CN106549847B - A kind of novel integrated modularization avionics system - Google Patents
A kind of novel integrated modularization avionics system Download PDFInfo
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- CN106549847B CN106549847B CN201611170369.2A CN201611170369A CN106549847B CN 106549847 B CN106549847 B CN 106549847B CN 201611170369 A CN201611170369 A CN 201611170369A CN 106549847 B CN106549847 B CN 106549847B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L12/40006—Architecture of a communication node
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L12/40169—Flexible bus arrangements
- H04L12/40176—Flexible bus arrangements involving redundancy
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L67/00—Network arrangements or protocols for supporting network services or applications
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- H04L67/12—Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L2012/40267—Bus for use in transportation systems
- H04L2012/4028—Bus for use in transportation systems the transportation system being an aircraft
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Abstract
The embodiment of the invention discloses a kind of novel integrated modularization avionics systems, belong to avionics technical field.The system includes：Avionics core resource subsystem, the resident application that domain system is controlled for aircraft provide computing resource；Avionics information platform subsystem, the resident application that domain system is serviced for airplane information provide computing resource；Avionics data network subsystem is connect with avionics core resource subsystem and avionics information platform subsystem respectively, transmits the interaction data between avionics core resource subsystem and avionics information platform subsystem；Data conversion subsystem is connect with avionics data network subsystem, for providing function switching signal for aircraft system, realizes the mutual conversion between non-ARINC664 signals and ARINC664 signals.Functional domain of the embodiment of the present invention belonging to each resident functions is different, carries out function in different ways and is resident, to improve synthesization, the integration degree of aircraft system, while improving system performance.
Description
Technical field
The present invention relates to avionics technical field, more particularly to a kind of novel integrated modularization avionics system.
Background technology
Comprehensively modularized avionics system (Integrated Module Aviomics, IMA, modular comprehensive avionics system
System) it is the avionics system synthesis framework that active service Typical Aircraft uses, the C919 aircraft avionics system that B787, A380 and Chinese quotient fly
System is all made of IMA frameworks.B787 aircrafts use god of the common core system (Common Core System, CCS) as aircraft
Through maincenter, using the AFDX buses of 10/100Mbps as aircraft avionics system data transmission " maincenter ", using teledata collection
Middle device (Remote Data Concentrator, RDC) is acquired as data and data conversion equipment, realizes aviation electronics and flies
The high integrity of machine function.Common core system is by two common core resources (Common Core Resource, CCR) cabinet
Composition, each CCR cabinets are by 8 general purpose processing blocks, 2 energy supply control modules, 2 built-in AFDX interchangers and 2 light
Fine conversion module composition, the AFDX network transmissions of external optical fiber and cable two media, two CCR cabinets are remote with external six
It holds AFDX interchangers to be connected, organizes the comprehensively modularized avionics system of remaining in pairs.The avionics system composite rack that C919 aircrafts use
Structure is similar with B787 aircrafts.
The core processing system of A380 aircrafts is divided into cockpit, main cabin, four function divisions of the energy and shared device, no
Same function division, is connected using unified AFDX networks using multiple IMA, manages and execute the boat of entire aircraft jointly
Electric task, core processing and input/output module, referred to as CPIOM used by the IMA of A380, each CPIOM modules contain
1 central processing unit wiring board, 1 power supply and input/out line plate, 2 input/out line plates, 1 PCI internal mutual
Yoke plate and end system circuit.
Existing comprehensively modularized avionics system, all aircraft resident functions (are developed and ensure that grade is respectively DAL A, DAL
B, DAL C, DAL D, DAL E) reside in the processing cabinet of IMA that (B787 aircrafts and C919 aircrafts reside in CCR cabinets
GPM in, A380 aircrafts then by CPIOM processing unit complete), since A grades of resident applications of DAL are for aircraft safety
It is required that high, E grades of resident applications of DAL do not influence aircraft safety, and according to existing design framework, this five kinds of grades are stayed
It stays function to reside in the hardware environment of same architecture design, the complexity and software faults of Software for Design will certainly be increased
Probability sacrifices the overall performance of system；With the continuous development of technology, avionics system it is increasingly huge, integrated level is increasingly
Height will increasingly answer the distribution of core processing cabinet resource using existing comprehensively modularized avionics system (IMA) framework
Miscellaneous, with increasing for resident application, the overall performance of system will also be affected, since different grades of resident application is stayed simultaneously
It stays in the same cabinet, is coupled closely between system, the probability of system fault will increase.
In the implementation of the present invention, inventor has found that at least there are the following problems：It is comprehensive used by A380 aircrafts
Modularization avionics system, synthesization degree is relatively low, and simultaneously the shared of resource is not implemented in each CPIOM modules；B787 aircrafts are adopted
Comprehensively modularized avionics system, the degree of coupling is larger between system, is easy to bring resource contention and excessive coupled problem.According to existing
The comprehensively modularized avionics system having, aircraft system resident functions reside in identical hard from A grades of DAL E grades of-DAL functions
In part framework.Which increase the Software for Design complexity of hardware platform itself and software faults probability, sacrifice the whole of system
Body performance.Simultaneously with the continuous development of technology, avionics system is increasingly huge, and integrated level is higher and higher, using existing synthesis
Modularization avionics system (IMA) framework, will become increasingly complex to the distribution of core processing cabinet resource, with resident application
Increase, the overall performance of system will also be affected, and different grades of resident application resides in the same cabinet simultaneously, system
Between couple close, the probability of system fault will increase.
Invention content
The purpose of the embodiment of the present invention is to provide a kind of novel integrated modularization avionics system, and the embodiment of the present invention is by aircraft
The resident functions of system function are classified according to guarantee grade difference is developed, and different function domain selects different hardware structures,
Reduce Software for Design complexity；Functional domain belonging to each resident functions is different, carries out function in different ways and is resident,
To improve synthesization, the integration degree of aircraft system, while improving system performance.
One side according to the ... of the embodiment of the present invention provides a kind of novel integrated modularization avionics system, including：
Avionics core resource subsystem, the resident application that domain system is controlled for aircraft provide computing resource；
Avionics information platform subsystem, the resident application that domain system is serviced for airplane information provide computing resource；
Avionics data network subsystem is connect with avionics core resource subsystem and avionics information platform subsystem respectively,
Transmit the interaction data between avionics core resource subsystem and avionics information platform subsystem；
Data conversion subsystem is connect with avionics data network subsystem, and work(is converted for providing signal for aircraft system
Can, realize the mutual conversion between non-ARINC664 signals and ARINC664 signals.
Further, the resident application of aircraft control domain system includes：It develops and ensures grade DAL A, develops guarantee grade
DAL B and development ensure grade DAL C；
Airplane information service domain system resident application include：It develops and ensures grade DAL D, develops guarantee grade DAL E.
Further, avionics core resource subsystem includes：First processing cabinet and second processing cabinet, the first processor
Cabinet and second processing stack of cabinets redundancy structure in pairs, the first processing cabinet and second processing cabinet structure having the same.
Further, the first processing cabinet includes：
First processing component, the computing resource of the resident application of processing aircraft control domain system；
First switch component realizes internal information interaction；
Electric power network component is electrically connected with the first processing component and the first switch component respectively, is the first processing component
It powers with the first switch component；
Power-supply control unit, control electric power network component are that the first processing component and the first switch component are powered；
Framework panel connector, provide power supply, reserce cell, discrete magnitude input, discrete magnitude output, A664 network interfaces,
Maintenance interface and debugging interface.
Further, the first processing component includes five first processing modules, the model of the CPU of each first processing module
For PPC7448, processing is synchronized between two CPU in the same first processing module using Lockstep.
Further, the first switch component includes：First switch module and second switch module, the first interchanger
Module and second switch module form dual redundant framework, wherein first switch module and the second switch mould
Block is gigabit AFDX interchangers.
Further, the electric power network component includes：
First electric power network module and second source network module, wherein the first electric power network module and second source net
Network module is 12.5V DC power supply network modules.
Further, the power-supply control unit includes：
First energy supply control module and second source control module, the first energy supply control module and second source control module
Form dual redundant framework, wherein the first energy supply control module is electrically connected with the first electric power network module, second source control module
It is electrically connected with second source network module.
Further, avionics information platform subsystem includes：
Second processing component, the computing resource of the resident application of processing airplane information service domain system；
Gateway component realizes network interconnection with avionics data network subsystem；
Second switch component realizes internal information interaction；
Storage assembly stores computing resource.
Further, the second processing component includes：Two Second processing modules, the CPU of each Second processing module
Using multi-core processor.
Gateway component includes：First gateway and the second gateway, the first gateway and the second gateway form dual redundant framework；
Second switch component includes：3rd switch module, the 3rd switch module are Ethernet switch.
Storage assembly includes：First memory module and the second memory module.
Further, the avionics data network subsystem includes：First gigabit networking component and the second gigabit networking group
Part, the first gigabit networking component and the second gigabit networking component form dual redundant framework.
Further, the first gigabit networking component respectively with the first switch module, the first gateway, 3rd switch module
Form first network framework；
Second gigabit networking component forms second with second switch module, the second gateway, 3rd switch module respectively
The network architecture；
The first network framework is the dual redundant network architecture with second network architecture.
It is according to the ... of the embodiment of the present invention that another aspect provides a kind of flight instruments, including novel integrated described above
Modularization avionics system.
The advantageous effect of the embodiment of the present invention is,
1) a kind of novel integrated modularization proposed on the basis of original centralization comprehensively modularized avionics system IMA
Avionics system, using open framework, core network uses gigabit AFDX networks, and process resource is mainly by two core processings
Aircraft functional domain is divided into aircraft control domain system and (set by cabinet CCR and an avionics information platform subsystem AIPS composition
Meter develops the system for ensureing grade DAL A, DAL B and DAL C, such as flight management system) and airplane information service-domain system
Unite AISD (system that development and design ensures grade DAL D, DAL E, such as onboard maintenance system), two core processing cabinets
CCR controls domain system resident application for aircraft and provides computing resource, and avionics information platform subsystem AIPS is airplane information service
Domain system AISD resident applications provide computing resource；
2) each core processing cabinet CCR includes 2 energy supply control modules (PCM), 3 general purpose processing blocks (GPM), and two
A reserved slot and two gigabit AFDX switch modules；Avionics information platform subsystem AIPS includes 2 pieces of high-performance treatments
Module, 2 gateway modules, 2 high-capacity storage modules, 1 switch module, cabinet at least have ten slots；
3) use gigabit AFDX as core network so that network certainty, real-time are protected；
4) by process resource distributed arrangement, be conducive to making full use of for resource.
The present invention overcomes that synthesization degree in the prior art is low, and the degree of coupling is larger between system by the above technological means,
Easily bring the technical problems such as resource contention and excessive coupled problem.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram for novel integrated modularization avionics system that first embodiment of the invention provides；
Fig. 2 is the avionics core resource subsystem 10 and avionics information platform subsystem 20 that first embodiment of the invention provides
Network cross-linked relation schematic diagram；
Fig. 3 is a kind of structural schematic diagram for novel integrated modularization avionics system that second embodiment of the invention provides；
Fig. 4 is the structural schematic diagram for the avionics core resource subsystem 10 that second embodiment of the invention provides.
Specific implementation mode
In order to make the objectives, technical solutions and advantages of the present invention clearer, With reference to embodiment and join
According to attached drawing, the present invention is described in more detail.It should be understood that these descriptions are merely illustrative, and it is not intended to limit this hair
Bright range.In addition, in the following description, descriptions of well-known structures and technologies are omitted, to avoid this is unnecessarily obscured
The concept of invention.
Novel integrated modularization avionics system proposed by the invention is the base in existing comprehensively modularized avionics system
On plinth, aircraft resident functions system is divided into aircraft control domain system and services domain system with airplane information, for the resident work(of difference
The characteristics of energy chooses different data processing platform (DPP)s, and (avionics core resource subsystem 10 is the resident application that aircraft controls domain system
Computing resource is provided, the resident application that avionics information platform subsystem 20 services domain system for airplane information provides computing resource),
Message transmission rate, transmission bandwidth are improved as core network using gigabit AFDX networks simultaneously, so that more be resident is answered
With the synthesization degree for improving aircraft system into platform can be resident.
Aircraft controls the resident application of domain system, system development ensure grade it is high (predominantly DAL A, DAL B and
The system of DAL C, such as flight management system), it is high for the reliability requirement of process resource and Internet resources, and handle money
The demand of the size in source etc. is comparatively without so high.
And domain system serviced for airplane information, system development ensures that relatively low (predominantly DAL D, DAL E are grade
System, such as onboard maintenance system, information system), since airplane information service domain system is mainly that aircraft provides information, improves and fly
Machine comfort level, little for the safety effects of aircraft, the failure of corresponding function can't influence the safety of aircraft, meanwhile, because
Big for aircraft information system data volume, required process resource is more, for the size, memory capacity, processing speed etc. of process resource
Aspect has related needs.The difference of domain system is serviced with airplane information for aircraft control domain system, aircraft is resident by consideration
Function system is classified according to guarantee grade is developed, and the low system for ensureing grade of developing on the one hand is avoided to develop guarantee etc. to height
The interference of grade system resident application, reduces the complexity of resident application design；On the other hand, according to different brackets resident application
Feature and it is different to system resource requirements, selects different processors to carry out the design of related resident platform, reduction is set
Charging, while the advantage of different processor is played to greatest extent.
Referring to Fig. 1, Fig. 1 is a kind of structure for novel integrated modularization avionics system that first embodiment of the invention provides
Schematic diagram.
As shown in Figure 1, a kind of novel integrated modularization avionics system that first embodiment of the invention provides, the framework packet
It includes：
Avionics core resource subsystem 10, the resident application that domain system is controlled for aircraft provide computing resource.
Avionics information platform subsystem 20, the resident application that domain system is serviced for airplane information provide computing resource.
Specifically, aircraft system function is different according to guarantee grade is developed, and is divided into aircraft control domain system and aircraft letter
Breath service domain system, aircraft control domain system function include mainly that development and design ensures that grade DAL A, development ensure grade DAL
B and the system for developing guarantee grade DAL C, such as flight management system.It includes design that airplane information, which services domain-functionalities mainly,
It develops and ensures grade DAL D, develops the system for ensureing grade DAL E, such as onboard maintenance system.According to the development of resident functions
Ensure that grade is different.
Ensure that grade is different according to the development of resident functions, the high process resource of security requirement is by avionics core resource
System 10 provides.The low process resource of security requirement is provided by avionics information platform subsystem 20, i.e., aircraft controls domain system
Function resides in avionics core resource subsystem 10, and airplane information domain system function resides in avionics information platform subsystem 20
In.
Process resource distributed arrangement (is divided into aircraft control domain system and machine information service-domain work(by the embodiment of the present invention
Can), be conducive to making full use of for resource.
Avionics data network subsystem 30, respectively with avionics core resource subsystem 10 and avionics information platform subsystem 20
Connection, the interaction data between transmission avionics core resource subsystem 10 and avionics information platform subsystem 20.
Data conversion subsystem 40 is connect with avionics data network subsystem 30, is turned for providing signal for aircraft system
Function is changed, realizes mutual conversion of the non-ARINC664 signals (such as ARINC 429, CAN) between ARINC664 signals.
As shown in Fig. 2, the avionics core resource subsystem 10 and avionics information that Fig. 2, which is first embodiment of the invention, to be provided are flat
20 network cross-linked relation schematic diagram of station subsystem.
Specifically, avionics data network subsystem 30 (ADNS subsystems) is connected respectively to avionics core resource subsystem 10
With avionics information platform subsystem 20, the friendship between transmission avionics core resource subsystem 10 and avionics information platform subsystem 20
Mutual data.
In the present invention, the interchanger in avionics core resource subsystem 10 uses gigabit AFDX interchangers, avionics information flat
Interchanger in station subsystem 20 uses Ethernet switch, and avionics data network subsystem 30 is divided to for two network architectures, and
Play the role of data interaction.As shown in Figure 2, centered on gateway (avionics data network subsystem 30), top half is boat
Electric core resource subsystem 10 is AFDX networks with avionics data network subsystem 30, and lower half portion is avionics information platform subsystem
System 20 is ethernet network with avionics data network subsystem 30.
Avionics core resource subsystem 10 can also reduce since required resident functions are reduced to its cabinet, to small-sized
Change, lightweight IMA cabinets direction turns, simultaneously because the resident functions classification of difference DAL grades is resident, reduces Software for Design
Complexity can select the multi-core processor of higher performance simultaneously for D/E grades of functions of DAL according to resident functions feature, from
And the chip of single core processor framework limits before breaking away from.
Referring to Fig. 3, Fig. 3 is the structural representation for the avionics core resource subsystem 10 that second embodiment of the invention provides
Figure.Fig. 4 is the structural schematic diagram for the avionics core resource subsystem 10 that second embodiment of the invention provides.
As shown in Figure 3,4, the avionics core resource subsystem 10 that second embodiment of the invention provides further comprises：
First processing cabinet 11 and second processing cabinet 12,12 groups of the first processing cabinet 11 and second processing cabinet are in pairs superfluous
Remaining framework, the first processing cabinet 11 and 12 structure having the same of second processing cabinet.
First processing cabinet 11 and second processing cabinet 12 form avionics core resource subsystem 10, the first processing cabinet 11
Dual redundant framework is formed with second processing cabinet 12, the common resident application that domain system 10 is controlled for aircraft provides computing resource.
First processing cabinet 11 further comprises：
First processing component 111, the computing resource of the resident application of processing aircraft control domain system.
Specifically, the first processing component 111 includes five first processing modules 111-1, each first processing module 111-1
CPU use high reliability single core processor (such as PPC7448), using Lockstep to the same first processing module
Processing is synchronized between two CPU in 111-1.
Since the first processing cabinet 11 and second processing cabinet 12 only need the computing resource of processing aircraft control domain system,
Thus the quantity of first processing module 111-1 (general purpose processing block, GPM) is reduced, and B787 types can configure at eight piece first
Module 111-1 is managed, aircraft model is different, and the quantity of first processing module 111-1 changes accordingly, first processing module
The particular number of 111-1 can be according to airplane design initial stage to resident application demand assessed after determine, if be not required to
That wants can then reserve, and be used as subsequent expansion.
Connection relation between first processing component 111 and power-supply control unit 114 and the first switch component 112 is still
Existing connection type is continued to use, details are not described herein again.
CPU selected by first processing module (general purpose processing block, GPM) using high reliability single core processor (such as
Can select PPC7448), it using Lockstep technologies, realizes the tight synchronization between two CPU in the same GPM, meets high complete
Whole property requirement.
Resident functions are by original DAL A, DAL B, DAL C, DAL D in first processing module (general purpose processing block, GPM)
And E grades of DAL becomes the complexity drop of only resident partition method between DAL A, DAL B and C grades of DAL, different DAL
It is low, be conducive to the comprehensive integration of resident functions.
First switch component 112 realizes internal information interaction.Specifically, the first switch component 112 includes：First
Switch module 112-1 and second switch module 112-2, the first switch module 112-1 and second switch module 112-2
Dual redundant framework is formed, and is communicated with avionics data network subsystem 30.Wherein, the first switch module 112-1
It is gigabit AFDX interchangers with the second switch module 112-2.
Electric power network component 113 is electrically connected with the first processing component 111 and the first switch component 112 respectively, is first
112 assembly power supply of processing component 111 and the first interchanger.
Power-supply control unit 114, control electric power network component 114 are the first processing component 111 and the first switch component
112 power supplies.
Power-supply control unit 114 includes：First energy supply control module 114-1 and second source control module 114-2, first
Energy supply control module 114-1 and second source control module 114-2 form dual redundant framework.
Electric power network component 115 includes：First electric power network module 115-1 and second source network module 115-2,
In, the first electric power network module 115-1 and second source network module 115-2 are 12.5VDC electric power network modules.
Wherein, the first energy supply control module 114-1 is electrically connected with the first electric power network module 115-1, second source control
Module 114-2 is electrically connected with second source network module 115-2.
Framework panel connector 116, provides that power supply, reserce cell, discrete magnitude input, discrete magnitude output, A664 networks connect
Mouth, maintenance interface and debugging interface.
As shown in figure 3, the avionics information platform subsystem 20 that third embodiment of the invention provides includes：
Second processing component 21, the computing resource of the resident application of processing airplane information service domain system.
The second processing component 21 includes：Two Second processing modules 211.At two 211 selections of Second processing module
The CPU of the high module of rationality energy, each Second processing module uses multi-core processor.
Gateway component 22 realizes network interconnection with avionics data network subsystem 30.
Gateway component 22 includes：First gateway 221 and the second gateway 222, the first gateway 221 and the second gateway 222 composition
Dual redundant framework.
Second switch component 23 realizes internal information interaction.
Second switch component 23 includes：3rd switch module 231, the 3rd switch module 231 are Ethernet
Interchanger.
Storage assembly 24 stores computing resource.
Storage assembly 24 includes：First memory module 241 and the second memory module 242.
In this framework, only resident airplane information services domain-functionalities to avionics information platform subsystem (AIPS subsystems), that is, grinds
System ensures the function of D grade of grade DAL and E grades of DAL, does not influence the flight safety of aircraft, avionics information platform subsystem 20 to
Include two Second processing modules less, 2 high-capacity storage modules, two gateways, a switch module, cabinet at least has
Ten slots, other slots support subsequent expansion function.Second processing module uses high-performance multi-core processor, processing speed
Soon, small, small power consumption.The stock number needed simultaneously for airplane information service is bigger, so being equipped with two pieces of large capacities
Memory before in scheme, does not have memory module in core processing cabinet CCR, is provided subsequently to carry out big data calculating yet
One scalability.What it is due to avionics information platform subsystem (AIPS subsystems) processing is the resident of D grades of DAL and E grades of DAL
Function does not interfere with the safety of aircraft, and Ethernet switch may be used in the interchanger in system, by security gateway and flies
Machine control domain carries out security isolation, while reaching the function of data interaction.
As shown in figure 3, the avionics data network subsystem 30 that third embodiment of the invention provides includes：
First gigabit networking component 31 and the second gigabit networking component 32, the first gigabit networking component 31 and the second kilomega network
Network component 32 forms dual redundant framework.Specifically, as shown in figure 3, the first gigabit networking component 31 is A networks, the second kilomega network
Network component 32 is B networks, and the first gigabit networking component 31 and the second gigabit networking component 32 are all made of gigabit AFDX as trunk
Network so that network certainty, real-time are protected.
First gigabit networking component 31 respectively with the first switch module 112-1, the first gateway 221,3rd switch mould
Block 231 forms first network framework (referring to Fig. 3, i.e. A nets).
Second gigabit networking component 32 respectively with second switch module 112-2, the second gateway 222,3rd switch mould
Block 231 forms second network architecture (referring to Fig. 3, i.e. B nets).
The first network framework (i.e. A nets) is the dual redundant network architecture with second network architecture (i.e. B nets).
The avionics data network subsystem 30 (ADNS subsystems) of the embodiment of the present invention uses the gigabit AFDX nets of double remainings
Network forms, and improves the transmission rate of core network, and transmission bandwidth improves transmitted data amount, is that the big data of avionics system is handled
Processing capacity provides possibility.Due to residing A grades of DAL, DAL B in the first processing cabinet 11 and second processing cabinet 12
Grade, the resident functions of C grades of DAL, so network also requires high integrality, the end system of AFDX to use EDE technologies accordingly, from
And reach the high integrality of network.
The embodiment of the present invention additionally provides a kind of flight instruments, including above-mentioned novel integrated modularization avionics system.
As described above, the present invention describes a kind of novel integrated modularization avionics system in detail, the embodiment of the present invention have with
Lower technique effect：
1. a kind of novel integrated proposed on the basis of original centralization novel integrated modularization avionics system (IMA)
Modularization avionics system, using open framework, by two core processing cabinet CCR, gigabit AFDX interchangers, avionics information
Platform subsystem forms；
2. aircraft system resident functions staying method：Aircraft system function is different according to guarantee grade is developed, and is divided into aircraft
It controls domain system and airplane information services domain system, aircraft control domain system function includes mainly that development and design ensures grade
The system of DAL A, DAL B and DAL C, such as flight management system, airplane information service domain-functionalities include mainly that design is ground
The system that system ensures grade DAL D, DAL E, such as onboard maintenance system.Ensure that grade is different according to the development of resident functions,
The high process resource of security requirement is provided by the GPM in CCR processing cabinets, and processor selects the place for meeting ARINC653 standards
Manage device；The low process resource of security requirement is provided by the processing module in AIPS, i.e., aircraft control domain system function resides in
In two CCR cabinets, airplane information domain system function resides in AIPS platforms；
3. due to comprehensively modularized avionics system cabinet only handle DAL A B C grades of resident functions, GPM quantitative designs are
5 pieces (wherein two pieces are reserved slot), reduce the size of CCR cabinets；
4. airplane information service processing cabinet design method：Including 2 pieces of processing modules, 2 gateway modules, 2 large capacities
Memory module, 1 switch module, cabinet at least have ten slots；Using double remaining security gateways by the network of information field
It is isolated with aircraft control domain network, processing module uses high-performance processor, and small, power consumption is big.
It should be understood that the above-mentioned specific implementation mode of the present invention is used only for exemplary illustration or explains the present invention's
Principle, but not to limit the present invention.Therefore, that is done without departing from the spirit and scope of the present invention is any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.In addition, appended claims purport of the present invention
Covering the whole variations fallen into attached claim scope and boundary or this range and the equivalent form on boundary and is repairing
Change example.
Claims (11)
1. a kind of novel integrated modularization avionics system, which is characterized in that including：
Avionics core resource subsystem, the resident application that domain system is controlled for aircraft provide computing resource；
Avionics information platform subsystem, the resident application that domain system is serviced for airplane information provide computing resource；
Avionics data network subsystem is connect with avionics core resource subsystem and avionics information platform subsystem respectively, transmission
Interaction data between avionics core resource subsystem and avionics information platform subsystem；
Data conversion subsystem is connect with avionics data network subsystem, real for providing function switching signal for aircraft system
Existing mutual conversion between non-ARINC664 signals and ARINC664 signals；
The avionics core resource subsystem includes：First processing cabinet and second processing cabinet, the first processing cabinet and second
It handles cabinet and forms dual redundant framework, the first processing cabinet and second processing cabinet structure having the same；
Described first, which handles cabinet, includes：
First processing component, the computing resource of the resident application of processing aircraft control domain system；
First switch component realizes internal information interaction；
Electric power network component is electrically connected with the first processing component and the first switch component respectively, is the first processing component and the
One switch component is powered；
Power-supply control unit, control electric power network component are that the first processing component and the first switch component are powered；
Framework panel connector provides power supply, reserce cell, discrete magnitude input, discrete magnitude output, A664 network interfaces, safeguards
Interface and debugging interface.
2. system according to claim 1, which is characterized in that
Aircraft control domain system resident application include：It develops and ensures grade DAL A, develops guarantee grade DAL B and development
Ensure grade DAL C；
Airplane information service domain system resident application include：It develops and ensures grade DAL D, develops guarantee grade DAL E.
3. system according to claim 1, which is characterized in that the first processing component includes five first processing modules, often
The model PPC7448 of the CPU of a first processing module, using Lockstep to two in the same first processing module
Processing is synchronized between CPU.
4. system according to claim 1, which is characterized in that the first switch component includes：
First switch module and second switch module, the first switch module and second switch module form dual redundant frame
Structure, wherein first switch module and the second switch module are gigabit AFDX interchangers.
5. system according to claim 1, which is characterized in that the electric power network component includes：
First electric power network module and second source network module, wherein the first electric power network module and second source network mould
Block is 12.5V DC power supply network modules.
6. system according to claim 5, which is characterized in that the power-supply control unit includes：
First energy supply control module and second source control module, the first energy supply control module and second source control module composition
Dual redundant framework, wherein the first energy supply control module is electrically connected with the first electric power network module, second source control module and the
Two electric power network modules are electrically connected.
7. according to the system described in any one of claim 1-6, which is characterized in that avionics information platform subsystem includes：
Second processing component, the computing resource of the resident application of processing airplane information service domain system；
Gateway component realizes network interconnection with avionics data network subsystem；
Second switch component realizes internal information interaction；
Storage assembly stores computing resource.
8. system according to claim 7, which is characterized in that
The second processing component includes：The CPU of two Second processing modules, each Second processing module is handled using multinuclear
Device；
Gateway component includes：First gateway and the second gateway, the first gateway and the second gateway form dual redundant framework；
Second switch component includes：3rd switch module described in 3rd switch module is Ethernet exchanging；
Storage assembly includes：First memory module and the second memory module.
9. system according to claim 7, which is characterized in that the avionics data network subsystem includes：First gigabit
Networking component and the second gigabit networking component, the first gigabit networking component and the second gigabit networking component form dual redundant framework.
10. system according to claim 9, which is characterized in that
First gigabit networking component forms first network with the first switch module, the first gateway, 3rd switch module respectively
Framework；
Second gigabit networking component forms the second network with second switch module, the second gateway, 3rd switch module respectively
Framework；
The first network framework is the dual redundant network architecture with second network architecture.
11. a kind of flight instruments, which is characterized in that including the novel integrated module described in any one of claim 1-6,8-10
Change avionics system.
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| CN108075824A (en) * | 2018-01-02 | 2018-05-25 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Common core resource cabinet and comprehensively modularized avionics system |
| CN109743241A (en) * | 2018-12-26 | 2019-05-10 | 中国民航大学 | A kind of long-range aeronautical data bus switch equipment based on high-performance processor |
| CN109936483B (en) * | 2019-04-22 | 2021-12-14 | 中国航空无线电电子研究所 | Universal intelligent remote data concentrator |
| CN110311697B (en) * | 2019-06-24 | 2021-07-09 | 中国航空无线电电子研究所 | Remote data concentrator |
| CN110609700B (en) * | 2019-09-23 | 2022-11-04 | 中国航空无线电电子研究所 | Distributed comprehensive modular avionics system configuration management system |
| CN111682886B (en) * | 2020-06-15 | 2021-06-08 | 北京国科天迅科技有限公司 | Optical fiber avionics network system for data transmission by adopting coaxial cable |
| CN112051859A (en) * | 2020-08-11 | 2020-12-08 | 湖北吉利太力飞车有限公司 | Avionics system of air traffic aircraft based on AFDX network |
| CN113573277B (en) * | 2021-08-11 | 2023-04-07 | 中国商用飞机有限责任公司 | Application resident type wireless avionics network system architecture |
| CN114741133B (en) * | 2022-04-21 | 2023-10-27 | 中国航空无线电电子研究所 | Comprehensive modularized avionics system resource allocation and assessment method based on model |
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