the universal data source component, the universal buffer data area component, the universal exciter component, the universal data packing/analyzing component and the universal data monitoring and displaying component;
s4: the universal airborne bus monitoring and testing system is applied and verified: in order to verify the universality of the universal airborne bus testing system and the monitoring system, prototype software of the universal airborne data bus testing and monitoring system is built, and the prototype system consists of a core part and an extension part: the core part comprises universal bus interface monitoring software, data analysis software and universal test system framework software; the extension part comprises adaptive interface software aiming at various typical onboard data buses, and the function verification of the prototype system is completed by utilizing the prototype system to test and monitor the ARINC429 bus data, the 1553B bus data and the AFDX bus data respectively.
Examples
(1) Framework design in field of airborne bus monitoring and testing system
The field framework of the airborne bus monitoring and testing system is a software framework of the whole system designed by using C + + language, the framework can be expanded and reused according to different user requirements, airborne bus monitoring and testing systems of different types and different purposes are quickly built, and the software framework of the general airborne bus testing system is shown in FIG. 4;
the system comprises a core abstraction layer and six subsystems, wherein the core abstraction layer extracts common components of various airborne bus test systems, so that a universal test flow is realized, and the six subsystems are extensions of field components and are used for adapting to various different data sources, bus types, exciter types, analysis requirements and display requirements;
the method comprises the following steps that firstly, a core abstract layer comprises five abstract classes, namely a bus Model class Model, an Exciter Model class Exciter, an abstract data write class DBWriter, an abstract data source class DataSource and an abstract display class View, wherein the classes are abstract component sets of a universal airborne data bus test system, and the actual test processes of various airborne bus systems are completed through interaction among the classes;
the data source subsystem: the data source subsystem takes an abstract data source class DataSource as a base class, constructs a factory class of a specific data source, the factory class can load and initialize specific data sources according to user configuration files, such as flight environment simulation software of airplanes and flight environments, such as FlightSim, FlightGear or Prepar3D, and the software encapsulates data sources required by various airborne bus test systems;
the data distribution subsystem: the active object of the data distribution subsystem is a DataDispathcer class object, which reads data in an abstract data source and writes the data read from the data source into the unified data storage subsystem by a DBWriter class subclass object, namely a specific data write-in object of some airborne subsystem, wherein the data distribution subsystem also adopts an abstract factory mode and can flexibly generate various data write-in objects according to user requirements, and the data write-in objects correspond to the data required by each airborne subsystem;
fourthly, unifying the data storage subsystem: the data storage subsystem is used for organizing various data required by each airborne subsystem in a B + tree form and storing the data in a shared memory so that all the subsystems can access in real time, and the essence is that a simplified real-time database is realized in the memory, and the addition, deletion, modification and query of various data can be quickly completed;
the exciter subsystem: the exciter subsystem needs to simulate the behaviors of various subsystems in an airborne system, such as a flight management system, a display control system, navigation, radar and the like, and the subsystems are characterized by periodically reading in external data, performing certain calculation and outputting the external data to other subsystems, so that the exciter subsystem not only comprises various exciter objects, but also needs to design a periodic working thread to schedule the objects and drive the objects to complete the periodic process of 'reading data, processing data and outputting data', and meanwhile, for the test requirement, sometimes the current output data needs to be frozen, and a master controller is further needed to control the behaviors of all exciters;
sixthly, the data analysis subsystem: the data analysis subsystem completes the packaging and analysis of the ICD, in order to realize the universality of various bus types and ICD formats, an abstract analysis component in the core subsystem is replaced by a concrete bus class object, meanwhile, various ICD formats are packaged in a Map class object, and are analyzed and loaded into a memory when the system is initialized to serve as rules for packaging and analyzing a specific ICD;
the data display subsystem: the data display subsystem meets the general requirements of users on arrangement, appearance, data types and the like of various display components, and the display component factory class objects in the system can generate various display components such as progress bars, dashboards, text boxes and the like according to the specific requirements of the users and display monitoring data according to the arrangement mode and the data types defined by the users;
(2) data source subsystem design
The class structure of the data source subsystem is as shown in fig. 5, the subsystem and the data distribution subsystem have a dependency relationship, the data dispatcher class object in the data distribution subsystem first refers to the data source factory class object, and uses its GetSource method to obtain the actual data source, where the data source to be obtained is manually configured in the configuration file before the system is started, in fig. 5, three data source subclasses are identified, but the user can completely use other data sources, the method is to write a concrete data source class as the subclass of the abstract data source class, and implement the three methods specified in its abstract class, i.e. the Init method, SendData method and RecData method, at the same time, the user should write the factory class of the concrete data source object, and let it inherit the data source factory class, and implement its abstract method GetSource, so that, without originally testing the system source code, the user only needs to generate a dynamic library of a specific factory class and a specific data source class, and the adaptation to the new data source can be completed;
(3) data distribution subsystem design
The class structure of the data distribution subsystem is shown in fig. 6, the data acquired from the data source subsystem is data of each subsystem of the whole aircraft, such as a flight control system, an autopilot system, a hydraulic system, a flight management system, and the like, which are usually packaged in some large structural body and are not stored according to the class of the subsystem, so that a data distribution service needs to be provided to store data required by each exciter into the unified data storage subsystem in a class, the data distribution subsystem provides an abstract factory class dbwritefactory, which can be used to generate data write objects of various onboard subsystems, such as a flight management system data write class FMSWriter, a navigation system data write class navwritter, a display system data write class dispwritter, and the like, which are generated by the corresponding specific factory class, and a user must implement a GetData method in the subclass to acquire the data, and implementing a SyncDB method to write data into the unified data storage subsystem;
in the aspect of universal design, a user can add various new data write-in objects to meet the specific requirements of the airborne bus test system, and the method is that a specific data write-in class is written as a subclass of an abstract data write-in class DBWriter class, and a specific factory class is written as a subclass of an abstract factory class DBWriter factory;
(4) unified data storage subsystem design
Unified data storage subsystem summary design
The unified data storage subsystem is a link connecting the data distribution subsystem, the exciter subsystem and the data analysis subsystem, and is a storage center of test data of the airborne bus test system, various airborne data read by the data distribution subsystem from the data source subsystem are classified and stored in the unified data storage subsystem according to a tree structure, so that various exciters in the exciter subsystem can conveniently read, meanwhile, the data in the unified data storage subsystem are mapped into ICD format data transmitted on the airborne bus by the data analysis subsystem according to a mapping rule (called as an I/OMAP rule) specified by a user, and the ICD format data are transmitted to the airborne bus by the exciter, and the principle of the ICD format data is shown in FIG. 7;
② unified data storage subsystem module partitioning
The internal modules of the unified data storage subsystem are divided into a configuration tool and a run-time support module, the configuration tool module comprises a mapping configuration module, an analyzer configuration management module, a shared memory operation module, a shared memory queue management module and a configuration file analysis module, the modules load and initialize various data from a local configuration file to a shared memory according to user configuration, convert the unified data storage format into various ICD formats according to analysis rules and mapping rules specified by a user, and the shared memory management module provides an interactive approach for various user processes;
the support module is divided into four layers during operation: the logical table operation layer provides a uniform interface for data addition, deletion, modification and check for the data distribution subsystem, the exciter subsystem and the data analysis subsystem, the mapping operation module of the physical adaptation layer provides ICD packaging/analysis support for the data analysis subsystem, the shared memory address of each item of data is stored in the data index layer according to a B tree mode, so that the rapid retrieval and modification of the data are supported, and the memory operation layer stores actual data;
data organization of unified data storage subsystem
In order to support real-time data interaction of an airborne data bus test system, test data of each airborne subsystem is stored in a shared memory in a B-tree mode, and indexes are provided in an application process memory, wherein three types of B-trees are respectively a Table index tree, a variable index tree and a mapping index tree, and are respectively responsible for subsystem variable Table addressing, intra-Table variable addressing and ICD mapping relation Table addressing, it needs to be stated that each B-tree in the application process memory stores addresses of corresponding variables in the shared memory instead of actual variables, so that the data storage time is saved, and in the shared memory, a Table linked list, a variable Table and a mapping Table are stored in a linked list mode, so that the data of the unified data storage subsystem is conveniently inserted and deleted, and the data organization is shown in figure 9;
keeping consistency of system data
In order to ensure that users of the unified data storage subsystem (i.e. the exciter subsystem, the data distribution subsystem and the data analysis subsystem, which are collectively referred to as application programs herein) can efficiently access data in real time, two buffer areas are opened up in the memory space of the application program to store various variables required by the application program, namely an input variable buffer area and an output variable buffer area, the input variables and the output variables required by each application program are loaded from a configuration file into the memory during the system initialization stage and are periodically updated according to the data in the shared memory, in order to ensure the synchronization between the data in the application program buffer area and the data in the shared memory, a periodic synchronization process is used to refresh the data in real time, including refreshing the input data in the local memory into the shared memory and updating the output data in the shared memory into the local buffer area, the principle is shown in fig. 10, and it should be noted that the input and output are relative to the shared memory;
interface provided by index layer
The index layer provides an initialization interface, a search interface, an insertion interface, a deletion interface and a group search interface for external systems (such as a data distribution subsystem), the interfaces are actually realized by a bottom-layer B tree index, the B tree index provides the realization of initialization, search, insertion and deletion operations based on a B tree, and the purpose of providing the interface layer is to conveniently replace a dynamic library when a better retrieval algorithm needs to be replaced without any modification on the code of a main program, and the principle is as shown in FIG. 11;
(5) exciter subsystem design
The exciter subsystem reads and calculates test data and sends the test data to the airborne bus, and a large number of exciters must be arranged in a real airborne bus test system to simulate the behaviors of various airborne systems, meanwhile, the behaviors of the exciters have strict time sequence relation and need to periodically collect and send data, so that the universality of the airborne bus test system can be improved by designing a flexible and expandable universal exciter frame, meanwhile, the software frame can enable an exciter developer to save a large amount of development time and only pay attention to application logic without paying attention to communication and scheduling of a bottom layer, and the section designs a universal exciter frame which can meet the development requirements of various exciters in the airborne bus test system and is similar to the diagram shown in FIG. 12;
the exciter subsystem adopts the idea of 'assembly + frame', and a 'white box frame' is designed, so that developers of the airborne bus test system can customize various airborne system exciters according to requirements;
the exciter scheduling framework mainly comprises two parts, namely component management and component scheduling, wherein the component management is to load the configuration information of the components into the framework and manage the basic information of the components; the component scheduling is to drive the component to normally run, a scheduler model and a period group model are designed in the component scheduling according to the periodic characteristics of the exciter, the exciters in the same period are added into the same period group, then the period group is driven by the scheduler, and each exciter member in the group is driven by the period group to complete the scheduling of the exciter;
the scheduling framework principle is shown in fig. 13:
the top-level scheduler is responsible for the starting, stopping, pausing and stepping control of the exciters on all the nodes in the whole airborne bus test system, sends the instructions to each node, controls the schedulers on the nodes to schedule the exciters on the node, at each test system node, a scheduler resides, all the exciter tasks are grouped by cycles, with cycle groups as component containers, each cycle group containing all the exciter components for a particular cycle, an exciter may be made up of one or more exciter components, for example, in the test system node 1 of fig. 13, the components FMS1, FMS2, and FMS3 form an actuator of the flight management system, which means that the actuator of the flight management system is formed by three different periods of components, and each test node has a component manager to manage the registration and loading of all components on the node;
(6) data parsing subsystem design
Main object of system
The design class diagram of the data analysis subsystem is shown in fig. 14, the data analysis subsystem is a key technology for completing the adaptation of multiple types of buses and the coexistence of airborne networks of multiple types of ICDs, and is also an actual implementation module of the unified management technology of airborne data buses ICDs, the system comprises two types of objects, one type is a bus class object (Model class object), a process of interconversion between a unified data storage subsystem data format and a bus test system data format (ICD format) is encapsulated, the type of object converts the uniformly expressed data format into a specified ICD format or performs reverse analysis operation according to a given rule, the other type is a Map _ combus class object which specifies a conversion rule and specifies a certain bus packaging and analysis rule, and through the abstraction, a user can flexibly select various ICD packaging/analysis programs and packaging/analysis rules to adapt to different types of buses and different ICDs of the same type of buses A format;
② configuration and registration of analysis rules
ICD packaging/parsing rules are specified by a user in a system configuration file before system initialization, the configuration files are automatically parsed and loaded into a memory by a bus test system in a system initialization stage, for an exciter using a specific type of bus and a specific type of ICD, ICD packaging/parsing rules (called Map rules) of input data and output data of the exciter are required to be registered in the memory, the mapping rules are stored in a local memory space of an exciter subsystem in the system initialization stage, in order to provide support for multi-bus and multi-ICD formats of a certain exciter, a local mapping set is opened up in a local memory of the exciter subsystem, the mapping rules of various buses and ICDs can be stored simultaneously, and therefore, the user can enable one exciter subsystem to communicate with various buses simultaneously, and analyzes and packs the data according to various different ICD analysis rules, and the registration process of the analysis rules is shown in FIG. 15;
③ ICD parsing/packaging process
Each exciter (for an analysis subsystem, an application program) in the exciter subsystem calls a frame transfer operation of the data analysis subsystem, converts data in the unified data storage system into test data transmitted on the airborne bus test system, namely ICD format data according to an ICD packaging rule specified in a local mapping rule, and solves the test data transmitted on the bus test system through a reverse flow in the opposite direction;
(7) data display subsystem design
The design goal of the data display subsystem is to provide a customizable and various-form monitoring data display interface for users, facilitate the users to observe, count, compare and analyze bus data, design a View class View and a display assembly factory class ControlFactory to achieve the goal, as shown in fig. 17, the View class is designed as an abstract class, which is responsible for displaying various types of bus data, and besides some display component classes provided by the system itself, the user can add more display components according to the system test requirements, displaying data according to a specified form, the ControlFactory class is responsible for generating various specific display component factory classes, the specific display component factories can generate various display component objects according to system configuration, and UI classes are designed for uniformly managing various display components in the display subsystem to complete operations such as component management, registration loading and the like;
(8) universal airborne data bus test and monitoring system prototype building
In order to verify the universality of the airborne bus test system and the monitoring system, two special bus test systems and a mixed bus test system are respectively built by using the universal field framework and the field components;
constructing AFDX bus test system prototype
A prototype of an AFDX bus test system is built for an airborne network of a large airplane of a certain type, a data source adopts airplane and flight environment simulation software flight, an exciter subsystem adopts a flight management system, a display control system and an electromechanical management system exciter, a data analysis subsystem adopts AFDX bus ICD analysis configuration, a display subsystem is built by adopting display components such as a compass, an altimeter and a flight attitude meter, and system components and data flow are shown in FIG. 18;
② ARINC429 bus test system prototype building
An ARINC429 bus test system is built for an airborne network of a domestic passenger plane of a certain model, flight environment simulation software flight gear is adopted for a data source, an inertial navigation system exciter and a radar system exciter are used for an exciter subsystem, an ARINC429 bus ICD analysis configuration is adopted for a data analysis subsystem, various text display components are built for a display subsystem, and system components and data flow are shown in figure 19;
mixed bus test system prototype building
A bus test system with mixed AFDX and ARINC429 buses is established for an airborne network of a certain type of mixed bus, a data source subsystem adopts Prepar3D as a data source, an exciter subsystem adopts an electromechanical management system exciter, a flight management system exciter and a display control system exciter as AFDX bus data transceiving exciters, an atmospheric data computer exciter and an inertial navigation system exciter as ARINC429 bus data transceiving exciters, a data analysis subsystem simultaneously adopts ARINC429 buses and AFDX bus analysis configuration, a display subsystem adopts various graphical display components and text display components to be established in a mixed mode, and system components and data flow are shown in figure 20;
in the prototype building process of the three systems, a main frame program of the whole bus test system does not need to be modified, a user only needs to modify a configuration file and write a corresponding subclass program to complete building of different types of bus test systems, meanwhile, the problems of transmission, analysis, monitoring and display of test data in the bus test system with the coexistence of multiple types of buses and ICDs are well solved in the prototype of the hybrid type bus test system, and the result of prototype verification shows that the universal onboard bus test system provided by the invention has good expandability and good adaptability to novel buses and novel ICD formats.
While the invention has been described with reference to exemplary embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention, and in particular, features of the disclosed embodiments may be combined in any manner without departing from the scope of the invention. Therefore, it is intended that the invention not be limited to the particular embodiments disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (3)
1. A universal airborne data bus monitoring and testing software framework design method is characterized in that: the design method of the universal airborne data bus monitoring and testing software framework comprises the following steps:
s1: the field analysis of the airborne bus test system: analyzing the test procedures of various airborne bus systems to obtain the common operation and universal test of all airborne bus test systems;
s2: the field framework design of the airborne bus test system is as follows: under the guidance of a general design principle, a field engineering method and a software product line method are adopted, and an extensible field framework supporting the reuse of the airborne data bus test system is designed, and the framework can be expanded and reused according to different user requirements, so that airborne bus monitoring and test systems of different types and different purposes can be quickly built;
s3: the field component design of an airborne bus test system is as follows: extracting various universal field components according to the common operation of the airborne bus test system;
s4: the universal airborne bus monitoring and testing system is applied and verified: in order to verify the universality of the universal airborne bus testing system and the monitoring system, prototype software of the universal airborne data bus testing and monitoring system is built, and the prototype system consists of a core part and an extension part: the core part comprises universal bus interface monitoring software, data analysis software and universal test system framework software; the extension part comprises adaptive interface software aiming at various typical onboard data buses, and the function verification of the prototype system is completed by utilizing the prototype system to test and monitor the ARINC429 bus data, the 1553B bus data and the AFDX bus data respectively.
2. The method for designing a generic airborne data bus monitoring and testing software framework according to claim 1, characterized in that: the method for testing the commonality and the general purpose of the onboard bus test system in the step S1 comprises the following steps:
a1: data acquisition: acquiring data to be transmitted from an airplane and flight environment simulation software;
a2: data processing: the exciter carries out certain processing on the acquired data to obtain data to be sent, and the data is in a computer representation format;
a3: data packaging: the airborne bus ICD packaging and analyzing program packages the data in the computer format into ICD format data;
a4: data transmission: the ICD format data is sent to an airborne data bus, and at the moment, the monitoring module can also be used for monitoring the data before sending so as to compare the data with the data received by a receiver and perform time delay analysis;
a5: data reception: the receiving end receives the ICD format data from the bus, and the monitoring module can be used for monitoring the received data for comparison;
a6: unpacking the data: the airborne bus ICD packaging and analyzing program analyzes the bus data in the ICD format into data in a computer format;
a7: and (3) displaying data: and displaying various data through the monitoring interface.
3. The method for designing a generic onboard data bus supervision and test software framework according to claim 2, characterized in that: the general domain components in the step S3 include: the universal data source component, the universal buffer data area component, the universal exciter component, the universal data packing/analyzing component and the universal data monitoring and displaying component.
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| CN115567421A (en) * | 2022-09-20 | 2023-01-03 | 武汉船舶通信研究所（中国船舶重工集团公司第七二二研究所） | Situation centralized monitoring system for airborne equipment |
| CN116107703A (en) * | 2023-04-14 | 2023-05-12 | 北京蓝天航空科技股份有限公司 | Interface control document generation method and device |
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| CN103873324A (en) * | 2014-03-17 | 2014-06-18 | 中国航空无线电电子研究所 | Universal bus testing system |
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| CN103873324A (en) * | 2014-03-17 | 2014-06-18 | 中国航空无线电电子研究所 | Universal bus testing system |
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| CN115567421A (en) * | 2022-09-20 | 2023-01-03 | 武汉船舶通信研究所（中国船舶重工集团公司第七二二研究所） | Situation centralized monitoring system for airborne equipment |
| CN116107703A (en) * | 2023-04-14 | 2023-05-12 | 北京蓝天航空科技股份有限公司 | Interface control document generation method and device |
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