CN112784434A - Model-based avionics design method - Google Patents
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Abstract
A model-based avionics design method, comprising: analyzing a data interface from an avionics system level to a physical layer level, and establishing a hierarchical model of the data interface from top to bottom based on the scene, behavior, function and architecture of the avionics system; and verifying the interface control file according to the hierarchical model. The data interface is subjected to hierarchical structural design, mapping of scene-behavior-function-architecture interface traceability and integrity is achieved, the transferability of system functions and the connection consistency are verified, and rapid interface test verification and interface requirement confirmation are achieved. According to the hierarchical construction, the system function and behavior model is subjected to hierarchical mapping, a system architecture design interface is output, and then actual bus interface data corresponding to the EICD physical hierarchy is formed.
Description
Technical Field
The invention relates to the technical field of avionics system design, in particular to an avionics system design method based on a model.
Background
The avionics system is a complex which adopts a distributed computer and cross-links various airborne electronic subsystems together through a multipath transmission data bus, and integrates the existing single-function dispersion systems such as communication radio stations, radars, navigation equipment and the like into a whole to form a multifunctional comprehensive system. The functions of information measurement, acquisition, transmission, processing, monitoring and display can be realized, and the tasks of flight control, engine control, navigation, performance management and the like can be completed.
The avionics system has many and miscellaneous signals, and in the design process of the avionics system, data interfaces of various bus protocols among subsystems need to be clearly defined, and interface data are transmitted according to the requirements of the interface protocols. The data interface is an important design basis for driving software development, and the application of the data interface is performed throughout the whole process of the avionics system design cycle.
However, in the data interface design of the current avionics system, the description forms of various data interfaces are not uniform; and most of the paper documents are maintained and stored. The method is not beneficial to tracing and uniformly managing various data, is inconvenient for viewing, retrieving and using various data formats, and is difficult to provide service for subsequent airborne software research and development, data acquisition and development of related simulation tools.
Disclosure of Invention
Objects of the invention
The invention aims to provide a model-based avionics system design method, which is used for verifying the transferability and connection consistency of avionics system functions and quickly realizing interface test verification and interface requirement confirmation by realizing interface tracing and mapping of scenes, behaviors, functions and architectures.
(II) technical scheme
To solve the above problems, according to an aspect of the present invention, there is provided a model-based avionics design method, including: analyzing a data interface from an avionics system level to a physical layer level, and establishing a hierarchical model of the data interface from top to bottom based on the scene, behavior, function and architecture of the avionics system; an interface control file (ICD) is validated according to the hierarchical model.
Further, establishing a hierarchical model of the top-down data interface includes: compiling an avionic system and internal hardware and software component interfaces thereof through an Interface Control Document (ICD), establishing a Scene Interface Control Document (SICD), describing the overall function realized by the avionic system, establishing a Functional Interface Control Document (FICD) according to the overall function, and dividing the avionic system into a system and a subsystem; generating a logic interface control file (LICD) according to the relation between the system and the subsystem, and defining the relation between a system interface and a connection of a logic level; a physical interface control file (EICD) is generated based on the logical level system interface.
Further, the scene interface control file (SICD) includes: the function definition module is used for defining the whole functions of the system; the activity diagram modeling module is used for establishing an activity diagram based on a scene according to the overall function of the system to be realized; the function decomposition module forms an activity information stream according to the functions and services of the activity graph subdivision system and the subsystems and generates the function interface control file; a function verification module: and verifying the correctness of the information flow and the activity diagram based on the activity diagram simulation.
Further, the function interface control File (FICD) includes: a structural diagram modeling module: generating a system structure Diagram of a logic level by utilizing IBD (Internal Block Diagram) according to the relation between each system and each subsystem; an ICD definition module: defining a system interface and connection relation of a logic level according to a cross-linking relation between the activity information flow and the system; the information flow binding module: binding the information flow of the system analysis level to the system interface and connection relation of the logic level; an XML generation module: and generating an LICD XML format file containing system logic architecture, logic interfaces, interface connection relations and interface binding information.
Further, the logical interface control file includes: a structural diagram modeling module: generating a system structure Diagram of a physical layer by utilizing IBD (Internal Block Diagram) according to the system structure Diagram of the logical layer; the data interface definition module: defining a physical level interface type according to a logical level interface and combining an actual bus data protocol of an avionic system, and establishing a physical interface control file; an ICD binding module: binding the bus data of the actual physical layer to the physical interface control file; an XML generation module: and generating an EICD XML format file containing system physical architecture, component interfaces, component connection relations and interface binding bus data protocol information.
(III) advantageous effects
The technical scheme of the invention has the following beneficial technical effects:
designing a data interface based on an XML language hierarchical architecture to realize uniform hierarchical avionics system ICD management;
through applying the language modeling based on the model, the ICD is designed and verified by abstractively establishing a hierarchical model of a data interface, and the correct description and tracking representation of the ICD are realized;
and establishing a mapping of the traceability and integrity of the interface of the scene-behavior-function-architecture, and verifying the transitivity of the system function and the consistency of connection.
Drawings
FIG. 1 is a block diagram of a hierarchical model provided by the present invention;
FIG. 2 is a block diagram of a scene interface control file provided by the present invention;
FIG. 3 is a block diagram of a functional interface control file provided by the present invention;
FIG. 4 is a block diagram of a logical interface control file provided by the present invention;
fig. 5 is an application diagram of a scene interface control file provided in an embodiment of the present invention;
FIG. 6 is a diagram of an application of a function interface control file provided by an embodiment of the present invention;
FIG. 7 is a diagram of an application of a logical interface control file provided by an embodiment of the present invention;
fig. 8 is an application diagram of a physical interface control file according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known architectures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Avionics systems and their internal hardware and software component interfaces must be defined and specified (e.g., explicit, complete, verifiable, consistent, and traceable specifications), which are typically written in the form of interface control files (ICDs) and represent the basis for avionics system integration activities.
The invention focuses on analyzing the data interface from the avionics system level to the logic level, applies the language modeling abstraction based on the model to establish the hierarchical model of the data interface, and applies the advantages based on the model to design and verify ICDs, thereby ensuring the correct description and tracking representation of the interface and the ICDs.
Based on the above, the invention provides a model-based avionics system design method, which comprises the following steps:
s1: an interface control file (ICD) hierarchical design data interface of the avionics system based on an eXtensible Markup Language (XML) Language; the method comprises the following steps:
s11: the ICD of the avionics system is layered, and the method sequentially comprises the following steps: SICD (scene interface control file), FICD (Functional interface control file), lic (Logical interface control file), EICD (physical interface control file);
s12: generating a data interface file in an XML format in the avionics system of each level;
s13: and establishing interface mapping which sequentially comprises scenes, behaviors, functions and architectures from top to bottom.
Specifically, data are expressed and stored based on an XML language, real-time performance of the data can be guaranteed, and the XML language is suitable for various systems including windows linux avionics systems. Meanwhile, XML is a plain text meta language based on Unicode, which is a language for defining markup languages, and is not dependent on any programming language, operating system, or software vendor. The XML language defines markup languages such as elements, attributes, etc., which can be used to describe the relationships, properties, and requirements of objects.
The SICD is an operation scene analysis layer, an activity diagram based on a system operation scene is established according to the overall system function to be realized by the avionics system, and the functions and services of the system and the subsystems are divided according to the activity diagram to form an activity information stream to obtain the FICD; meanwhile, based on activity diagram simulation, the correctness of the information flow and the activity diagram is verified.
Wherein verifying the correctness of the information flow and the activity graph comprises: the activity graph is executed, verifying the correctness of inputs and outputs, and whether the control flow (driving the sequence between activities) and the information flow (data transfer between activities) are functioning correctly between activities.
Therefore, this layer mainly describes service models constituting behavior and usage scenarios of the avionics system, the usage scenarios being operational scenarios defining functional activities between participants of the activity (human and system, system and system), such as "performing ground inspection" as one of the necessary scenarios for an onboard maintenance system.
The interface description of this layer focuses on the cross-linking and information flow between black boxes for illustrating the scenario and the outlined behavior of the system application.
The FICD obtained by the operation scene analysis layer is a system analysis layer, a plurality of subsystems are obtained after the system is split, and the FICD can generate a system structure diagram of a logic level according to the relation between each system and each subsystem; and according to the cross-linking relation between the activity information flow and the system, defining the system interface and the connection relation of the logic level, binding the information flow of the FICD to the system interface of the logic level, and simultaneously binding the information flow of the FICD to the connection relation of the logic level. And finally generating an LICD XML format file containing system logic architecture, logic interfaces, interface connection relations and interface binding information.
Specifically, an operation scenario includes multiple systems, such as an "onboard maintenance system", "display system", "system under test", and a "system user" (i.e., a human being) required for performing ground inspection, and a system structure diagram is established according to input and output information between the systems in the activity diagram, a relationship between the systems, and a possible cross-linking interface form.
The system is subdivided into subsystems according to different functional modules, the subsystems can be crosslinked, and the subsystems can also be crosslinked with other systems, for example, one system can have two subsystems of a data processing system and a data storage system according to functional division.
The logical level LICD generates a physical level system configuration diagram from the logical level system configuration diagram. And defining the type of a physical layer interface based on a logic layer interface and combining an actual bus data protocol of an avionic system, and establishing the EICD.
The LICD can bind the bus data of the actual physical level to the EICD to generate an EICD XML format file containing system physical architecture, component interfaces, component connection relation and interface binding bus data protocol information.
Specifically, for each module in the logical architecture, the allocation of each component in the logical architecture to physical hardware is realized by identifying corresponding physical components, and meanwhile, interface definition is detailed, including the details of encoding of the physical interface and the specific definition of a transmission bus, and finally, the generation of the physical architecture is realized.
S2: establishing a hierarchical model of a data interface, designing and verifying the ICD of the avionics system based on the hierarchical model, and describing and tracking the ICD of the avionics system.
The electrical interface definition model mainly comprises general attributes, electrical connection relations and signal electrical characteristics of the equipment. The XML format-based electrical interface document can conveniently realize the interaction of electrical interface data between different platform software applications and different design bodies. But for the query, storage, change and output of the electrical characteristics in the electrical interface document, the query, storage, change and output need to be realized in a relational database by constructing a relational data table mapped with XML data.
Example (b):
fig. 5 is an application diagram of a scene interface control file provided in an embodiment of the present invention, fig. 6 is an application diagram of a function interface control file provided in an embodiment of the present invention, fig. 7 is an application diagram of a logic interface control file provided in an embodiment of the present invention, fig. 8 is an application diagram of a physical interface control file provided in an embodiment of the present invention, and as can be seen, in combination with the overall hierarchical model architecture diagram of fig. 1, fig. 5 to fig. 8 are flowcharts of specific implementation modes of a model-based avionics system design method in this embodiment.
The invention aims to protect a model-based avionics design method, which comprises the following steps: analyzing a data interface from an avionics system level to a physical layer level, and establishing a hierarchical model of the data interface from top to bottom based on the scene, behavior, function and architecture of the avionics system; and verifying the interface control file according to the hierarchical model. The data interface is subjected to hierarchical architectural design, mapping of scene-behavior-function-architecture interface traceability and integrity is achieved, the transferability of system functions and the connection consistency are verified, and rapid interface test verification and interface requirement confirmation are achieved. According to the hierarchical construction, the system function and behavior model is subjected to hierarchical mapping, a system architecture design interface is output, and then actual bus interface data corresponding to the EICD hierarchy is formed.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (5)
1. A model-based avionics design method, comprising:
analyzing a data interface from an avionics system level to a logic level, and establishing a hierarchical model of the data interface from top to bottom based on the scene, behavior, function and architecture of the avionics system;
and verifying the interface control file according to the hierarchical model.
2. The method of claim 1, wherein building a hierarchical model of a top-down data interface comprises:
the avionics system and the internal hardware and software component interfaces thereof are written through interface control files,
a scene interface control file is established to describe the whole functions realized by the avionics system,
establishing a functional interface control file according to the integral function, and dividing the avionic system into a system and a subsystem;
generating a logic interface control file according to the relationship between the system and the subsystem, and defining the relationship between a system interface and a connection of a logic level;
and generating a physical interface control file according to the system interface of the logic level.
3. The method of claim 1, wherein the scene interface control file comprises:
the function definition module is used for defining the whole functions of the system;
the activity diagram modeling module is used for establishing an activity diagram based on a scene according to the overall function of the system to be realized;
the function decomposition module forms an activity information stream according to the functions and services of the activity graph subdivision system and the subsystems and generates the function interface control file;
a function verification module: and verifying the correctness of the information flow and the activity diagram based on the activity diagram simulation.
4. The method of claim 1, wherein the function interface control file comprises:
a structural diagram modeling module: generating a system structure diagram of a logic level by utilizing IBD according to the relation between each system and each subsystem;
an ICD definition module: defining a system interface and connection relation of a logic level according to a cross-linking relation between the activity information flow and the system;
the information flow binding module: binding the information flow of the system analysis level to the system interface and connection relation of the logic level;
an XML generation module: and generating an LICD XML format file containing system logic architecture, logic interfaces, interface connection relations and interface binding information.
5. The method of claim 1, wherein the logical interface control file comprises:
a physical structure generation module: generating a system structure diagram of a physical layer by IBD according to the system structure diagram of a logic layer;
the data interface definition module: defining a physical level interface type according to a logical level interface and combining an actual bus data protocol of an avionic system, and establishing a physical interface control file;
an ICD binding module: binding the bus data of the actual physical layer to the physical interface control file;
an XML generation module: and generating an EICD XML format file containing system physical architecture, component interfaces, component connection relations and interface binding bus data protocol information.
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