CN106342316B - Aeronautical satellite platform high-fidelity satellite simulation general framework system - Google Patents
Aeronautical satellite platform high-fidelity satellite simulation general framework systemInfo
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- CN106342316B CN106342316B CN201110012031.5A CN201110012031A CN106342316B CN 106342316 B CN106342316 B CN 106342316B CN 201110012031 A CN201110012031 A CN 201110012031A CN 106342316 B CN106342316 B CN 106342316B
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Abstract
The invention discloses a kind of aeronautical satellite platform high-fidelity satellite simulation general framework, comprise Main Processor Unit and be hung on dynamic base and the database of Main Processor Unit outward; Main Processor Unit comprises telemetry parameter processing module, telecommand criterion processing module, telemetry-acquisition module and dynamic base interface management module; Wherein dynamic base interface management module is connected respectively with telemetry parameter processing module, telecommand criterion processing module, telemetry-acquisition module, and telemetry parameter processing module is connected with telemetry-acquisition module; Dynamic base is connected with dynamic base interface management module with database; Wherein one group of dynamic base corresponding to each satellite code name, a subsystem of the corresponding satellite of each dynamic base, for the function of emulation subsystem; Use the present invention to build general-purpose platform for high-fidelity satellite simulation, improved the efficiency of Development of Simulation Software.
Description
Technical field
The present invention relates to satellite simulation technical field, relate in particular to a kind of aeronautical satellite platform high-fidelity satellite imitativeTrue general framework system.
Background technology
Satellite plays an important role in economy and national defence, and carrying out of satellite research work needs system emulationThe support of technology. Emulation technology at the development and design of satellite, in orbit, integrated management and practical application etc.Each stage is essential, it with lower cost to satellite system carry out comprehensive network analysis, scheme is establishedMeter and performance evaluation. Increasingly extensive along with satellite simulation technology application, the need of high-fidelity satellite simulation softwareAsk also and day by day increase. Along with the increasing of number of satellite and the cycle of exploitation shorten, high-fidelity satellite simulation softwareIn order to coordinate the progress of whole project, also quick, efficient, stable developing.
Because high-fidelity satellite simulation software is wanted a series of satellite of emulation, and emulation between satellite hasOtherness. So the design of high-fidelity satellite simulation software should be flexible as far as possible, general, to meet one beThe difference demand of row satellite. Therefore, develop a kind of general high-fidelity Satellite Software emulation platform and become solutionHigh-fidelity satellite simulation software is quick, efficient, the approach of stable research and development.
Summary of the invention
The invention provides a kind of aeronautical satellite platform high-fidelity satellite simulation general framework system, solved orderThe differentiation problem of front high-fidelity satellite simulation software Satellite model, realizes high-fidelity satellite simulation softwareModularization, generalization are general platform of the rapidly and efficiently stable exploitation decorum of high-fidelity simulation software.
The object of the invention is to be achieved through the following technical solutions:
This system comprises Main Processor Unit and is hung on dynamic base and the database of Main Processor Unit outward; Main processing is singleUnit comprises that telemetry parameter processing module, telecommand criterion processing module, telemetry-acquisition module and dynamic base connectMouth administration module; Wherein dynamic base interface management module and telemetry parameter processing module, telecommand criterion placeReason module, telemetry-acquisition module are connected respectively, and telemetry parameter processing module is connected with telemetry-acquisition module; MovingState storehouse is connected with dynamic base interface management module with database;
In database, store the needed table of dynamic base simulation of loading file and Main Processor Unit; Wherein movingState storehouse simulation of loading file comprises the dynamic base that satellite code name, simulation model and simulation model are corresponding; Main processingThe needed table in unit comprises telemetry-acquisition table, telecommand criterion table, telemetry parameter processing coefficient table, distantSurvey parameter list; Acquisition method and the radio frequency channel position of telemetry parameter in telemetry-acquisition table, are recorded, telecommand standardSouvenir has carried instruction particular content, and telemetry parameter processing coefficient souvenir has carried telemetry parameter processing coefficient, distantSurvey parameter table stores the essential information of telemetry parameter, comprising: parameter code name, parameter name, remote measurement typeWith remote measurement initial value;
Wherein one group of dynamic base corresponding to each satellite code name, point of the corresponding satellite of each dynamic baseSystem, for the function of emulation subsystem;
When aeronautical satellite platform high-fidelity satellite simulation general framework system starts after normal logic operation, shouldSystem can produce the frame count of 0～15 frame;
1) dynamic base interface management module: be responsible for externally mutual; Dynamic base interface management module receive fromOutside initialization data, the needed table of Main Processor Unit simultaneously storing in loading of databases; InitializeData comprise: satellite code name and simulation model; According in the satellite code name calling data storehouse in initialization dataDynamic base simulation of loading file, loads the simulation model institute of this satellite code name according to dynamic base simulation of loading fileOne group of corresponding dynamic base;
The each dynamic base being loaded is carried out telemetry parameter according to the essential information of telemetry parameter in telemetry parameter tableInitialize, start the emulation of subsystem, the telemetry that emulation is produced is in real time by dynamic base interface managementModule is transferred to telemetry parameter processing module;
2) telemetry parameter processing module: the corresponding a kind of processing method of each class telemetry parameter, telemetry parameter processingModule is according to the processing coefficient of recording in telemetry parameter processing coefficient table and being pre-stored in telemetry parameter processing moduleThe processing method of telemetry parameter, the telemetry parameter that emulation is produced is in real time according to corresponding processing method and locateReason coefficient processing is the remote measurement source code that ground needs;
3) telemetry-acquisition module: telemetry-acquisition module has multiple telemetry mouths, each telemetry mouth basisThe remote measurement source code of the respective frame that current frame count produces telemetry parameter processing module gathers, when collectionGather telemetry parameter processing module remote measurement source code after treatment according to the acquisition method in telemetry-acquisition table, and rootAccording to the radio frequency channel position in telemetry-acquisition table, remote measurement source code is put under corresponding radio frequency channel and passed ground;
4) telecommand criterion processing module: according to the current telecommand code name receiving from ground, from remote controlIn instruction criterion table, obtain the particular content of telecommand, according to the execute flag in telecommand particular contentTelecommand is differentiated and directly carried out instruction or logic execution instruction, if directly carry out instructionDirectly carry out current telecommand, if logic is carried out instruction, according to telecommand criterion table middle fingerThe subsystem mark forwarding logic of order is carried out the dynamic base of instruction to corresponding subsystem, corresponding subsystem dynamicallyStorehouse actuating logic is carried out instruction.
The processing method of telemetry parameter processing module comprises: source code processing, voltage processing, linear process, lineThe processing of property interpolation, look-up table, Temperature Treatment, state processing, multinomial processing.
In telemetry-acquisition table, comprise telemetry parameter code name field, the affiliated subsystem field of parameter, telemetry parameterUnder frame field, telemetry parameter ripple Taoist monastic name field, gather the digital code field of this telemetry parameter.
Simulation model comprises: digital pattern, rail control semi physical pattern, number pipe semi physical pattern, rail controlNumber pipe associating semi physical pattern.
The dynamic base title that each simulation model is corresponding is as follows:
1) digital pattern: tracking-telemetry and command subsystem dynamic base, confession sub power distribution system dynamic base, thermal control subsystem moveState storehouse, Payload Subsystem dynamic base, data handling subsystem dynamic base, far put unit dynamic base;
2) rail control semi physical pattern: tracking-telemetry and command subsystem dynamic base;
3) count pipe semi physical pattern: tracking-telemetry and command subsystem dynamic base;
4) associating semi physical pattern: tracking-telemetry and command subsystem dynamic base.
Beneficial effect of the present invention:
The design of aeronautical satellite platform high-fidelity satellite simulation software generic frame system is defended in the high-fidelity of having developedIn star simulation software, obtain application, built general-purpose platform for high-fidelity satellite simulation, improved simulation softwareThe efficiency of exploitation.
Brief description of the drawings
Fig. 1 is frame system schematic diagram of the present invention;
Detailed description of the invention
In order to understand better technical scheme of the present invention, below in conjunction with drawings and the specific embodiments to the present inventionBe described in further detail.
The present invention, according to database application technology and Dynamic loading technique, has carried out high-fidelity satellite simulation softwareUnified Modeling, realized aeronautical satellite platform high-fidelity satellite simulation software generic frame system design. ThisInvention is used the public processing of the required use of each subsystem dynamic base in Main Processor Unit management simulation processMethod, and leave expansion interface. The satellite processing method of identical platform different model is consistent, thereby protectsDemonstrate,prove the stability of Main Processor Unit; Once certain model need to be added special processing method, expansion interface canTo be easy to realize this demand.
Usage data library management configuration parameter: the various configuration parameters of satellite simulation software are stored in database,If the configuration parameter of satellite needs amendment, in the situation that not changing Main Processor Unit, pass through Update TableConfiguration data in storehouse can be realized;
Use dynamic base to realize and change logic: be dynamic base by the logic realization changing possibly. If satelliteLogic to change, in the situation that not changing Main Processor Unit, by replace dynamic base can realize.
The present invention and dummy satellite are irrelevant, only need to from database table, obtain corresponding with outside man-machine interfaceInitialization information, thereby dummy satellite and software frame system are completely independent, have strengthened the steady of systemQualitative and reusability. Be specifically described below, as shown in Figure 1:
This system comprises Main Processor Unit and is hung on dynamic base and the database of Main Processor Unit outward; Main processing is singleUnit comprises that telemetry parameter processing module, telecommand criterion processing module, telemetry-acquisition module and dynamic base connectMouth administration module; Wherein dynamic base interface management module and telemetry parameter processing module, telecommand criterion placeReason module, telemetry-acquisition module are connected respectively, and telemetry parameter processing module is connected with telemetry-acquisition module; MovingState storehouse is connected with dynamic base interface management module with database;
In database, store the needed table of dynamic base simulation of loading file and Main Processor Unit; Wherein movingState storehouse simulation of loading file comprises the dynamic base that satellite code name, simulation model and simulation model are corresponding; Main processingThe needed table in unit comprises telemetry-acquisition table, telecommand criterion table, telemetry parameter processing coefficient table, distantSurvey parameter list; Acquisition method and the radio frequency channel position of telemetry parameter in telemetry-acquisition table, are recorded, telecommand standardSouvenir has carried instruction particular content, and telemetry parameter processing coefficient souvenir has carried telemetry parameter processing coefficient, distantSurvey parameter table stores the essential information of telemetry parameter, comprising: parameter code name, parameter name, remote measurement typeWith remote measurement initial value;
Wherein one group of dynamic base corresponding to each satellite code name, point of the corresponding satellite of each dynamic baseSystem, for the function of emulation subsystem;
Simulation model comprises: digital pattern, rail control semi physical pattern, number pipe semi physical pattern, rail controlNumber pipe associating semi physical pattern.
The dynamic base title that each simulation model is corresponding is as follows:
1) digital pattern: tracking-telemetry and command subsystem dynamic base, confession sub power distribution system dynamic base, thermal control subsystem moveState storehouse, Payload Subsystem dynamic base, data handling subsystem dynamic base, far put unit dynamic base;
2) rail control semi physical pattern: tracking-telemetry and command subsystem dynamic base;
3) count pipe semi physical pattern: tracking-telemetry and command subsystem dynamic base;
4) associating semi physical pattern: tracking-telemetry and command subsystem dynamic base.
When aeronautical satellite platform high-fidelity satellite simulation general framework system starts after normal logic operation, shouldSystem can produce the frame count of 0～15 frame;
1) dynamic base interface management module: be responsible for externally mutual; Dynamic base interface management module receive fromOutside initialization data, initialization data comprises: satellite code name and simulation model; According in initialization dataSatellite code name calling data storehouse in dynamic base simulation of loading file, add according to dynamic base simulation of loading fileCarry the corresponding one group of dynamic base of simulation model of this satellite code name, the main place simultaneously storing in loading of databasesThe needed table in reason unit;
The each dynamic base being loaded is carried out telemetry parameter according to the essential information of telemetry parameter in telemetry parameter tableInitialize, start the emulation of subsystem, the telemetry that emulation is produced is in real time by dynamic base interface managementModule is transferred to telemetry parameter processing module;
2) telemetry parameter processing module: the corresponding a kind of processing method of each class telemetry parameter, telemetry parameter processingModule is according to the processing coefficient of recording in telemetry parameter processing coefficient table and being pre-stored in telemetry parameter processing moduleThe processing method of telemetry parameter, the telemetry parameter that emulation is produced is in real time according to corresponding processing method and locateReason coefficient processing is the remote measurement source code that ground needs; Main methods: source code processing, voltage processing, lineProperty processing, linear interpolation processing, look-up table, Temperature Treatment, state processing, multinomial processing, depend onThe processing method of other parameter.
3) telemetry-acquisition module: telemetry-acquisition module has multiple telemetry mouths, each telemetry mouth basisThe remote measurement source code of the respective frame that current frame count produces telemetry parameter processing module gathers, when collectionGather telemetry parameter processing module remote measurement source code after treatment according to the acquisition method in telemetry-acquisition table, and rootAccording to the radio frequency channel position in telemetry-acquisition table, remote measurement source code is put under corresponding radio frequency channel and passed ground;
4) telecommand criterion processing module: according to the current telecommand code name receiving from ground, from remote controlIn instruction criterion table, obtain the particular content of telecommand, according to the execute flag in telecommand particular contentTelecommand is differentiated and directly carried out instruction or logic and carry out instruction (execute flag is 1 to be directCarry out instruction, it is that logic is carried out instruction that execute flag is 0), directly carry out if directly carry out instructionCurrent telecommand, if logic is carried out instruction, according to the subsystem of instruction in telecommand criterion tableMark forwarding logic is carried out the dynamic base of instruction to corresponding subsystem, the dynamic base actuating logic of corresponding subsystemCarry out instruction and by feedback result remote measurement to ground.
The invention enables the high-fidelity emulation of dissimilar satellite can realize at Data processing unified; For notWith the model data of satellite, only need to be according to the model file of the design of database table and this satellite by its typingDatabase, can contain total data information.
In sum, these are only preferred embodiment of the present invention, be not intended to limit guarantor of the present inventionProtect scope. Within the spirit and principles in the present invention all, any amendment of doing, be equal to replacement, improvement etc.,Within all should being included in protection scope of the present invention.
Claims (5)
1. an aeronautical satellite platform high-fidelity satellite simulation general framework system, is characterized in that: comprise masterProcessing unit and be hung on dynamic base and the database of Main Processor Unit outward; Main Processor Unit comprises telemetry parameter placeReason module, telecommand criterion processing module, telemetry-acquisition module and dynamic base interface management module; WhereinDynamic base interface management module and telemetry parameter processing module, telecommand criterion processing module, telemetry-acquisitionModule is connected respectively, and telemetry parameter processing module is connected with telemetry-acquisition module; Dynamic base and database and movingState bank interface administration module is connected;
In database, store the needed table of dynamic base simulation of loading file and Main Processor Unit; Wherein movingState storehouse simulation of loading file comprises the dynamic base that satellite code name, simulation model and simulation model are corresponding; Main processingThe needed table in unit comprises telemetry-acquisition table, telecommand criterion table, telemetry parameter processing coefficient table, distantSurvey parameter list; Acquisition method and the radio frequency channel position of telemetry parameter in telemetry-acquisition table, are recorded, telecommand standardSouvenir has carried instruction particular content, and telemetry parameter processing coefficient souvenir has carried telemetry parameter processing coefficient, distantSurvey parameter table stores the essential information of telemetry parameter, comprising: parameter code name, parameter name, remote measurement typeWith remote measurement initial value;
Wherein one group of dynamic base corresponding to each satellite code name, point of the corresponding satellite of each dynamic baseSystem, for the function of emulation subsystem;
When aeronautical satellite platform high-fidelity satellite simulation general framework system starts after normal logic operation, shouldSystem can produce the frame count of 0～15 frame;
1) dynamic base interface management module: be responsible for externally mutual; Dynamic base interface management module receive fromOutside initialization data, the needed table of Main Processor Unit simultaneously storing in loading of databases; InitializeData comprise: satellite code name and simulation model; According in the satellite code name calling data storehouse in initialization dataDynamic base simulation of loading file, loads the simulation model institute of this satellite code name according to dynamic base simulation of loading fileOne group of corresponding dynamic base;
The each dynamic base being loaded is carried out telemetry parameter according to the essential information of telemetry parameter in telemetry parameter tableInitialize, start the emulation of subsystem, the telemetry that emulation is produced is in real time by dynamic base interface managementModule is transferred to telemetry parameter processing module;
2) telemetry parameter processing module: the corresponding a kind of processing method of each class telemetry parameter, telemetry parameter processingModule is according to the processing coefficient of recording in telemetry parameter processing coefficient table and being pre-stored in telemetry parameter processing moduleThe processing method of telemetry parameter, the telemetry parameter that emulation is produced is in real time according to corresponding processing method and locateReason coefficient processing is the remote measurement source code that ground needs;
3) telemetry-acquisition module: telemetry-acquisition module has multiple telemetry mouths, each telemetry mouth basisThe remote measurement source code of the respective frame that current frame count produces telemetry parameter processing module gathers, when collectionGather telemetry parameter processing module remote measurement source code after treatment according to the acquisition method in telemetry-acquisition table, and rootAccording to the radio frequency channel position in telemetry-acquisition table, remote measurement source code is put under corresponding radio frequency channel and passed ground;
4) telecommand criterion processing module: according to the current telecommand code name receiving from ground, from remote controlIn instruction criterion table, obtain the particular content of telecommand, according to the execute flag in telecommand particular contentTelecommand is differentiated and directly carried out instruction or logic execution instruction, if directly carry out instructionDirectly carry out current telecommand, if logic is carried out instruction, according to telecommand criterion table middle fingerThe subsystem mark forwarding logic of order is carried out the dynamic base of instruction to corresponding subsystem, corresponding subsystem dynamicallyStorehouse actuating logic is carried out instruction.
2. a kind of aeronautical satellite platform high-fidelity satellite simulation general framework system as claimed in claim 1,It is characterized in that, the processing method of telemetry parameter processing module comprises: source code processing, voltage processing, linearityProcessing, linear interpolation processing, look-up table, Temperature Treatment, state processing, multinomial processing.
3. a kind of aeronautical satellite platform high-fidelity satellite simulation general framework system as claimed in claim 1,It is characterized in that, in telemetry parameter acquisition tables, comprise telemetry parameter code name field, the affiliated subsystem word of parameterSection, frame field, telemetry parameter ripple Taoist monastic name field under telemetry parameter, gather the digital code of this telemetry parameterField.
4. a kind of aeronautical satellite platform high-fidelity satellite simulation general framework system as claimed in claim 1,It is characterized in that, simulation model comprises: digital pattern, rail control semi physical pattern, number pipe semi physical pattern,Rail control is counted pipe associating semi physical pattern.
5. a kind of aeronautical satellite platform high-fidelity satellite simulation general framework system as claimed in claim 4,The dynamic base title that each simulation model is corresponding is as follows:
1) digital pattern: tracking-telemetry and command subsystem dynamic base, dynamic for sub power distribution system dynamic base, thermal control subsystemStorehouse, Payload Subsystem dynamic base, data handling subsystem dynamic base, far put unit dynamic base;
2) rail control semi physical pattern: tracking-telemetry and command subsystem dynamic base;
3) count pipe semi physical pattern: tracking-telemetry and command subsystem dynamic base;
4) associating semi physical pattern: tracking-telemetry and command subsystem dynamic base.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107273115A (en) * | 2017-05-17 | 2017-10-20 | 哈尔滨工业大学 | Satellite rapid build system and method based on standardized module |
| CN107942722A (en) * | 2017-11-06 | 2018-04-20 | 航天东方红卫星有限公司 | A kind of moonlet Surface power drive emulation test method and system |
| CN110113093A (en) * | 2019-04-18 | 2019-08-09 | 中国科学院国家空间科学中心 | A kind of modularization payload floor synthetic test macro |
| CN110865556A (en) * | 2019-12-03 | 2020-03-06 | 中国科学院软件研究所 | Virtual satellite, and test platform and method for software and algorithm based on virtual satellite |
| CN112577535A (en) * | 2019-09-27 | 2021-03-30 | 陕西星邑空间技术有限公司 | Data processing method, device and system |
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2011
- 2011-07-29 CN CN201110012031.5A patent/CN106342316B/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107273115A (en) * | 2017-05-17 | 2017-10-20 | 哈尔滨工业大学 | Satellite rapid build system and method based on standardized module |
| CN107942722A (en) * | 2017-11-06 | 2018-04-20 | 航天东方红卫星有限公司 | A kind of moonlet Surface power drive emulation test method and system |
| CN110113093A (en) * | 2019-04-18 | 2019-08-09 | 中国科学院国家空间科学中心 | A kind of modularization payload floor synthetic test macro |
| CN110113093B (en) * | 2019-04-18 | 2021-06-08 | 中国科学院国家空间科学中心 | Ground comprehensive test system for modularized effective load |
| CN112577535A (en) * | 2019-09-27 | 2021-03-30 | 陕西星邑空间技术有限公司 | Data processing method, device and system |
| CN110865556A (en) * | 2019-12-03 | 2020-03-06 | 中国科学院软件研究所 | Virtual satellite, and test platform and method for software and algorithm based on virtual satellite |
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