CN109614285B - Configuration management method for integrated modular avionics system - Google Patents
Configuration management method for integrated modular avionics system Download PDFInfo
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- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/30—Monitoring
- G06F11/3051—Monitoring arrangements for monitoring the configuration of the computing system or of the computing system component, e.g. monitoring the presence of processing resources, peripherals, I/O links, software programs
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/30—Monitoring
- G06F11/3003—Monitoring arrangements specially adapted to the computing system or computing system component being monitored
- G06F11/3013—Monitoring arrangements specially adapted to the computing system or computing system component being monitored where the computing system is an embedded system, i.e. a combination of hardware and software dedicated to perform a certain function in mobile devices, printers, automotive or aircraft systems
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/30—Monitoring
- G06F11/3055—Monitoring arrangements for monitoring the status of the computing system or of the computing system component, e.g. monitoring if the computing system is on, off, available, not available
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- G06F11/32—Monitoring with visual or acoustical indication of the functioning of the machine
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Abstract
The invention discloses a configuration management method for an integrated modular avionics system, which comprises a module-level configuration list management method, wherein the configuration list management method comprises the following steps: (A.1) each hardware module of the comprehensive modularized avionics system obtains a configuration list of the hardware module from Flash in a starting stage, reports the configuration list to a configuration management platform, and waits for the configuration management platform to issue a final configuration list; (A.2) each hardware module checks whether the configuration list of the hardware module is consistent with the final configuration list or not, and reports the result to the state management platform; and (A.3) the state management platform determines whether to enable the hardware module to exit the normal working state according to the comparison result. The invention ensures the configuration consistency and compatibility of the system and plays an important role in the safety reliability and the system consistency of the IMA platform.
Description
Technical Field
The invention relates to the field of software design of a comprehensive modular avionics system, in particular to a configuration management method of the comprehensive modular avionics system.
Background
IMA (Integrated Modular Avionics) is the core of an aircraft Avionics system and can provide various resources including computing resources, communication resources, I/O interface resources, and system service resources to other aircraft systems.
As shown in the example of fig. 1, the physical components of an IMA system include:
two CCR (binding Computing Resource, general processing cabinets) named CCR _ L and CCR _ R, respectively. Each CCR has 10 GPM (General Processor Module) slots, 2 PCM (Power Conditioning Module) slots, and 2 ACS (rack Switch) slots, which are named as XA01 to XA14 from left to right as shown in fig. 1.
■ XA01 and XA14 slots, which are PCM resident slots;
■ XA02 to XA11 are 10 slots in total, and are GPM resident slots;
■ XA12 and XA13 slots, which are ACS resident slots;
■ the hardware modules residing on CCR _ L are named: GPM _ L1, GPM _ L2, GPM _ L3, GPM _ L4, PCM _ L1, PCM _ L2, ACS _ LA, ACS _ LB;
■ the hardware modules residing on CCR _ R are named: GPM _ R1, GPM _ R2, GPM _ R3, GPM _ R4, PCM _ R1, PCM _ R2, ACS _ RA, ACS _ RB;
four RDIUs (Remote Data Interface Unit), named RDIU _1, RDIU _2, RDIU _3, and RDIU _4, which are physically connected to the two CCR's through the AFDX bus.
Current IMA platform functions are divided into resource functions and support functions. The resource function provides three resources: data calculation, data transmission and data conversion. The support functions include: health management, data loading, fatigue indication, data monitoring, state management, network management, temperature monitoring, auxiliary cooling, fault recovery and the like.
Because the IMA platform relates to a plurality of hardware modules, each hardware module can have an independent configuration list, in order to ensure the configuration consistency, completeness and compatibility of the system, the invention provides a configuration management method of the IMA platform, and the configuration management function becomes one of the important support functions of the IMA platform.
After the configuration management functions become important functions of the IMA platform, the functional composition of the IMA platform is as shown in fig. 2.
Disclosure of Invention
The invention aims to provide a configuration management method for an integrated modular avionics system, which is used as one of important support functions of an IMA platform, realizes decision, distribution and report of system configuration by configuration management, ensures the configuration consistency and compatibility of the system, and plays an important role in the safety reliability and the system consistency of the IMA platform; meanwhile, the user can periodically obtain the monitoring report, and the system maintenance is also important.
The invention aims to be realized by the following technical scheme:
a configuration management method for an integrated modular avionics system comprises a module-level configuration list management method, wherein the configuration list management method comprises the following steps:
(A.1) each hardware module of the comprehensive modularized avionics system obtains a configuration list of the hardware module from Flash in a starting stage, reports the configuration list to a configuration management platform, and waits for the configuration management platform to issue a final configuration list;
(A.2) each hardware module checks whether the configuration list of the hardware module is consistent with the final configuration list or not, and reports the result to the state management platform;
and (A.3) the state management platform determines whether to enable the hardware module to exit the normal working state according to the comparison result.
Further, the method also comprises a platform-level configuration list management method, which comprises the following steps:
(B.1) the configuration management platform receives model messages sent by each RDIU module;
(B.2) after receiving the model information, the configuration management platform compares the model information, selects most of the model information as the current model information, and if the most of the model information is not obtained, records the fault and ignores the model information;
(B.3) the configuration management platform receives the configuration lists sent by the hardware modules, compares the configuration lists to obtain most of the configuration lists, and records faults if the most of the configuration lists cannot be obtained through comparison;
(B.4) the configuration management platform under the same CCR sends most configuration lists mutually and compares the configuration lists, if the configuration lists are consistent, the configuration list of the CCR is obtained, and otherwise, a fault is recorded;
(B.5) the CCR mutually sends configuration messages and compares the configuration messages, if the configuration messages are consistent, a final configuration list is obtained, and if the configuration lists are inconsistent, a fault is recorded;
and (B.6) the configuration management platform distributes the final configuration list to each hardware module and reports the final configuration list to the OMS.
Further, the method for reporting the module level configuration comprises the following steps:
each hardware module acquires a monitoring report of the hardware module and periodically reports the monitoring report to the OMS and the health management platform.
Further, the method for reporting the platform-level configuration comprises the following steps:
after receiving the monitoring reports of each hardware module, the health management platform integrates the monitoring reports of each hardware module into a complete report and periodically sends the report to the OMS.
Drawings
FIG. 1 is a schematic diagram of a hardware architecture of IMA;
FIG. 2 is a functional decomposition of an IMA system;
FIG. 3 is a sequence diagram of a configuration reporting function;
fig. 4 is a diagram illustrating a configuration reporting function software and hardware structure;
FIG. 5 is a sequence diagram of a configuration manifest management function;
FIG. 6 is a diagram of software and hardware configuration for configuration list management;
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
The configuration management method for the integrated modular avionics system provided by the embodiment includes two parts, namely a configuration reporting method and a configuration list management method. The configuration reporting method is to periodically report the monitoring report to an OMS (online Maintenance System). The configuration list management method refers to decision, distribution and inspection of the configuration list. The following describes these two sections separately.
1. Configuration reporting function
The configuration reporting function is divided into module level configuration reporting and platform level configuration reporting.
Fig. 3 and fig. 4 are diagrams of a reporting function sequence diagram and a software and hardware structure diagram. As can be seen from the model diagram, each hardware module (including GPM, PCM, RDIU, ACS) periodically sends its own monitoring report to the configuration management platform and OMS. The user can obtain the working state and configuration list condition of the system and each hardware module through the OMS.
1.1 Module level configuration reporting function
Each hardware module obtains a monitoring report of the hardware module and periodically reports the monitoring report to the OMS and the health management platform, wherein the hardware module comprises a GPM, an RDIU, an ACS and a PCM.
1.2 platform level configuration reporting function
After receiving the monitoring reports of each hardware module, the health management platform integrates the monitoring reports of each hardware module into a complete report, and periodically sends the report to the OMS.
2. And configuring a list management function.
The configuration list management function is divided into module level configuration list management and platform level configuration list management.
The configuration list management function sequence chart and the software and hardware structure chart are shown in fig. 5 and fig. 6. As can be seen from the model diagram, the configuration inventory management mainly realizes the consistency and compatibility of the configuration of each hardware module. And generating a final configuration list by sending messages among all hardware modules and by a certain election and decision algorithm. After obtaining the final configuration list, the configuration management platform sends the configuration list to each hardware module. Each hardware module compares its own configuration list with the final configuration list. If the comparison result of the configuration list is consistent, the module continues to work; if the comparison result is inconsistent, the fault information is recorded and reported to the state management platform, and the state management platform enables the module to release the normal working state.
2.1 Module level configuration List management
(A.1) each hardware module of the comprehensive modularized avionics system obtains a configuration list of the hardware module from Flash in a starting stage, reports the configuration list to a configuration management platform, and waits for the configuration management platform to issue a final configuration list; . The hardware module comprises GPM, RDIU, ACS and PCM.
And (A.2) each hardware module checks whether the configuration list of the hardware module is consistent with the final configuration list or not, and reports the result to the state management platform.
And (A.3) the state management platform determines whether to enable the hardware module to exit the normal working state according to the comparison result.
2.2 platform level configuration inventory management
(B.1) the configuration management platform receives model messages (AirFrameType) sent by RDIU modules such as RDIU _1, RDIU _3, RDIU _7 and the like
And (B.2) after receiving the model information, the configuration management platform compares the received three model information and selects most model information as the current model information. If most model information is not obtained, recording the fault and ignoring the model information.
(B.3) the configuration management platform (which is respectively deployed on GPM _1 and GPM _4) should receive the configuration lists sent by the configuration management functions of the hardware modules (including GPM, RDIU, ACS and PCM), and compare the configuration lists to obtain most of the configuration lists of the configuration management platforms GPM _1 and GPM _ 4. If the comparison does not yield the majority of the configuration list, a fault is recorded.
And (B.4) mutually sending most configuration lists by the configuration management platforms (GPM _1 and GPM _4) under the same CCR, comparing, obtaining the configuration list of the CCR if the configuration lists are consistent, and recording faults if the configuration lists are not consistent.
And (B.5) mutually sending configuration messages between CCR (CCR _ L and CCR _ R) and comparing, obtaining a final configuration list if the configuration messages are consistent, and recording faults if the configuration lists are not consistent.
And (B.6) the configuration management platform distributes the final configuration list to each hardware module and reports the final configuration list to the OMS.
It should be understood that equivalents and modifications of the technical solution and inventive concept thereof may occur to those skilled in the art, and all such modifications and alterations should fall within the scope of the appended claims.
Claims (3)
1. A configuration management method for an integrated modular avionics system comprises a module-level configuration list management method and a platform-level configuration list management method, and is characterized in that the configuration list management method comprises the following steps:
(A.1) a remote data interface unit in the integrated modular avionics system sends own model information to a configuration management platform of the same general processing cabinet, each hardware module of the integrated modular avionics system reports a self configuration list acquired from Flash in a starting stage to the configuration management platform of the same general processing cabinet in each sending period, and the configuration management platform waits for issuing a final configuration list; the hardware module comprises a general computer module, a power supply module, a remote data interface unit and a rack switch;
(A.2) each hardware module checks whether the configuration list of the hardware module is consistent with the final configuration list or not, and reports the result to the state management platform;
(A.3) the state management platform determines whether to make the hardware module exit the normal working state according to the comparison result;
the platform-level configuration list management method comprises the following steps:
(B.1) the configuration management platform receives model messages sent by each remote data interface unit in the same general processing cabinet;
(B.2) after receiving the model information, the configuration management platform compares the model information, selects most of the model information as the current model information, and if the most of the model information is not obtained, records the fault and ignores the model information;
(B.3) the configuration management platform receives configuration lists sent by all hardware modules in the same general processing cabinet, compares the configuration lists to obtain most of the configuration lists, and records faults if the most of the configuration lists cannot be obtained through comparison;
(B.4) the configuration management platforms under the same universal processing cabinet send most configuration lists to each other and compare, if the configuration lists are consistent, the cabinet configuration list of the same universal processing cabinet is obtained, and if the configuration lists are not consistent, a fault is recorded;
(B.5) the configuration management platforms among different universal processing cabinets send cabinet configuration lists to each other and compare, if the configuration lists are consistent, a final configuration list is obtained, and if the configuration lists are inconsistent, a fault is recorded;
and (B.6) the configuration management platform distributes the final configuration list to each hardware module and reports the final configuration list to the OMS.
2. The configuration management method for the integrated modular avionics system according to claim 1, further comprising a module-level configuration reporting method, comprising the steps of:
each hardware module acquires a monitoring report of the hardware module and periodically reports the monitoring report to the OMS and the health management platform.
3. The configuration management method for the integrated modular avionics system according to claim 2, further comprising a platform-level configuration reporting method, comprising the steps of:
after receiving the monitoring reports of each hardware module, the health management platform integrates the monitoring reports of each hardware module into a complete report and periodically sends the report to the OMS.
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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 |
| CN112102520B (en) * | 2020-08-14 | 2023-09-05 | 陕西千山航空电子有限责任公司 | Method for reporting state information of aviation equipment |
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| CN103825902A (en) * | 2014-03-04 | 2014-05-28 | 中国民航大学 | Reconstruction decision-making system and decision making method for comprehensive modularized avionics system |
| CN105224360A (en) * | 2015-09-08 | 2016-01-06 | 中国航空无线电电子研究所 | A kind of IMA system based on two-stage management and control and dynamic restructuring control method thereof |
| CN105553697A (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司西安航空计算技术研究所 | Avionics system network management system adopting SNMP protocol |
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| FR2950170B1 (en) * | 2009-09-16 | 2011-10-14 | Airbus Operations Sas | METHOD FOR GENERATING INTERFACE CONFIGURATION FILES FOR CALCULATORS OF AN AVIONIC PLATFORM |
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| CN103617074A (en) * | 2013-11-29 | 2014-03-05 | 中国航空无线电电子研究所 | Software communication system structure logic device system and monitoring, inquiring and controlling method |
| CN103825902A (en) * | 2014-03-04 | 2014-05-28 | 中国民航大学 | Reconstruction decision-making system and decision making method for comprehensive modularized avionics system |
| CN105224360A (en) * | 2015-09-08 | 2016-01-06 | 中国航空无线电电子研究所 | A kind of IMA system based on two-stage management and control and dynamic restructuring control method thereof |
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