CN104992022A - Aeronautics electronic system interface management method based on models - Google Patents
Aeronautics electronic system interface management method based on models Download PDFInfo
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Abstract
The present invention relates to an aeronautics electronic system interface management method based on models, which comprises the following steps of: establishing a data hierarchical model; establishing a data type model; establishing a rule configuration model; based on the data hierarchical model, the data type model and the rule configuration model, forming a data template; according to data of a real type of aircraft, carrying out interface data design on the real type of aircraft in a form of the data template; carrying out statistics and analysis on designed interface data; and processing the interface data to generate an ICD file for a designer to use or generate a header file to be directly provided for a developer. According to the interface management method, the modeling idea is used as the core and interface design and management of an aeronautics electronic system on the basis of the uniform data are implemented; and meanwhile, data interaction with the integral aeronautics electronic system about the design process can be implemented. According to the present invention, interface management can be carried out and data support can be provided in the integral developing process of the aeronautics electronic system.
Description
Technical field
The invention belongs to avionics field, relate to the interface management of avionics system, be specifically related to a kind of avionics system interface managerial method based on model.
Background technology
Traditional avionics system interface management for be with 1553B/ARINC429 etc. for the low speed bus of representative is for core, centered by low speed bus, carry out whole system design, and undertaken designing and managing by the mode of document.When avionics new technology comprehensive based on a new generations of the frameworks such as IMA, AFDX or ARINC653, along with being doubled and redoubled of quantity of information, System Resources Sharing demand, the traditional approach of the working experience of simple dependence designer has been difficult to realize the reasonable distribution to resource, needs badly and adopts new method for designing and instrument.
In addition, specific design and practical experience show, need new method for designing and instrument to promote work efficiency.First, for civil aircraft Airworthiness Certification process, need to provide complete from the accordance evidence being designed into checking, not only workload is huge to adopt the R&D Approach centered by document, and be difficult to ensure the consistance between document data and integrality, bring thick-and-thin to evidence obtaining work.Secondly, the experience accumulated in a ripe type design, be also difficult to directly be applied in the design of new model by the mode of document, the effective accumulation and the knowledge sharing that affect R&D process knowledge are multiplexing.
In view of the above-mentioned technological deficiency of prior art, in the urgent need to developing a kind of novel avionics system interface managerial method.
Summary of the invention
The object of this invention is to provide a kind of avionics system interface managerial method based on model, it for core, realizes Interface design and the management of the avionics system on uniform data basis with modelling thought.
To achieve these goals, the invention provides following technical scheme: a kind of avionics system interface managerial method based on model, it comprises the steps:
Set up data hierarchal model, described data hierarchal model is used for the hierarchical structure of the whole aircraft of complete description, supports from model level, system-level, subsystem irrespective of size, device level, channel level, message-level, signal level, until all processes of parametric degree;
Set up data type model, described data type model carries out the type of the hardware interface of data transmission between equipment in system and subsystem and equipment for representing, it is divided into different bus data Type models and non-bus data type model;
Set up rule configuration model, described rule configuration model is used for the Communications Protocol Specification based on dissimilar hardware interface, configures the attribute constraint condition of various interface data;
Form data template based on described data hierarchal model, data type model Sum fanction allocation models, described data template is the design template of various interface data, for standardization, describes various interface data to unitized and integrality;
According to the data of true model aircraft, with the form of described data template, interface data design is carried out to true model aircraft;
Statistics and analysis being carried out to the described interface data of design, for designer provides with reference to guiding, ensureing correctness and the reliability of interface data, for data analysis and localization of fault provide effective means; With
Described interface data is generated as ICD document and is directly supplied to developer for designer or generation header file.
Further, wherein, when carrying out interface data design, utilize data center's model to guide for designer, described data center model is the unified specialized standard template knowledge base shared.
Further, wherein, the described avionics system interface managerial method based on model comprises further with the described interface data of the form Display designing of data form, data navigation tree, data hardware configuration topological diagram and device external interface schema.
Again further, wherein, the described avionics system interface managerial method based on model comprise further to user data, daily record data, edition data, user right and multi-person synergy design manage thus realize Data Management Model.
Again further, wherein, carry out statistics and analysis to the described interface data of design to comprise and carry out data statistic analysis, carry out Data integrality analysis, carry out data fit analysis, carry out data redundancy analysis, carry out data-interface specificity analysis and carry out the analysis of signal course.
In addition, set up described rule configuration model comprise set up numerical nomenclature rule, set up specification number create-rule, set up data constraint rule and set up data attribute interconnection constraint rule.
Avionics system interface managerial method based on model of the present invention by abstract to model, system, subsystem, equipment, message, signal and the parameter etc. that use in avionics system Interface design be data hierarchal model, by abstract for different hardware interface types be data type model, and design data and data analysis process is realized based on data template Sum fanction allocation models, normalization and the unified management of data is carried out by data center's model and data management module, interface data is combined closely, makes data publication/change standardization.Meanwhile, realized the inheritance of data by generalized interface model, ensure that each designer obtains versions of data and data are unified, significant increase many designers cooperation efficiency.Design based on model, left-hand seat is convenient, and can ensure data correctness and accordance, the work efficiency of significant increase when mass data defines.Graphic software platform topological structure is provided, makes designer have reflection directly perceived to data message, promote design efficiency.The early-time analysis of design phase can be carried out, for designer's decision-making provides foundation, and the analysis of signal course can be provided after failure, improve fault analysis and location efficiency.Can automatically generate ICD document and header file, not only alleviate the workload of design and development personnel, also assures that the correctness of document and data.Based on the design of model, make data have good standardization, can carry out good data interaction with other instrument of using in avionics system design process, the significant increase inheritability of data, has broken the data silo in Interface design work.
Accompanying drawing explanation
Fig. 1 is the formation schematic diagram of the system used based on the avionics system interface managerial method of model of the present invention.
Fig. 2 is Lv0 to the Lv7 level avionics system data model structure of OEM maturation.
Fig. 3 is the schematic flow sheet of the avionics system interface managerial method based on model of the present invention.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described, and the content of embodiment is not as the restriction to protection scope of the present invention.
The invention provides a kind of avionics system interface managerial method based on model, its with modelling thought for core, realize Interface design and the management of the avionics system on uniform data basis, can in the whole process of avionics system research and development, carry out interface management and Data support is provided.
Fig. 1 shows the formation schematic diagram of the system used based on the avionics system interface managerial method of model of the present invention.As shown in Figure 1, described interface management system comprises data hierarchal model, data type model, rule configuration model, data template, design data module, database, data analysis module and common interface module etc.
Wherein, described data hierarchal model is used for the hierarchical structure of the whole aircraft of complete description, supports from aircraft-level (i.e. model level), system-level, subsystem irrespective of size, device level, channel level, message-level, signal level, until all processes of parametric degree.
Described data hierarchal model is the core content of interface management system of the present invention.Top-down and the design cycle according to the system latitude of aircraft, progressively refinement goes out the data hierarchal model of aircraft, that is, use external OEM ripe Lv0 to the Lv7 level avionics system data model structure shown in Fig. 2, the hierarchical structure of the whole aircraft of complete description.Like this, by described data hierarchal model, the hierarchical structure of whole aircraft can be described out.As shown in Figure 2, for the aircraft of certain model, its data hierarchal model mainly comprises aircraft-level (i.e. model level), system-level, subsystem irrespective of size, device level, channel level, message-level, signal level and parametric degree.Wherein, below model, comprise multiple system, below each system, comprise multiple subsystem, each subsystem comprises multiple equipment, have different passages between equipment from equipment, carried out the transmission of message between equipment by described passage, described message is made up of multi-signal and parameter again.By whole aircraft is carried out layering, form hierarchical structure, contribute to designing its interface data and managing.
Described data type model is for representing the type of the hardware interface carrying out data transmission in system and subsystem irrespective of size between equipment and equipment.Under normal circumstances, described data type model is divided into different bus data Type models and non-bus data type model.
Described data type model is the important component part of interface management system.According to the type of hardware interface conventional in avionics system design process, progressively refinement goes out the type of the hardware interface carrying out data transmission in system and subsystem irrespective of size between equipment and equipment, and with the model split of Type model for different bus data Type models and non-bus data type model.Wherein, bus data Type model mainly comprises the numerous types of data models such as 1553B bus, RS422 bus, FC bus, 1394 buses and ARINC429 bus.But not bus data Type model mainly comprises the multiple non-bus data type models such as discrete signal, reference signal, simulating signal, sound signal, vision signal.
For the aircraft of same model, no matter adopt the hardware interface of which kind of type, namely, no matter adopt which kind of data type model, model level in described data hierarchal model, system-level, subsystem irrespective of size are all the same with the interface data of device level, that is, these interface data can not change along with the difference of hardware interface type.And the interface data of channel level, message-level, signal level and parametric degree can along with hardware interface type, that is, the difference of data type model and different.
Described rule configuration model is used for the Communications Protocol Specification based on dissimilar hardware interface, configures the attribute constraint condition of various interface data.For the interface data of channel level, message-level, signal level and parametric degree, they can be different along with the difference of the hardware interface type adopted.And dissimilar hardware interface has different Communications Protocol Specification, in order to meet the requirement of these Communications Protocol Specification, make these interface data must meet certain attribute constraint.And described rule configuration model is just used to these interface data configuration attribute constraint conditions.
How efficient configuration rule is provided, so that interface data designer is faster, carry out interface data design expediently in order to give interface data designer further.In the present invention, described rule configuration model generally includes the important rule such as numerical nomenclature rule, specification number create-rule, data constraint rule, data attribute interconnection constraint rule.Wherein, described numerical nomenclature rule is for defining the rules such as length character format satisfied needed for the title of model, system, subsystem, equipment, passage, message and signal.Described specification number create-rule is for defining the automatic create-rule of specification number of the attribute item of passage, message, signal and parameter under the dissimilar hardware interface of configuration.Described data constraint rule is used for the Communications Protocol Specification based on dissimilar hardware interface, defines the protocol rule of the attribute item demand fulfillment of various interface data.Described data attribute interconnection constraint rule is used for the interconnection constraint relation rule between the different attribute item of defining interface data.By described rule configuration model, the particular restriction rule of the docking port data that may occur when can meet design in varied situations.
Described data template is the design template of various interface data.It is for standardization, describe various interface data to unitized and integrality.This data template is based on described data hierarchal model, data type model Sum fanction allocation models and being formed.
Described data template is the element of interface management system of the present invention.The interface data of avionics system, based on above-mentioned data hierarchal model and data type model, is divided into data hierarchal model and the different types of data model of multiple association by interface management system of the present invention.And described data template is according to level and hardware interface type, by the determinant attribute of level and the Communications Protocol Specification requirement of dissimilar hardware interface, the Communications Protocol Specification such as such as 1553B standard, ARINC429 bus specification, 1394 bus specifications, carry out templating process in the mode of model, i.e. the data template of the determinant attribute formation of the different level of abstract extraction and hardware interface simultaneously.
In the present invention, because the interface data of aircraft-level (i.e. model level), system-level, subsystem irrespective of size and device level is not because data type, namely hardware interface type is different and different, so, in the present invention, for the aircraft of a model, only has a model data template; For a system of the aircraft of this model, only has a system data template; For a subsystem of the aircraft of this model, only has a subsystem data template; For an equipment of the aircraft of this model, only has a device data template.Wherein, described model data template mainly comprises the core attribute such as model identification and model abbreviation.Described system data template mainly comprises the core attribute such as the subsystem title under system banner, system abbreviation, Chinese, system and the device name under system.Described subsystem data template mainly comprises the core attribute such as the device name under subsystem identification, subsystem abbreviation, Chinese and subsystem.Described device data model mainly comprises the core attribute such as device identification, equipment abbreviation, Chinese, equipment performance.
Meanwhile, in the present invention, because the interface data of channel level, message-level, signal level and parametric degree can according to hardware interface type, i.e. the difference of data type and different.Therefore, in the present invention, channel data template, message data template, signal data template and supplemental characteristic template have multiple, and it is according to hardware interface type, that is, the difference of data type and different.
As previously described, conventional data type model comprises 1553B bus, RS422 bus, FC bus, 1394 buses and ARINC429 bus etc.And the core attribute of the various interface data of different types of data differs greatly, below for 1553B bus, the hardware interface type of 1553B bus is described, i.e. the determinant attribute of channel data template, message data template, signal data template and supplemental characteristic template under the data type model of 1553B bus.Wherein, the channel data template of 1553B bus mainly comprises device identification, the core attribute such as device end type and No. RT, equipment of carry under bus ID, bus abbreviation, bus type, bus.The message data template of 1553B bus mainly comprises message name, message identifier, specification number, message source, targets of messages, communication format, transport-type, permission interruption, system state, rewriting permission, message-length, refresh cycle, maximum-delay, message comprise specification of signals number, the core attribute such as signal name and signal length.The core attribute such as parameter field, supplemental characteristic position, parameter name that the signal data template of 1553B bus mainly comprises signal name, signal identification, specification number, signal type, signal source, signal target, signal format, range of signal, computation rate, resolution, precision, MSB, LSB, unit, distribution, signal comprise.The supplemental characteristic template of 1553B bus mainly comprises parameter name, parameter type, parameter bits number, sign bit, unit, maximal value, minimum value, precision, LSB, MSB, sign bit on the occasion of core attribute such as implication, bit value and value implications.
Certainly, in various data template, except there is core attribute described above, also comprise some the attribute constraint rules according to described rule configuration model configuration.
Like this, for the aircraft of a model, for it devises complete data template.When designing its any interface data, corresponding data template can both be found, interface data design will be carried out according to the form of described data template.Therefore, realize the standardized management of data, unitized management and Integrity Management by Templated model data mode, effectively improve work efficiency and the work standardization design process of designer.
Described design data module is used for the data according to true model aircraft, with the form of described data template, carries out interface data design to true model aircraft.Described design data module is the important implementation of interface management system.Because the various interface data for whole avionics system have all designed data template, so when the interface data design carrying out true model aircraft, only need to fill each data template according to the data of true model aircraft in described design data module, after each data template populated, also just complete the interface data design effort of this true model aircraft.Particularly, can according to each attribute of the data stuffing of actual signal aircraft aforesaid model data template, system data template, subsystem data template and device data template.Meanwhile, according to adopted hardware interface type, i.e. data type model, fill in each attribute of corresponding channel data template, message data template, signal data template and supplemental characteristic template.Treat each attribute of these data templates all fill complete after, just achieve the design of the interface data to concrete facticity model aircraft.
Certainly, interface management system of the present invention may further include data center's model.Wherein, described data center model is the unified specialized standard template knowledge base shared, for guiding for designer's design interface data.
In the present invention, the interface data and method for designing etc. thereof of existing model aircraft is stored in the specialized standard template knowledge base that described unification is shared.By the specialized standard template knowledge base that described unification is shared, provide example and guide for designer carries out interface data design, be convenient to the design that designer carries out interface data.
Preferably, in the present invention, the specialized standard template knowledge base that described unification is shared comprises signal pond and signal domain.Comprise based on the good basis signal data of signal data template formal definition in described signal pond, designer shares interface by knowledge base, the basis signal data that can obtain needed for selection and then the data directly quoting signal pond, thus without the need to the definition signal that starts anew, alleviate work load, promote work efficiency.
Comprise based on the good underlying parameter data of supplemental characteristic template formal definition in described signal domain, designer shares interface by knowledge base, the underlying parameter data that can obtain needed for selection and then the data directly quoting signal domain, thus without the need to the defined parameters that starts anew, effectively improve work efficiency.
In addition, the specialized standard template knowledge base that described unification is shared also can comprise the shared knowledge and general specification that designer shares, and for realizing data sharing function, providing support for other designer carries out interface data design and helping.
Certainly, the interface data designed in described design data module, after processing and sorting, also can be stored in described data center model, thinks that interface data design next time provides example and guide.
Described database, for being stored in the interface data designed in described design data module, namely supports the storage of the interface data completed in design process.The main database supporting to commonly use at present, as databases such as Oracle, SQL Server.Meanwhile, described database can provide data basis for follow-up data display module, data analysis module, data management module, document creation module and common interface module.
Described data analysis module, for realizing the statistics and analysis of designed interface data, for designer provides with reference to guiding, ensures correctness and the reliability of interface data, for data analysis and localization of fault provide effective means.
In the present invention, described data analysis module mainly completes the statistics and analysis function of the interface data of a certain model aircraft.Described data analysis module comprises data statistic analysis submodule, Data integrality analysis submodule, data fit analyzes submodule, data redundancy analysis submodule, data-interface specificity analysis submodule and signal course analyze submodule.By the analysis of the interface data to a certain model aircraft, for designer provides with reference to guiding, ensure correctness and the reliability of interface data, for data analysis and localization of fault provide effective means.
Wherein, described data statistic analysis submodule is used for the statistic of classification interface data of a certain model aircraft being carried out to system quantity, number of devices, number of channels, message number, number of signals and number of parameters, and shows with the form of attribute area.Support the concrete statistics list of system, equipment, passage, message, signal and the parameter under this model aircraft of display simultaneously, facilitate designer to carry out checking statistic analysis result.
Described Data integrality analysis submodule is used for carrying out integrity analysis to the attribute of described data template.Because interface management system of the present invention is element with data template, by carrying out integrity analysis to whether the attribute of abstract definition in data template is complete, effectively can reduce indispensable attributes and omitting risk, improving the integrality of data.
Described data fit is analyzed submodule and is used for carrying out rule match Inspection and analysis to the attribute in described data template.In the present invention, described interface management system take data template as element, and in described rule configuration model, define the constraint condition of the attribute of each data template, the accordance analysis of interface data is realized by carrying out rule match Inspection and analysis to the attribute in described data template, effectively can improve the accordance of interface data and general specification, promote the reliability of interface data.
The substantial amounts of the interface data of a certain model aircraft, and multi-person synergy design easily causes design iterations and produces redundant data.Described data redundancy is analyzed submodule and is analyzed by determinant attributes such as the data name to same level data, abbreviations, analysis is carried out and alarm prompt to identical redundant data, effective guide design personnel reduce redundant data design, improve high efficiency and the parsimony of design data.
Described data-interface specificity analysis submodule is used for realizing data-interface specificity analysis.In the present invention, interface for important component part, is divided into multiple bus type and non-bus type with data type model by described interface management system.By realizing data-interface specificity analysis based on the data analysis algorithm of different bus, as by defined 1553B bus master data attribute, the model related data of statistical study, data bus line load characteristics algorithm and bus efficiency characteristics algorithm, calculate bus load and bus efficiency, real-time query interface features data, and alarm prompt is carried out to the data exceeding load, guide design personnel carry out reasonable distribution and design, improve the stability of design data.
Signal data stream between design data module definition equipment, meanwhile, the device interior input signal defined in logical design and the logic association relation of output signal.Described signal course is analyzed submodule and can be realized signal data and send signal, signal by the tracking of a series of signal transmitting procedures such as distinct device transmitting procedure and receiving equipment Received signal strength from transmitting apparatus, and with visual signal course figure mode display transmitting procedure.Designer can by the concrete operations of reviewing stream signal and tracking downstream signal in signal course figure, realize to signal from be sent to reception whole transmitting procedure check and review tracking operation, guide design personnel check Signal transmissions course fast, signal fault localization method is provided, that carries out design process affects localization of fault, improves the reliability of design data.
Described common interface module is used for for the upstream tool of this interface management system and downstream tool provide data inheritance and succession, and can provide Data support for carrying out between other instrument data interaction.
Interface management system of the present invention bears important Interface design function in avionics system Life cycle unified model.Therefore, described interface management system not only needs the framework data model inheriting upstream, needs to provide the data model supporting that downstream is designed simultaneously.So, theoretical based on life cycle unified model, the common interface module of described interface management system needs the frequently-used data interface (as framework model data such as Doors, AADL and Rhapsody) supporting upstream, also needs to support and provides the frequently-used data interface of downstream design (as VapsXT, AFDX configuration tool file, the multiple ICD interface data such as IDL, WSDL).By described common interface module, realize the inheritance of avionics system data and hand down design, also for data interaction between other instrument (such as emulation tool etc.) of using in this interface management system and avionics system design process provides Data support.Realized the succession function of interface data by described common interface module, effectively reduce the error probability of data transmission, reduce the design iterations process in data transmission procedure and repeating data, improve the design efficiency of avionics system.
In addition, in the present invention, described interface management system may further include data display module.Described data display module is used for the described interface data of the form Display designing of data form, data navigation tree, data hardware configuration topological diagram and device external interface schema.
Wherein, the data form of a certain model aircraft mainly comprises the channel data list of model data list, system data list, subsystem data list, device data list and different types of data, message data list, signal data express and supplemental characteristic list.Designer, according to aforesaid data hierarchal model, shows the determinant attribute of different layers DBMS in the data of a certain model aircraft, intuitively effectively shows data attribute with the form of data form.
The navigation tree of a certain model aircraft mainly realizes with two kinds of navigation tree forms in interface management system, i.e. bus view and system view.Wherein, bus view is that data hierarchal model is carried out level display with bus (that is, interface) for main perspective, shows the data under this model under different types of data and data hierarchical relationship.And system view is that main perspective carries out level display data hierarchal model with system/device, show data correlation relation between the data of distinct device under this model and equipment.Like this, two levels hierarchal model tree clearly can be formed, improve the design efficiency of designing user.
Described data hardware configuration topological diagram is for showing the physical interface topological diagram between the equipment that designed in a certain model aircraft, and the phase is divided into facility center management visual angle and visual angle centered by passage.Can classify as required and show the topological structure of a certain system/device in facility center management visual angle, the physical topology annexation of interface types different between display current device and miscellaneous equipment.Centered by passage, visual angle is the topological diagram structure of equipment under a certain passage of display of classifying as required, shows the physical topology annexation of the interface of all devices under a certain passage, increases the efficient visualized operation that interface management mode realizes.
Described data equipment external interface figure is for showing the interface schema of the external message signal between the equipment that designed in a certain model aircraft, namely, visual angle centered by a certain equipment, the information stream transmission mode between display current device and miscellaneous equipment and the incidence relation of transmission.Designer, by the data hardware configuration topological diagram of equipment physical interface and the device external interface schema of equipment room data stream relation, comprehensively realizes the visualized operation of model data interface.
And in the present invention, preferably, described interface management system comprises data management module further.Described data management module is used for managing the design of user data, daily record data, edition data, user right and multi-person synergy thus realizing Data Management Model.
In the present invention, described data management module is mainly through realizing Data Management Model to user data management, daily record data management, edition data management, user authority management and multi-person synergy design management.By this data management module, designer's electronization unified management Interface design data can be realized, improve data management efficiency, for data referencing and data query provide pacing items.
Specifically, user data management refers to that described data management module passes through user data, and user role and user department carry out designing and recording related data, realize managing the information of designer.Daily record data management refers to that described data management module uses C/S (client and server) architecture mode, designer passes through client operation, there are the concrete operations of user in the mode administrative institute of server record, and forms Operation Log and carry out way to manage realization.Edition data management refers to that described data management module is arranged by plaintext and baseline set-up mode forms version structural drawing.Owing to achieving electronized data administration, version management support is checked and restore funcitons old version, and supports hierarchal model versions of data comparing function between different editions.Because described interface management system is for core content with data hierarchal model, realize the design function of different designs personnel to data, therefore, described data management module, by the distribution incidence relation of personnel and data level modelling function, realizes the management function of designer's design authority.Multi-person synergy design management refers to that described data management module manages data interaction relation between different clients user based on C/S, namely, the data interlock of same time design module and unlocking function, multi-person synergy design module, by the management of interaction data transfer function, ensures that the design conflicts process of designer is normally avoided in data interaction.
Finally, in the present invention, preferably, described interface management system comprises document files generation module further.Described document files generation module is directly supplied to developer for the ICD document generating WORD and PDF for designer or generation header file.
Particularly, described document files generation module mainly comprises document structure tree submodule and file generated submodule.Described document structure tree submodule can generate the ICD document of WORD and PDF for designer, also can generate header file and directly be supplied to developer.Designer realizes the mutual exchange and conmmunication function of personnel by document and data file, and the document data of generation provides important data foundation for next stage works.
Meanwhile, described document structure tree submodule comprises versatile customization document structure tree submodule and configurable document structure tree submodule.Described versatile customization document structure tree submodule is the general file generation template based on specific design unit, realizes WORD, PDF, EXCEL data file of deriving set form.And described configurable document structure tree submodule is the mode by the basic setup of document template configurator configuration input document, realize deriving WORD, PDF, EXCEL data file meeting configuration requirement.
Described file generated submodule is the document format data such as header file (.h), Xml of being specified by the data genaration that designer designs.
Fig. 3 shows the schematic flow sheet of the avionics system interface managerial method based on model of the present invention.As shown in Figure 3, when the avionics system interface management utilizing above-mentioned interface management system to carry out based on model, be first set up data hierarchal model.That is, the data hierarchal model of a certain model aircraft is set up, with the hierarchical structure of the whole aircraft of complete description.Described data hierarchal model mainly comprises model level, system-level, subsystem irrespective of size, device level, channel level, message-level, signal level and parametric degree.
Secondly, be set up data type model.That is, according to the type of carrying out the hardware interface of data transmission between the equipment in the system of this model aircraft and subsystem and equipment, its data type model is determined.If which employs different hardware interface types, namely have employed different buses and carry out transmission of messages, so it will have multiple different data type model.
Again, be set up rule configuration model.That is, according to the Communications Protocol Specification of its hardware interface adopted, the attribute constraint condition of various interface data is configured, with the requirement making interface data meet the Communications Protocol Specification of adopted hardware interface.
Then, data template is formed based on described data hierarchal model, data type model Sum fanction allocation models.The data template formed is the design template of various interface data, for standardization, describes various interface data to unitized and integrality.
Next be exactly the data according to true model aircraft, with the form of described data template, interface data design carried out to true model aircraft, thus form corresponding interface data.Designed interface data is stored in corresponding database, so that follow-up docking port data carry out various operation and process.
After interface data has designed, docking port data can carry out various operation and process.Such as, statistics and analysis being carried out to the described interface data of design, for designer provides with reference to guiding, ensureing correctness and the reliability of interface data, for data analysis and localization of fault provide effective means.Carry out statistics and analysis to the described interface data of design can comprise and carry out data statistic analysis, carry out Data integrality analysis, carry out data fit analysis, carry out data redundancy analysis, carry out data-interface specificity analysis and carry out the analysis of signal course.
Also described interface data can be generated as ICD document and directly be supplied to developer for designer or generation header file.
Meanwhile, also can with the described interface data of the form Display designing of data form, data navigation tree, data hardware configuration topological diagram and device external interface schema.
Further, can manage the design of user data, daily record data, edition data, user right and multi-person synergy thus realize Data Management Model.
In addition, also by generalized interface model, designed interface data and upstream and downstream instrument can be carried out data interaction.
The above embodiment of the present invention is only for example of the present invention is clearly described, and is not the restriction to embodiments of the present invention.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here cannot give exhaustive to all embodiments.Every belong to technical scheme of the present invention the apparent change of extending out or variation be still in the row of protection scope of the present invention.
Claims (6)
1., based on an avionics system interface managerial method for model, it comprises the steps:
Set up data hierarchal model, described data hierarchal model is used for the hierarchical structure of the whole aircraft of complete description, supports from model level, system-level, subsystem irrespective of size, device level, channel level, message-level, signal level, until all processes of parametric degree;
Set up data type model, described data type model carries out the type of the hardware interface of data transmission between equipment in system and subsystem and equipment for representing, it is divided into different bus data Type models and non-bus data type model;
Set up rule configuration model, described rule configuration model is used for the Communications Protocol Specification based on dissimilar hardware interface, configures the attribute constraint condition of various interface data;
Form data template based on described data hierarchal model, data type model Sum fanction allocation models, described data template is the design template of various interface data, for standardization, describes various interface data to unitized and integrality;
According to the data of true model aircraft, with the form of described data template, interface data design is carried out to true model aircraft;
Statistics and analysis being carried out to the described interface data of design, for designer provides with reference to guiding, ensureing correctness and the reliability of interface data, for data analysis and localization of fault provide effective means; With
Described interface data is generated as ICD document and is directly supplied to developer for designer or generation header file.
2. the avionics system interface managerial method based on model according to claim 1, it is characterized in that, when carrying out interface data design, utilize data center's model to guide for designer, described data center model is the unified specialized standard template knowledge base shared.
3. the avionics system interface managerial method based on model according to claim 2, it is characterized in that, comprise further with the described interface data of the form Display designing of data form, data navigation tree, data hardware configuration topological diagram and device external interface schema.
4. the avionics system interface managerial method based on model according to claim 3, it is characterized in that, comprise further and the design of user data, daily record data, edition data, user right and multi-person synergy is managed thus realizes Data Management Model.
5. the avionics system interface managerial method based on model according to claim 4, it is characterized in that, statistics and analysis is carried out to the described interface data of design and comprises and carry out data statistic analysis, carry out Data integrality analysis, carry out data fit analysis, carry out data redundancy analysis, carry out data-interface specificity analysis and carry out the analysis of signal course.
6. the avionics system interface managerial method based on model according to claim 5, it is characterized in that, set up described rule configuration model comprise set up numerical nomenclature rule, set up specification number create-rule, set up data constraint rule and set up data attribute interconnection constraint rule.
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