CN102750301B - 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 blue drawing generating method of the integrated avionics model of describing for AADL.
Background technology
In synthesization, modularization avionics system, the operation that general-purpose system management software is responsible for whole integrated avionics, realizes control and the management of resource, workflow, pattern control, fault recovery and information security by user configured blueprint file.According to the feature of synthesization, modularization avionics system, use AADL to set up avionics system model, carry out the design of authentication of users by various analysis tools, be the current study hotspot in avionics system modeling direction.In the time of user's avionics system that finally operation comprehensively completes in real environment, blueprint file while also needing to move.Conventionally user can be by the blueprint file at xml editing machine inediting xml form, then the blueprint file of xml form is converted to the scale-of-two blueprint file that can load and obtains blueprint file while operation.But in the time using AADL to set up avionics system model, data in blueprint file have been reflected to model and have suffered, manually write blueprint file for fear of user, the present invention proposes a kind of blueprint information of extracting from avionics system model, generation can load the method for scale-of-two blueprint file automatically.The method has improved integrated avionics development efficiency, saves 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 of taking a lot of work, easily makeing mistakes, the invention provides a kind of blue drawing generating method of the integrated avionics model of describing for AADL, the present invention is directed to the avionics system model that AADL sets up, blueprint when automatic generating run.
The technical solution that the present invention has:
A kind of blue drawing generating method of the integrated avionics model of describing for AADL: its special character is: comprise the following steps:
1] modeling: user is the bottom-up avionics system model of setting up in AADL modeling environment:
1.1] to hardware configuration modeling:
1.1.1] set up corresponding processing unit model for all processing units in avionics system,
Described processing unit model comprises that the attribute information of alignment processing unit describes and the configuration test model that powers on; The attribute information of described processing unit is described and is comprised physical I D;
1.1.2] set up functional block model for all general utility functions modules (CFM) in avionics system, in described functional block model, comprise from step 1.1.1] the communication interface model that attribute information is described and general utility functions module comprises of processing unit model, the corresponding general utility functions module chosen in the processing unit model set up, the attribute information of described general utility functions module comprises general utility functions module type and slot number; The described processing unit model of choosing is at least one, described in the physical I D of processing unit model that chooses and the slot of general utility functions module number corresponding;
1.1.3] set up distributed hardware model for hardware platform in avionics system, described 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, described distributed hardware model is chosen corresponding functional block model according to function;
1.2] to software configuration modeling:
1.2.1] set up application partition model for the application partition operating on processing unit,
The attribute information that comprises multiple process models, port model, health monitoring model and corresponding application partition for communicating by letter in the model of described application partition is described, and the attribute information of described corresponding application partition is described and comprised the zone name of application partition, memory size and the application partition type that application partition takies;
Described process model comprises the attribute information description of process model, and the attribute information of described process model comprises process name, base priority, cycle and off period,
Described port model comprises the attribute information description of port model, and the attribute information of described port model comprises port type and transmission mode;
Described health monitoring model comprises the attribute information description of health monitoring model, and the attribute information of described health monitoring model comprises type of error, running status and processes address;
1.2.2] set up corresponding TLS model for the RE level of avionics system, in described TLS model, comprise at least one application partition model, at least one TLS logic allocation models, at least one dispatch list model, fault filtering model, fault filtering device model, describe for the TLS channel pattern of communicating by letter and the attribute information that transmits link model, health monitoring model and TLS model
The application partition model that TLS model comprises be TLS model according to function from step 1.2.1] choose corresponding a kind of operational mode configuration of TLS logic allocation models the application partition model set up;
1.2.3] set up all IA level models for the IA level of avionics system, described IA level model comprises that at least one is from step 1.2.2] attribute information of TLS model, at least one IA logic allocation models, fault filtering model, fault filtering device model and the IA level model chosen according to function is described the TLS model set up, a corresponding a kind of operational mode configuration of IA logic allocation models;
1.2.4] set up AC level model for the AC level of avionics system, described AC level model comprise managed zero to multiple IA level models, zero to multiple TLS models, at least one AC level logic allocation models,, the attribute information of fault filtering model, fault filtering device model and AC level model describes, the attribute information of described AC level model comprise AC level model TLS model identification;
1.2.5] set up AC level action model, IA level action model and RE level action model,
1.2.6] for AC level model is chosen AC level action ID set from AC level action model according to function, for IA level model is chosen IA level action ID set from IA level action model according to function, for TLS model is chosen RE level action ID set from RE level action model according to function
1.2.7] set up distributed software model, described 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: described Distributed System Model comprises distributed software model, distributed hardware model and the software mapping relations model to hardware;
2] according to avionics system auto-building model blueprint:
2.1] legitimacy of inspection avionics system model:
2.1.1] integrality of inspection avionics system model structure (checking the configuration information that whether lacks certain part in blueprint), 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; In the model of application partition, whether there is health monitoring model, process model; Whether there is AC level action model, IA level action model and RE level action model and the software mapping relations model to hardware;
2.1.2] attribute information of inspection avionics system model;
2.2] while extracting operation from avionics system model, user configures blueprint data:
2.2.1] from distributed hardware model, obtain the functional block model information of choosing,
TLS model 2.2.3] from processing unit model, obtain attribute information, the configuration detecting information that powers on of alignment processing unit,
2.2.4] from AC level model, obtain managed zero to multiple IA level model informations, zero attribute information to multiple TLS model informations, at least one AC level logic allocation models 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 TLS model, obtain application partition model information, TLS logic configuration information, at least one schedule information, fault filtering information, fault filtering device information, for the TLS channel information of communicating by letter and the attribute information of transmission link information, health monitoring model information and TLS model
2.2.7] in the mapping relations model from software to hardware, obtain the mapping relations information of software to hardware;
2.2.8] in each model from set up avionics system model, obtain attribute information, interface message, barrier filtering information, fault filtering device information, action message and the action ID aggregate information of corresponding avionics system unit:
2.3] according to the logical organization of distributed software model, generate the data that the system management in blueprint file is used, the data that described 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 modules;
2.4] by step 2.2] in the user that obtains configure blueprint data and step 2.3] in the system management usage data combination that obtains, form complete blueprint data, store in xml file with set form;
2.5] according to the requirement of target machine program by step 2.4] in form complete blueprint data generate the scale-of-two blueprint file that can load from xml form;
3] user loads blueprint file to target machine.
Technical solution of the present invention:
1, the present invention, by setting up avionics system auto-building model blueprint, has avoided user manually to write blueprint file, while having solved existing user manual editing blueprint Document Charge, the defect of taking a lot of work, easily makeing mistakes, improves blueprint formation efficiency.
2, the present invention, by the validity checking to avionics system model, has improved the reliability of data.
3, the present invention proposes a kind of blueprint information of extracting from avionics system model, generation can load the method for scale-of-two blueprint file automatically.The method has improved integrated avionics development efficiency, saves development and maintenance cost, and the credibility that improves software systems is had great importance.
4, the present invention is by carrying out validity checking to avionics system model, according to the Liquified gas tanker of synthesization, modularization avionics system, the model that user is set up carries out validity checking, improve the accuracy of modeling, main inspection two aspects, the inspection to model structure and the inspection to the property value in model.Model structure is checked to object is the integrality of inspection model, check the configuration information that whether lacks certain part in blueprint.The inspection of the property value in model is guaranteed to validity and the legitimacy of data.
Brief description of the 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 blueprint data file layout.
Embodiment
As shown in Figure 1, the three-decker of general-purpose system management software as shown in Figure 2 for relation in synthesization, modularization avionics system between two general utility functions modules (CFM).The management of AC level system is responsible for controlling and monitoring whole synthesization, modularization avionics system IMA (Integrated Module Avionics).The management of IA level system is responsible for controlling a certain sub-function module, 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.
Generating before blueprint file, user need to be in AADL modeling environment the bottom-up model of setting up avionics system.Carry out modeling according to the soft and hardware structure substep of the avionics system that will realize.
Step 1, to the modeling procedure of hardware configuration be:
1. set up all processing unit models, each processing unit comprises a CPU, and the processing unit attribute informations such as the cpu type of set handling unit, physical I D, memory size are described, the configuration test model that powers on;
2. set up all functional block models, in each modular model, comprise multiple processing unit models, in the processing unit model that these processing unit models are set up from the 1st step, choose, 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 multiple modular models in hardware platform, in the model that these modular models are set up from the 2nd step, choose, according to concrete communicating requirement, the communication interface of link block is to realize these communicating requirements.
Step 2, to the modeling procedure of software configuration be:
1. set up all application partition models, the port, the health monitoring information of use that in each application partition, comprise multiple process models, communicate by letter with other subregion and use, the zone name of each subregion, the attribute information such as memory size, divisional type taking are set, the attribute informations such as the process name, base priority, process cycle, off period of the process that each subregion comprises are set, the attribute information such as port type, transmission mode that each subregion comprises port;
2. set up all TLS models, in each TLS, comprise multiple application partition model, multiple TLS logic allocation models, multiple dispatch list model, communicate by letter and use that passage and transmission are connected, health monitoring allocation models with other TLS, the model that the application partition model comprising in TLS is set up from the first step, choose, every kind of corresponding a kind of operational mode of TLS logic allocation models configures, and the attribute information of TLS model is set;
3. set up all IA level models, comprise multiple three layers of stack (TLS) model in each IA, IA logic allocation models, chooses in the model that TLS model is set up from second step, and the attribute information of IA model is set;
4. set up AC level model, AC model is also as the software model of distributed system, it comprises managed IA model, TLS model, zero fault filtering table information, fault filtering device configuration information to multiple TLS logic allocation modelss, 0 set of the action lists ID to multiple IA logic allocation modelss, use, use, IA model, TLS model are 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;
After software model and hardware model have been set up, need to carry out modeling to the mapping relations of hardware to software, then set up Distributed System Model.The model that Distributed System Model comprises is the mapping relations model of distributed software model, distributed hardware model and software and hardware.
The avionics system model establishing leaves in a work space with document form, and these files can be organized in multiple engineerings.
Step 3, according to the step of avionics system auto-building model blueprint file be:
1. pair avionics system model carries out validity checking;
2. the data that while extracting operation the avionics system model of setting up from user, blueprint needs;
3. according to the logical organization of software systems model, the partial data in the relevant blueprint file of automatic creation system;
4. by the data in model with the complete blueprint data of data formation automatically generating, and generate the blueprint file of xml form;
5. the scale-of-two blueprint file that during according to operation, blueprint data call format can load from the blueprint file generated of xml form.
Step 1 completes the validity checking to avionics system model, mainly comprises two aspects, the inspection to model structure and the inspection to the property value in model.Model structure is checked to object is the integrality of inspection model, checks and comprise the configuration information that whether lacks certain part in blueprint:
---whether AC, IA and TLS level there is action lists ID set configuration, fault filtering table and filter deployment;
---in the configuration of application partition, whether there is subregion health monitoring, process configuration;
---whether exist action lists and logic to configure to physical mappings.
Inspection to the property value in model comprises:
---all length of name can not exceed 30 bytes;
---all paths can not exceed 64 bytes;
---all time wants the time value after check the value and unit coupling can not exceed long shaping scope;
---duplication of name, double sign inspection.
The main completion system mode input data of step 2 are extracted, and the main models relating 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 distributed hardware system model comprises:
---each hardware module information: the interface of module type, the processing unit comprising, use;
---each processing unit information: the test chart that powers on of the name of processing unit, numbering, use.
The information of obtaining from 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, subregion, port configuration information.
Step 3 mainly completes that automatic generation 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 configure with the initial logic of modules.Automatically the GSM zone configuration generating comprises:
---zone attribute;
---all processes that comprise in subregion;
---all of the port comprising in subregion.
Each TLS initial logic configuration:
---network configuration;
---communicating by letter with GSM subregion, passage, the transmission 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 modules:
---the identification information of transmitting terminal and receiving end;
---transmitting terminal communicate by letter with receiving end use transmission, receive transmission hyphen;
---transmitting terminal and receiving end communicate by letter the transmission that uses, receive transmission and be connected configuration.
Step 4 completes the data of extracting in model and the data that automatically generate are combined to form complete blueprint data, and asks user to input path and the filename of preserving file, and these data are stored in xml file with set form.User can directly use xml edit tool to open this file, browses and revise this file.Blueprint file data structure as shown in Figure 4,5, 6.
Step 5 completes the scale-of-two blueprint file function that can load from the blueprint file generated of xml form, the blueprint file of xml form is the file that people is more easy to identify and operate, binary file is the file of machine recognition, the blueprint file that this step reads xml form is set form according to the requirement of target machine program by Organization of Data, the binary data file of final formation, document format data as shown in Figure 7.
Avionics system model is carried out to validity checking, according to the Liquified gas tanker of synthesization, modularization avionics system, the model that user is set up carries out validity checking, improves the accuracy of modeling, main inspection two aspects, the inspection to model structure and the inspection to the property value in model.Model structure is checked to object is the integrality of inspection model, check the configuration information that whether lacks certain part in blueprint.The inspection of the property value in model is guaranteed to validity and the legitimacy of data.
The data that while extracting operation, blueprint needs, main completion system mode input data are extracted, and the main models relating 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 distributed hardware system model comprises each hardware module relevant information, each processing unit relevant information.The information of obtaining from distributed software system model comprises aircraft-level, complex zone level, TLS, subregion relevant information.
The data that automatic creation system is relevant, complete automatic generation user 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 modules.GSM zone configuration information has all of the port comprising in all processes of comprising in zone attribute, subregion, subregion.Passage, TC, interface configuration, dispatch list that each TLS initial logic configuration information has network configuration, communicates by letter use with GSM subregion.
Form complete blueprint data, complete the data of the data of extracting in model and generation are automatically combined to form to complete blueprint data, and ask user to input path and the filename of preserving file, these data are stored in xml file with set form.User can directly use xml edit tool to open this file, browses and revise this file.
The scale-of-two blueprint file that generation can load completes the scale-of-two blueprint file function that can load from the blueprint file generated of xml form, the blueprint file of xml form is the file that people is more easy to identify and operate, binary file is the file of machine recognition, the blueprint file that this step reads xml form is set form according to the requirement of target machine program by Organization of Data, finally forms binary data file.
Embodiment:
Taking a synthesization, modularization avionics system as example, in this system, there are 4 general modules, on every plank, there are two CPU, software is three-decker, aircraft-level software resides on 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 corresponding property value is set for each model.User carries out after the analysis and design of model under structural modeling platform, while operation, need to use the blueprint file of xml editing machine editor xml form in real environment, and the blueprint file of XML form is converted to the binary data file that can load.Manually write blueprint file for fear of user, use now the blueprint information of extracting from avionics system model, generation can load the method for scale-of-two blueprint file automatically,
The method job step is:
1. pair avionics system model carries out validity checking, and errors present, prompting are presented in miscue view, and user, according to bug patch model, reexamines model, until model is completely legal;
2. obtain the data in model: obtain hardware configuration information, attribute information, obtain software configuration information, AC level information, IA level information, TLS level information, obtain 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 modules automatically;
4. the data of obtaining according to step 2 and step 3, form complete blueprint data according to blueprint form, and prompting user provides the storing path and the filename that generate blueprint file, preserve the blueprint file of the xml form generating under this path;
5. according to the requirement of scale-of-two blueprint file data, the blueprint file of xml form is converted to binary file.
Carry out blueprint generation by the method, can automatically generate the data message relevant to GSM, alleviate avionics system modeling personnel's burden, the legitimacy of data in inspection model, the correctness of raising data;
Avionics system model taking the foundation of AADL modeling tool is the blueprint file that basis generates xml form, facilitates user to browse, again revise, merge with the data of other instrument generation; The loaded blueprint data file generating, can directly be loaded on target machine, facilitates user in true environment, to move debug system.
Claims (1)
1. the blue drawing generating method of an integrated avionics model of describing for AADL: it is characterized in that: comprise the following steps:
1] modeling: user is the bottom-up avionics system model of setting up in AADL modeling environment:
1.1] to hardware configuration modeling:
1.1.1] set up corresponding processing unit model for all processing units in avionics system,
Described processing unit model comprises that the attribute information of alignment processing unit describes and the configuration test model that powers on; The attribute information of described processing unit is described and is comprised physical I D;
1.1.2] set up functional block model for all general utility functions modules (CFM) in avionics system, in described functional block model, comprise from step 1.1.1] the communication interface model that attribute information is described and general utility functions module comprises of processing unit model, the corresponding general utility functions module chosen in the processing unit model set up, the attribute information of described general utility functions module comprises general utility functions module type and slot number; The described processing unit model of choosing is at least one, described in the physical I D of processing unit model that chooses and the slot of general utility functions module number corresponding;
1.1.3] set up distributed hardware model for hardware platform in avionics system, described 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, described distributed hardware model is chosen corresponding functional block model according to function;
1.2] to software configuration modeling:
1.2.1] set up application partition model for the application partition operating on processing unit,
The attribute information that comprises multiple process models, port model, health monitoring model and corresponding application partition for communicating by letter in the model of described application partition is described, and the attribute information of described corresponding application partition is described and comprised the zone name of application partition, memory size and the application partition type that application partition takies;
Described process model comprises the attribute information description of process model, and the attribute information of described process model comprises process name, base priority, cycle and off period,
Described port model comprises the attribute information description of port model, and the attribute information of described port model comprises port type and transmission mode;
Described health monitoring model comprises the attribute information description of health monitoring model, and the attribute information of described health monitoring model comprises type of error, running status and processes address;
1.2.2] set up corresponding TLS model for the RE level of avionics system, in described TLS model, comprise at least one application partition model, at least one TLS logic allocation models, at least one dispatch list model, fault filtering model, fault filtering device model, describe for the TLS channel pattern of communicating by letter and the attribute information that transmits link model, health monitoring model and TLS model
The application partition model that TLS model comprises be TLS model according to function from step 1.2.1] choose corresponding a kind of operational mode configuration of TLS logic allocation models the application partition model set up;
1.2.3] set up all IA level models for the IA level of avionics system, described IA level model comprises that at least one is from step 1.2.2] attribute information of TLS model, at least one IA logic allocation models, fault filtering model, fault filtering device model and the IA level model chosen according to function is described the TLS model set up, a corresponding a kind of operational mode configuration of IA logic allocation models;
1.2.4] set up AC level model for the AC level of avionics system, described AC level model comprises that managed zero describes to multiple IA level models, zero attribute information to multiple TLS models, at least one AC level logic allocation models, fault filtering model, fault filtering device model and AC level model, the attribute information of described AC level model comprise AC level model TLS model identification;
1.2.5] set up AC level action model, IA level action model and RE level action model;
1.2.6] for AC level model is chosen AC level action ID set from AC level action model according to function, for IA level model is chosen IA level action ID set from IA level action model according to function, for TLS model is chosen RE level action ID set from RE level action model according to function;
1.2.7] set up distributed software model, described 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: described Distributed System Model comprises distributed software model, distributed hardware model and the software mapping relations model to hardware;
2] according to avionics system auto-building model blueprint:
2.1] legitimacy of inspection avionics system model:
2.1.1] integrality of inspection avionics system model structure, check the configuration information that whether lacks certain part in blueprint, 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; In the model of application partition, whether there is health monitoring model, process model; Whether there is AC level action model, IA level action model and RE level action model and the software mapping relations model to hardware;
2.1.2] attribute information of inspection avionics system model;
2.2] while extracting operation from avionics system model, user configures blueprint data:
2.2.1] from distributed hardware model, obtain the functional block model information of choosing;
2.2.2] from processing unit model, obtain attribute information, the configuration detecting information that powers on of alignment processing unit;
2.2.3] from AC level model, obtain managed zero to multiple IA level model informations, zero attribute information to multiple TLS model informations, at least one AC level logic allocation models information, fault filtering information, fault filtering device information and AC level model;
2.2.4] 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;
2.2.5] from TLS model, obtain application partition model information, TLS logic configuration information, at least one schedule information, fault filtering information, fault filtering device information, for the TLS channel information of communicating by letter and the attribute information of transmission link information, health monitoring model information and TLS model;
2.2.6] in the mapping relations model from software to hardware, obtain the mapping relations information of software to hardware;
2.2.7] in each model from set up avionics system model, obtain attribute information, interface message, barrier filtering information, fault filtering device information, action message and the action ID aggregate information of corresponding avionics system unit;
2.3] according to the logical organization of distributed software model, generate the data that the system management in blueprint file is used, the data that described 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 modules;
2.4] by step 2.2] in the user that obtains configure blueprint data and step 2.3] in the system management usage data combination that obtains, form complete blueprint data, store in xml file with set form;
2.5] according to the requirement of target machine program by step 2.4] in form complete blueprint data generate the scale-of-two blueprint file that can load from xml form;
3] user loads blueprint file to target machine.
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| CN103123660B (en) * | 2012-12-31 | 2016-03-23 | 清华大学 | A kind of method to software and hardware system CAD mathematics library |
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| CN102073585B (en) * | 2010-11-25 | 2013-08-14 | 西北工业大学 | Method for testing delay attribute of embedded system stream based on model |
| CN102231132B (en) * | 2011-06-30 | 2013-12-25 | 西北工业大学 | Method for generating simulation test example of AADL (Architecture Analysis and Design Language) software component model based on SystemC |
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