CN106483893A - A kind of Dissimilar Redundant Flight Control Computers - Google Patents
A kind of Dissimilar Redundant Flight Control Computers Download PDFInfo
- Publication number
- CN106483893A CN106483893A CN201510539474.8A CN201510539474A CN106483893A CN 106483893 A CN106483893 A CN 106483893A CN 201510539474 A CN201510539474 A CN 201510539474A CN 106483893 A CN106483893 A CN 106483893A
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- Prior art keywords
- flight
- module
- input
- arinc
- control computer
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25314—Modular structure, modules
Abstract
The invention discloses a kind of Dissimilar Redundant Flight Control Computers, control ARINC bus, and the main flight-control computer electrically connecting with flight control ARINC bus including flight；Described main flight-control computer is made up of left main control computer, middle main control computer and right main control computer；The connected mode of described left, center, right main control computer internal circuit is identical；First, second, third branch road is included inside described left main control computer；Described tie point is made up of the first power module, the first input/output module and first processor module；Described second route second source module, the second input/output module and second processing device module composition；Described 3rd route the 3rd power module, the 3rd input/output module and the 3rd processor module composition.The Dissimilar Redundant Flight Control Computers of the present invention, remaining resource in position and separation functionally, anti-propagate between remaining unit than fault it is ensured that system have higher reliability and be easier to keep in repair.
Description
Technical field
The present invention relates to a kind of computer, and in particular to a kind of Dissimilar Redundant Flight Control Computers, belongs to field of computer technology.
Background technology
Flight control computer is the core of fly-by-wire flight control system, and its reliability has important impact to the reliability of whole flight control system, general work in the form of redundancy architecture.Aircraft using remaining fly-by-wire flight control system is the F-16A/B of the U.S. earliest, at that time because digital computer technique does not also develop into certain level, thus employs the analog telex system of four remainings；With the development of digital computer technique, the U.S. employs performance preferably digital similar four redundancy computer systems in F-16C/D later；Similar four redundancy architectures have structure simply, and low cost, small volume and lightweight feature are therefore widely used in new-generation fighter；For the flight control computer system using similar redundancy, the completely identical in structure computer of multiple stage, under identical instruction controls, runs identical program, and the moment is in identical working condition, therefore interchannel Rhizoma Nelumbinis put the palms together before one point tight；Experience have shown that, the coupling of remaining passage is tighter, is affected to make the probability that whole system is collapsed bigger by common-mode fault.Therefore, in order to solve problem above it would be highly desirable to a kind of new non-similarity flight control computer of research and development, the flight control computer of common-mode fault can effectively be suppressed.
Content of the invention
（One）Technical problem to be solved
For solving the above problems, the present invention proposes a kind of Dissimilar Redundant Flight Control Computers, remaining resource in position and separation functionally, anti-propagate between remaining unit than fault it is ensured that system have higher reliability and be easier to keep in repair.
（Two）Technical scheme
The Dissimilar Redundant Flight Control Computers of the present invention, control ARINC bus, and the main flight-control computer electrically connecting with flight control ARINC bus including flight；Described main flight-control computer is made up of left main control computer, middle main control computer and right main control computer；The connected mode of described left, center, right main control computer internal circuit is identical；First, second, third branch road is included inside described left main control computer；Described tie point is made up of the first power module, the first input/output module and first processor module；Described second route second source module, the second input/output module and second processing device module composition；Described 3rd route the 3rd power module, the 3rd input/output module and the 3rd processor module composition.
Further, one end of described second source module is electrically connected with the first modular power source, and the other end is electrically connected with the 3rd power module；One end of described second input/output module is electrically connected with the first input/output module, and the other end is electrically connected with the 3rd input/output module；One end of described second processing device module is electrically connected with first processor module, and the other end is electrically connected with the 3rd processor module.
Further, described first processor module includes AMD29050 processor；Described second processing device module includes Motoroal 68040 processor；Described 3rd processor module includes INTEL 80486 processor.
Further, the connected mode of described first, second, third input/output module internal circuit is identical；Described first input/output module controls ARINC EBI to form by three flights；Wherein, two flights control ARINC EBI is input interface, and it is input/output interface that another flight controls ARINC EBI.
Further, described flight controls ARINC bus to include left, center, right flight and controls ARINC bus.
Further, described flight controls ARINC bus is that flight controls ARINC 629 bus；It is that flight controls ARINC 629 EBI that described flight controls ARINC EBI.
（Three）Beneficial effect
Compared with prior art, the Dissimilar Redundant Flight Control Computers of the present invention, three passages of the main flight control computer in left, center, right of main flight-control computer all throw people's work, and each main flight-control computer calculates and obtains the control instruction of all main control rudders and actuator, trimming system and driver artificial feel system；Main flight-control computer and flight control ARINC bus to be divided into left, center, right flight three groups of ARINC bus of control, although main flight-control computer controls ARINC bus while listening for three groups of flights, but it is merely able to control ARINC bus transmissioning data to the flight with group, when one group of flight controls ARINC bus transmission mistake or break down, do not interfere with other two groups of normal work；Pilot command controls ARINC bus to be input to each main flight-control computer by flight.
Brief description
Fig. 1 is the overall system structure schematic diagram of the present invention.
Specific embodiment
A kind of Dissimilar Redundant Flight Control Computers as shown in Figure 1, control ARINC bus 4, and the main flight-control computer electrically connecting with flight control ARINC bus 4 including flight；Described main flight-control computer is made up of left main control computer 1, middle main control computer 2 and right main control computer 3；The connected mode of described left, center, right main control computer 1,2,3 internal circuit is identical；Described left main control computer 1 is internal to include first, second, third branch road；Described tie point is made up of the first power module, the first input/output module and first processor module；Described second route second source module, the second input/output module and second processing device module composition；Described 3rd route the 3rd power module, the 3rd input/output module and the 3rd processor module composition.
One end of described second source module is electrically connected with the first modular power source, and the other end is electrically connected with the 3rd power module；One end of described second input/output module is electrically connected with the first input/output module, and the other end is electrically connected with the 3rd input/output module；One end of described second processing device module is electrically connected with first processor module, and the other end is electrically connected with the 3rd processor module.
Described first processor module includes AMD29050 processor；Described second processing device module includes Motoroal
68040 processors；Described 3rd processor module includes INTEL 80486 processor.
The connected mode of described first, second, third input/output module internal circuit is identical；Described first input/output module controls ARINC EBI to form by three flights；Wherein, two flights control ARINC EBI is input interface, and it is input/output interface that another flight controls ARINC EBI.
Described flight controls ARINC bus 4 to include left, center, right flight and controls ARINC bus.
It is that flight controls ARINC 629 bus that described flight controls ARINC bus 4；It is that flight controls ARINC 629 EBI that described flight controls ARINC EBI.
The operation principle of the Dissimilar Redundant Flight Control Computers of the present invention：Three passages of the main flight control computer in left, center, right of main flight-control computer all throw people's work, and each main flight-control computer calculates and obtains the control instruction of all main control rudders and actuator, trimming system and driver artificial feel system；Main flight-control computer and flight control ARINC bus to be divided into left, center, right flight three groups of ARINC bus of control, although main flight-control computer controls ARINC bus while listening for three groups of flights, but it is merely able to control ARINC bus transmissioning data to the flight with group, when one group of flight controls ARINC bus transmission mistake or break down, do not interfere with other two groups of normal work；Pilot command controls ARINC bus to be input to each main flight-control computer by flight.
Embodiment described above is only that the preferred embodiment of the present invention is described, and not the spirit and scope of the present invention is defined.On the premise of without departing from design concept of the present invention; various modifications and improvement that this area ordinary person makes to technical scheme; protection scope of the present invention all should be dropped into, the technology contents that the present invention is claimed, all record in detail in the claims.
Claims (6)
1. a kind of Dissimilar Redundant Flight Control Computers it is characterised in that：Control ARINC bus, and the main flight-control computer electrically connecting with flight control ARINC bus including flight；Described main flight-control computer is made up of left main control computer, middle main control computer and right main control computer；The connected mode of described left, center, right main control computer internal circuit is identical；First, second, third branch road is included inside described left main control computer；Described tie point is made up of the first power module, the first input/output module and first processor module；Described second route second source module, the second input/output module and second processing device module composition；Described 3rd route the 3rd power module, the 3rd input/output module and the 3rd processor module composition.
2. Dissimilar Redundant Flight Control Computers according to claim 1 it is characterised in that：One end of described second source module is electrically connected with the first modular power source, and the other end is electrically connected with the 3rd power module；One end of described second input/output module is electrically connected with the first input/output module, and the other end is electrically connected with the 3rd input/output module；One end of described second processing device module is electrically connected with first processor module, and the other end is electrically connected with the 3rd processor module.
3. Dissimilar Redundant Flight Control Computers according to claim 1 it is characterised in that：Described first processor module includes AMD29050 processor；Described second processing device module includes Motoroal 68040 processor；Described 3rd processor module includes INTEL 80486 processor.
4. Dissimilar Redundant Flight Control Computers according to claim 1 it is characterised in that：The connected mode of described first, second, third input/output module internal circuit is identical；Described first input/output module controls ARINC EBI to form by three flights；Wherein, two flights control ARINC EBI is input interface, and it is input/output interface that another flight controls ARINC EBI.
5. Dissimilar Redundant Flight Control Computers according to claim 1 it is characterised in that：Described flight controls ARINC bus to include left, center, right flight and controls ARINC bus.
6. Dissimilar Redundant Flight Control Computers according to claim 1 it is characterised in that：It is that flight controls ARINC 629 bus that described flight controls ARINC bus；It is that flight controls ARINC 629 EBI that described flight controls ARINC EBI.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510539474.8A CN106483893A (en) | 2015-08-30 | 2015-08-30 | A kind of Dissimilar Redundant Flight Control Computers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510539474.8A CN106483893A (en) | 2015-08-30 | 2015-08-30 | A kind of Dissimilar Redundant Flight Control Computers |
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| Publication Number | Publication Date |
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| CN106483893A true CN106483893A (en) | 2017-03-08 |
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| CN201510539474.8A Pending CN106483893A (en) | 2015-08-30 | 2015-08-30 | A kind of Dissimilar Redundant Flight Control Computers |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106950992A (en) * | 2017-04-27 | 2017-07-14 | 广东容祺智能科技有限公司 | A kind of unmanned plane flies control redundant system and its method |
| CN110647059A (en) * | 2018-06-26 | 2020-01-03 | 海鹰航空通用装备有限责任公司 | Computer system suitable for high-reliability flight control of unmanned aerial vehicle |
-
2015
- 2015-08-30 CN CN201510539474.8A patent/CN106483893A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106950992A (en) * | 2017-04-27 | 2017-07-14 | 广东容祺智能科技有限公司 | A kind of unmanned plane flies control redundant system and its method |
| CN110647059A (en) * | 2018-06-26 | 2020-01-03 | 海鹰航空通用装备有限责任公司 | Computer system suitable for high-reliability flight control of unmanned aerial vehicle |
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Application publication date: 20170308 |