CN102750301A - Blueprint generating method for integrated avionic system model aiming at architecture analysis and design language (AADL) description - Google Patents
Blueprint generating method for integrated avionic system model aiming at architecture analysis and design language (AADL) description Download PDFInfo
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Abstract
The invention relates to a blueprint generating method for an integrated avionic system model aiming at architecture analysis and design language (AADL) description. The blueprint generating method includes the following steps: 1 modeling: building the avionic system model from bottom to top in an AADL modeling environment: 1.1 modeling a hardware structure; 1.2 modeling a software structure; 1.3 building a mapping relation model from software to hardware; 1.4 building a distributed system model which comprises a distributed software model, a distributed hardware model and the mapping relation model from software to hardware; 2 automatically generating a blueprint according to the avionic system model; and 3 enabling a user to upload a blueprint file to a target machine. The blueprint generating method solves the technical problem that time and labor are wasted and errors can be caused easily when the current users manually edit the blueprint file, automatically generates the blueprint in operation aiming at the avionic system model established by the AADL, prevents the users from manually editing the blueprint file and improves blueprint generating efficiency.
Description
Technical field
The present invention relates to synthetic aviation electronic system modeling technique field, relate in particular to the blueprint generation method of the synthesization avionics system model of describing to AADL.
Background technology
In synthesization, modularization avionics system, the general-purpose system management software is responsible for the operation of whole synthesization avionics system, realizes the control and the management of resource, workflow, pattern control, fault recovery and information security through user configured blueprint file.According to the characteristics of synthesization, modularization avionics system, use AADL to set up the avionics system model, verify user's design through various analysis tools, be at present at the research focus of avionics system modeling direction.When user's avionics system that finally operation is comprehensively accomplished in real environment, blueprint file in the time of also need moving.Usually the user can be through the blueprint file at xml editing machine inediting xml form, blueprint file when the scale-of-two blueprint file that then the blueprint file conversion of xml form is become can load obtains to move.But when using AADL to set up the avionics system model; Data in the blueprint file have been reflected to model and have suffered; Manually write the blueprint file for fear of the user, the present invention proposes a kind of blueprint information of from the avionics system model, extracting, generation can load the method for scale-of-two blueprint file automatically.This method has improved synthesization avionics system development efficiency, practices thrift development and maintenance cost, and the credibility that improves software systems is had great importance.
Summary of the invention
When solving existing user manual editing blueprint Document Charge, the technical matters taking a lot of work, be prone to make mistakes; The invention provides a kind of blueprint generation method of synthesization avionics system model of the AADL of being directed against description; The present invention is directed to the avionics system model that AADL sets up, automatically blueprint during generating run.
The technical solution that the present invention had:
The blueprint generation method of the synthesization avionics system model that a kind of AADL of being directed against describes: its special character is: may further comprise the steps:
1] modeling: the user is the bottom-up avionics system model of setting up in the AADL modeling environment:
1.1] to the hardware configuration modeling:
1.1.1] set up the corresponding processing model of element to all processing units in the avionics system,
Said processing unit model comprises that the attribute information of corresponding processing unit is described and configuration powers on test model; The attribute information of said processing unit is described and is comprised physical I D;
1.1.2] set up functional block model to all the general utility functions modules (CFM) in the avionics system; Comprise from step 1.1.1 in the said functional block model] the processing unit model, the communication interface model that attribute information is described and the general utility functions module comprises of corresponding general utility functions module chosen in the processing unit model set up, the attribute information of said general utility functions module comprises general utility functions module type and slot number; The said processing unit model of choosing is at least one, and the physical I D of the said processing unit model of choosing and the slot of general utility functions module are number corresponding;
1.1.3] set up the distributed hardware model to hardware platform in the avionics system; Said distributed hardware model comprises that at least one is from step 1.1.2] the functional block model chosen in the functional block model set up, said distributed hardware model is chosen corresponding functional block model according to function;
1.2] to the software configuration modeling:
1.2.1] set up the application partition model to the application partition that operates on the processing unit,
The attribute information that comprises a plurality of process models, the port model that is used to communicate by letter, health monitoring model and corresponding application partition in the said application partition model is described, and the attribute information of said corresponding application partition is described and comprised the zone name of application partition, memory size and the application partition type that application partition takies;
Said process model comprises the attribute information description of process model, and the attribute information of said process model comprises process name, base priority, cycle and off period,
Said port model comprises the attribute information description of port model, and the attribute information of said port model comprises port type and transmission mode;
Said health monitoring model comprises the attribute information description of health monitoring model, and the attribute information of said health monitoring model comprises type of error, running status and handles the address;
1.2.2] set up corresponding TLS model to the RE level of avionics system; The attribute information that comprises at least one application partition model, at least one TLS logic configuration model, at least one dispatch list model, fault filtering model, fault filtering device model, the TLS channel pattern that is used to communicate by letter and transmission link model, health monitoring model and TLS model in the said TLS model is described
The application partition model that comprises in the TLS model be the TLS model according to function from step 1.2.1] choose a corresponding a kind of operational mode configuration of TLS logic configuration model the application partition model set up;
1.2.3] set up all IA level models to the IA level of avionics system; Comprising that at least one is from step 1.2.2 in the said IA level model] attribute information of TLS model, at least one IA logic configuration model, fault filtering model, fault filtering device model and the IA level model chosen according to function the TLS model set up describes a corresponding a kind of operational mode configuration of IA logic configuration model;
1.2.4] set up AC level model to the AC level of avionics system; Said AC level model comprise managed zero to a plurality of IA level models, zero to a plurality of TLS models, at least one AC level logic configuration model,, the attribute information of fault filtering model, fault filtering device model and AC level model describes, the attribute information of said AC level model comprises the TLS model identification at AC level model place;
1.2.5] set up AC level action model, IA level action model and RE level action model,
1.2.6] be that AC level model is chosen AC level action ID set according to function from AC level action model; For IA level model is chosen IA level action ID set according to function from IA level action model; For the TLS model is chosen RE level action ID set according to function from RE level action model
1.2.7] set up the distributed software model, said distributed software model comprises AC level model, AC level action model, IA level action model and RE level action model
1.3] set up the mapping relations model of software to hardware;
1.4] set up Distributed System Model: said Distributed System Model comprises distributed software model, distributed hardware model and the software mapping relations model to hardware;
2] generate blueprint automatically according to the avionics system model:
2.1] legitimacy of inspection avionics system model:
2.1.1] integrality (i.e. whether inspection lacks the configuration information of certain part in the blueprint) of inspection avionics system model structure, the project of inspection is: whether AC level, IA level and TLS level exist corresponding action ID set, fault filtering model and fault filtering device model; Whether there are health monitoring model, process model in the application partition model; Whether there is AC level action model, IA level action model and RE level action model and software mapping relations model to hardware;
2.1.2] attribute information of inspection avionics system model;
2.2] user disposes blueprint data when from the avionics system model, extracting operation:
2.2.1] from the distributed hardware model, obtain the functional block model information of choosing,
TLS model 2.2.3] from the processing unit model, obtain attribute information, the configuration detecting information that powers on of corresponding processing unit,
2.2.4] from AC level model, obtain managed zero to a plurality of IA level model informations, zero attribute information to a plurality of TLS model informations, at least one AC level logic configuration model information, fault filtering information, fault filtering device information and AC level model,
2.2.5] from IA level model, obtain the attribute information of TLS model information, at least one IA logic configuration information, fault filtering information, fault filtering device information and the IA level model chosen,
2.2.6] from the TLS model, obtain the attribute information of application partition model information, TLS logic configuration information, at least one schedule information, fault filtering information, fault filtering device information, the TLS channel information that is used to communicate by letter and transmission link information, health monitoring model information and TLS model
2.2.7] obtain the mapping relations information of software in the mapping relations model from software to hardware to hardware;
2.2.8] obtain attribute information, interface message, barrier filtering information, fault filtering device information, action message and the action ID aggregate information of each unit of corresponding avionics system in each model from the avionics system model of being set up:
2.3] according to the logical organization of distributed software model; Generate the data that the system management in the blueprint file is used, the data that said system management is used comprise the initial communication configuration data of GSM zone configuration data, TLS initial logic configuration data, aircraft-level initial logic configuration data, AC level module and each module;
2.4] with step 2.2] and in the user that obtains dispose blueprint data and step 2.3] in the system management that obtains use data combination, form complete blueprint data, store in the xml file with set form;
2.5] according to the requirement of target machine program with step 2.4] in the complete blueprint data that forms generate the scale-of-two blueprint file that can load from the xml form;
3] user loads the blueprint file to target machine.
Technical solution of the present invention:
1, the present invention generates blueprint automatically through setting up the avionics system model, has avoided the user manually to write the blueprint file, when having solved existing user manual editing blueprint Document Charge, the defective taking a lot of work, be prone to make mistakes, improves the blueprint formation efficiency.
2, the present invention has improved the reliability of data through the validity checking to the avionics system model.
3, the present invention proposes a kind of blueprint information of from the avionics system model, extracting, generation can load the method for scale-of-two blueprint file automatically.This method has improved synthesization avionics system development efficiency, practices thrift development and maintenance cost, and the credibility that improves software systems is had great importance.
4, the present invention is through carrying out validity checking to the avionics system model; Characteristics and requirement according to synthesization, modularization avionics system; The model that the user is set up carries out validity checking; Improve the accuracy of modeling, mainly check two aspect contents, to the inspection of model structure with to the inspection of the property value in the model.To model structure inspection purpose is the integrality of inspection model, i.e. whether inspection lacks the configuration information of certain part in the blueprint.The inspection of the property value in the model is guaranteed the validity and the legitimacy of data.
Description of drawings
Fig. 1 synthesization, modularization avionics system unit software configuration;
Fig. 2 general-purpose system management software system structure;
Fig. 3 synthesization, modularization avionics system hardware configuration;
Fig. 4 xml form blueprint data structure (one);
Fig. 5 xml form blueprint data structure (two);
Fig. 6 xml form blueprint data structure (three);
Fig. 7 can load the blueprint data file layout.
Embodiment
Relation in synthesization, the modularization avionics system between two general utility functions modules (CFM) is as shown in Figure 1, and the three-decker of general-purpose system management software is as shown in Figure 2.The management of AC level system is responsible for control and is monitored whole synthesization, modularization avionics system IMA (Integrated Module Avionics).The a certain sub-function module of control is responsible in the management of IA level system, and the management of RE level system is the system management of the bottom, is in charge of the function of single PE (Processing Element).Synthesization, modularization avionics system hardware configuration are as shown in Figure 3.
Before generating the blueprint file, the user need be in the AADL modeling environment the bottom-up model of setting up avionics system.Soft, the modeling of hardware configuration proceed step by step according to the avionics system that will realize.
Step 1, be to the modeling procedure of hardware configuration:
1. set up all processing unit models, each processing unit comprises a CPU, and the processing unit attribute informations such as cpu type, physical I D, memory size that processing unit is set are described, the configuration test model that powers on;
2. set up all functional block models; Comprise a plurality of processing unit models in each modular model; Choose in the processing unit model that these processing unit models were set up from the 1st step, module type, the slot attribute information of modular model is set, and the communication interface that comprises of module;
3. set up avionics system hardware platform model, comprise a plurality of modular models in the hardware platform, choose in the model that these modular models were set up from the 2nd step, according to concrete communicating requirement, the communication interface of link block is to realize these communicating requirements.
Step 2, be to the modeling procedure of software configuration:
1. set up all application partition models; Comprise a plurality of process models in each application partition, communicate by letter with other subregion port that uses, the health monitoring information of use; Attribute informations such as the zone name of each subregion, the memory size that takies, divisional type are set; The attribute information such as process name, base priority, process cycle, off period of the process that each subregion comprises is set, and each subregion comprises attribute informations such as the port type, transmission mode of port;
2. set up all TLS models; Comprise a plurality of application partition models, a plurality of TLS logic configuration model, a plurality of dispatch list model among each TLS, communicate by letter with other TLS and use that passage is connected with transmission, the health monitoring allocation models; The application partition model that comprises among the TLS is chosen from the model that the first step is set up; Every kind of corresponding a kind of operational mode of TLS logic configuration model disposes, and the attribute information of TLS model is set;
3. set up all IA level models, comprise a plurality of three layers of stack (TLS) model among each IA, IA logic configuration model is chosen in the model that the TLS model was set up from second step, and the attribute information of IA model is set;
4. set up AC level model; The AC model is also as the software model of distributed system; It comprises IA model, the TLS model, zero managed and arrives the action lists ID set of a plurality of IA logic configuration models, use, fault filtering table information, the fault filtering device configuration information that uses to a plurality of TLS logic configuration models, 0; IA model, TLS model were selected from second step and the 3rd step, and the attribute information of AC model is set;
5. set up AC, IA and RE level action model;
Software model and hardware model need carry out modeling to the mapping relations of hardware to software after setting up and accomplishing, and set up Distributed System Model then.The model that Distributed System Model comprises is the mapping relations model of distributed software model, distributed hardware model and software and hardware.
Set up good avionics system model and leave in the work space with document form, these files can be organized in a plurality of engineerings.
Step 3, the step that generates the blueprint file automatically according to the avionics system model are:
1. the avionics system model is carried out validity checking;
2. the data that blueprint needs when from the avionics system model that the user sets up, extracting operation;
3. according to the logical organization of software systems model, the partial data in the relevant blueprint file of automatic creation system;
4. form complete blueprint data by data in the model and the data that generate automatically, and generate the blueprint file of xml form;
5. the blueprint data call format generates the scale-of-two blueprint file that can load from the blueprint file of xml form during according to operation.
Step 1 is accomplished the validity checking to the avionics system model, mainly comprises two aspects, to the inspection of model structure with to the inspection of the property value in the model.To model structure inspection purpose is the integrality of inspection model, i.e. whether inspection lacks the configuration information of certain part in the blueprint, comprising:
---whether AC, IA and TLS level exist action lists ID set configuration, fault filtering table and filter deployment;
---whether there are subregion health monitoring, process configuration in the application partition configuration;
---whether exist action lists and logic to dispose to physical mappings.
Inspection to the property value in the model comprises:
---all length of name can not surpass 30 bytes;
---all paths can not surpass 64 bytes;
---all time wants the time value after check the value and the unit coupling can not surpass long shaping scope;
---duplication of name, double sign inspection.
The main system model of accomplishing of step 2 is imported data extract, and the main models that relates to has distributed hardware system model, software systems model, logic to physical mappings model and action lists model at different levels.
The information of obtaining from the distributed hardware system model comprises:
---each hardware module information: the interface of module type, the processing unit that comprises, use;
---each processing unit information: the test chart that powers on of the name of processing unit, numbering, use.
The information of obtaining from the distributed software system model comprises:
---AC level information: the IA of AC level attribute information, AC level logic configuration information, AC level fault filtering table information, fault filtering device configuration information, action configuration information, the management of AC level, the TLS of AC level management;
---IA level information: the TLS of IA level attribute information, IA level logic configuration information, IA level fault filtering table information, fault filtering device configuration information, action configuration information, the management of IA level;
---TLS information: TLS attribute information, TLS logic configuration information, TLS fault filtering table information, fault filtering device configuration information, action configuration information, system health monitoring, module health monitoring, schedule information, Virtual Channel configuration;
---application partition information: the process configuration information in application partition attribute information, the subregion, port configuration information.
Step 3 is main to be accomplished and generates automatically that the user does not use and data that system management is used, and these data have GSM zone configuration, the configuration of TLS initial logic, the configuration of aircraft-level initial logic, AC module to dispose with the initial logic of each module.Automatically the GSM zone configuration that generates comprises:
---zone attribute;
---all processes that comprise in the subregion;
---all of the port that comprises in the subregion.
Each TLS initial logic configuration:
---network configuration;
---communicating by letter with the GSM subregion, passage, the transmission of using is connected, interface configuration;
---dispatch list.
The configuration of aircraft-level initial logic:
---sub-TLS logic configuration information.
The initial communication configuration of AC and each module:
---the identification information of transmitting terminal and receiving end;
---transmission, reception transmission hyphen that transmitting terminal is communicated by letter with receiving end and used;
---transmitting terminal and receiving end communicate by letter the transmission used, receive transmission and be connected configuration.
Step 4 is accomplished data of extracting in the model and the data combination that generates is automatically formed complete blueprint data, and asks the user to import path and the filename of preserving file, and these data are stored in the xml file with set form.The user can directly use the xml edit tool to open this document, browses and revise this document.The blueprint file data structure is like Fig. 4,5, shown in 6.
Step 5 is accomplished from the blueprint file of xml form and is generated the scale-of-two blueprint file function that can load; The blueprint file of xml form is the file that the people is prone to identification and operation; Binary file then is the file of machine recognition; The blueprint file that this step reads the xml form is set form according to the requirement of target machine program with data organization, finally forms binary data file, and document format data is as shown in Figure 7.
The avionics system model is carried out validity checking; According to the characteristics and the requirement of synthesization, modularization avionics system, the model that the user is set up carries out validity checking, improves the accuracy of modeling; Two aspect contents of main inspection are to the inspection of model structure with to the inspection of the property value in the model.To model structure inspection purpose is the integrality of inspection model, i.e. whether inspection lacks the configuration information of certain part in the blueprint.The inspection of the property value in the model is guaranteed the validity and the legitimacy of data.
The data that blueprint needs when extracting operation are mainly accomplished system model input data extract, and the main models that relates to has distributed hardware system model, software systems model, logic to physical mappings model and action lists model at different levels.The information of obtaining from the distributed hardware system model comprises each hardware module relevant information, each processing unit relevant information.The information of obtaining from the distributed software system model comprises aircraft-level, complex zone level, TLS, subregion relevant information.
The data that automatic creation system is relevant; Accomplish the automatic user of generation and do not use and the data of system management use, these data have the initial logic configuration of GSM zone configuration, the configuration of TLS initial logic, the configuration of aircraft-level initial logic, high-capacity module and each module.GSM zone configuration information has all of the port that comprises in all processes of comprising in zone attribute, the subregion, the subregion.Passage, TC, interface configuration, dispatch list that each TLS initial logic configuration information has network configuration, communicates by letter with the GSM subregion and use.
Form complete blueprint data, accomplish that data of extracting in the model and the data combination that generates are automatically formed complete blueprint data, and ask the user to import path and the filename of preserving file, these data are stored in the xml file with set form.The user can directly use the xml edit tool to open this document, browses and revise this document.
The scale-of-two blueprint file that generation can load is accomplished from the blueprint file of xml form and is generated the scale-of-two blueprint file function that can load; The blueprint file of xml form is the file that the people is prone to identification and operation; Binary file then is the file of machine recognition; The blueprint file that this step reads the xml form is set form according to the requirement of target machine program with data organization, finally forms binary data file.
Embodiment:
With a synthesization, modularization avionics system is example; 4 general modules are arranged in this system, two CPU are arranged on the every plank, software is three-decker; Aircraft-level software resides on the high-capacity module; 1 complex zone of AC management and 3 TLS use the structural modeling instrument in this development platform to set up a synthesization, modularization avionics system model, and the corresponding property value are set for each model.The user when in real environment, moving, needs to use the blueprint file of xml editing machine editor xml form, with the binary data file of blueprint file conversion for loading of XML form after the analysis of carrying out model under the structural modeling platform and design.Manually write the blueprint file for fear of the user, use now and from the avionics system model, extract blueprint information, generation can load the method for scale-of-two blueprint file automatically,
This method job step is:
1. the avionics system model is carried out validity checking, errors present, prompting are presented in the miscue view, the user reexamines model according to the bug patch model, and is legal fully up to model;
2. obtain the data in the model: obtain hardware configuration information, attribute information, obtain software configuration information, AC level information, IA level information, TLS level information, obtain the software and hardware map information;
3. the system architecture of obtaining according to step 2 generates the initial logic configuration of GSM zone configuration at different levels, the configuration of TLS initial logic, the configuration of aircraft-level initial logic, high-capacity module and each module automatically;
4. the data of obtaining according to step 2 and step 3 form complete blueprint data according to the blueprint form, and the prompting user provides storing path and the filename that generates the blueprint file, under this path, preserve the blueprint file of the xml form of generation;
5. be binary file according to the requirement of scale-of-two blueprint file data with the blueprint file conversion of xml form.
Carry out blueprint with the method and generate, can generate the data message relevant automatically, alleviate avionics system modeling personnel's burden, the legitimacy of data in the inspection model, the correctness of raising data with GSM;
The avionics system model of setting up with the AADL modeling tool is the blueprint file that the basis generates the xml form, and the data that make things convenient for the user to browse, revise once more, produce with other instrument merge; The loaded blueprint data file that generates can directly be loaded on the target machine, makes things convenient for the user in true environment, to move debug system.
Claims (1)
1. the blueprint generation method of a synthesization avionics system model of describing to AADL: it is characterized in that: may further comprise the steps:
1] modeling: the user is the bottom-up avionics system model of setting up in the AADL modeling environment:
1.1] to the hardware configuration modeling:
1.1.1] set up the corresponding processing model of element to all processing units in the avionics system,
Said processing unit model comprises that the attribute information of corresponding processing unit is described and configuration powers on test model; The attribute information of said processing unit is described and is comprised physical I D;
1.1.2] set up functional block model to all the general utility functions modules (CFM) in the avionics system; Comprise from step 1.1.1 in the said functional block model] the processing unit model, the communication interface model that attribute information is described and the general utility functions module comprises of corresponding general utility functions module chosen in the processing unit model set up, the attribute information of said general utility functions module comprises general utility functions module type and slot number; The said processing unit model of choosing is at least one, and the physical I D of the said processing unit model of choosing and the slot of general utility functions module are number corresponding;
1.1.3] set up the distributed hardware model to hardware platform in the avionics system; Said distributed hardware model comprises that at least one is from step 1.1.2] the functional block model chosen in the functional block model set up, said distributed hardware model is chosen corresponding functional block model according to function;
1.2] to the software configuration modeling:
1.2.1] set up the application partition model to the application partition that operates on the processing unit,
The attribute information that comprises a plurality of process models, the port model that is used to communicate by letter, health monitoring model and corresponding application partition in the said application partition model is described, and the attribute information of said corresponding application partition is described and comprised the zone name of application partition, memory size and the application partition type that application partition takies;
Said process model comprises the attribute information description of process model, and the attribute information of said process model comprises process name, base priority, cycle and off period,
Said port model comprises the attribute information description of port model, and the attribute information of said port model comprises port type and transmission mode;
Said health monitoring model comprises the attribute information description of health monitoring model, and the attribute information of said health monitoring model comprises type of error, running status and handles the address;
1.2.2] set up corresponding TLS model to the RE level of avionics system; The attribute information that comprises at least one application partition model, at least one TLS logic configuration model, at least one dispatch list model, fault filtering model, fault filtering device model, the TLS channel pattern that is used to communicate by letter and transmission link model, health monitoring model and TLS model in the said TLS model is described
The application partition model that comprises in the TLS model be the TLS model according to function from step 1.2.1] choose a corresponding a kind of operational mode configuration of TLS logic configuration model the application partition model set up;
1.2.3] set up all IA level models to the IA level of avionics system; Comprising that at least one is from step 1.2.2 in the said IA level model] attribute information of TLS model, at least one IA logic configuration model, fault filtering model, fault filtering device model and the IA level model chosen according to function the TLS model set up describes a corresponding a kind of operational mode configuration of IA logic configuration model;
1.2.4] set up AC level model to the AC level of avionics system; Said AC level model comprise managed zero to a plurality of IA level models, zero to a plurality of TLS models, at least one AC level logic configuration model,, the attribute information of fault filtering model, fault filtering device model and AC level model describes, the attribute information of said AC level model comprises the TLS model identification at AC level model place;
1.2.5] set up AC level action model, IA level action model and RE level action model,
1.2.6] be that AC level model is chosen AC level action ID set according to function from AC level action model; For IA level model is chosen IA level action ID set according to function from IA level action model; For the TLS model is chosen RE level action ID set according to function from RE level action model
1.2.7] set up the distributed software model, said distributed software model comprises AC level model, AC level action model, IA level action model and RE level action model
1.3] set up the mapping relations model of software to hardware;
1.4] set up Distributed System Model: said Distributed System Model comprises distributed software model, distributed hardware model and the software mapping relations model to hardware;
2] generate blueprint automatically according to the avionics system model:
2.1] legitimacy of inspection avionics system model:
2.1.1] integrality (i.e. whether inspection lacks the configuration information of certain part in the blueprint) of inspection avionics system model structure, the project of inspection is: whether AC level, IA level and TLS level exist corresponding action ID set, fault filtering model and fault filtering device model; Whether there are health monitoring model, process model in the application partition model; Whether there is AC level action model, IA level action model and RE level action model and software mapping relations model to hardware;
2.1.2] attribute information of inspection avionics system model;
2.2] user disposes blueprint data when from the avionics system model, extracting operation:
2.2.1] from the distributed hardware model, obtain the functional block model information of choosing,
TLS model 2.2.3] from the processing unit model, obtain attribute information, the configuration detecting information that powers on of corresponding processing unit,
2.2.4] from AC level model, obtain managed zero to a plurality of IA level model informations, zero attribute information to a plurality of TLS model informations, at least one AC level logic configuration model information, fault filtering information, fault filtering device information and AC level model,
2.2.5] from IA level model, obtain the attribute information of TLS model information, at least one IA logic configuration information, fault filtering information, fault filtering device information and the IA level model chosen,
2.2.6] from the TLS model, obtain the attribute information of application partition model information, TLS logic configuration information, at least one schedule information, fault filtering information, fault filtering device information, the TLS channel information that is used to communicate by letter and transmission link information, health monitoring model information and TLS model
2.2.7] obtain the mapping relations information of software in the mapping relations model from software to hardware to hardware;
2.2.8] obtain attribute information, interface message, barrier filtering information, fault filtering device information, action message and the action ID aggregate information of each unit of corresponding avionics system in each model from the avionics system model of being set up:
2.3] according to the logical organization of distributed software model; Generate the data that the system management in the blueprint file is used, the data that said system management is used comprise the initial communication configuration data of GSM zone configuration data, TLS initial logic configuration data, aircraft-level initial logic configuration data, AC level module and each module;
2.4] with step 2.2] and in the user that obtains dispose blueprint data and step 2.3] in the system management that obtains use data combination, form complete blueprint data, store in the xml file with set form;
2.5] according to the requirement of target machine program with step 2.4] in the complete blueprint data that forms generate the scale-of-two blueprint file that can load from the xml form;
3] user loads the blueprint file to target machine.
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| CN103995913A (en) * | 2014-03-18 | 2014-08-20 | 中国电子科技集团公司第十研究所 | Open hierarchical design method for complex electronic system |
| CN106452918A (en) * | 2016-11-23 | 2017-02-22 | 北京润科通用技术有限公司 | Communication method and system for avionics network system |
| CN106713010A (en) * | 2016-11-23 | 2017-05-24 | 北京润科通用技术有限公司 | Communication method and system for avionics network system |
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| CN110737441B (en) * | 2019-09-03 | 2023-08-01 | 中国航空无线电电子研究所 | IMA configuration generation method based on micro-service architecture |
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| CN112699028A (en) * | 2020-12-29 | 2021-04-23 | 彩虹无人机科技有限公司 | Avionics fault excitation test method for integrated module of unmanned aerial vehicle |
| CN112699031A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Test method of partitioned software architecture |
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