CN106873565B - A kind of redundancy flight control computer changes fault message synchronous method after part - Google Patents

A kind of redundancy flight control computer changes fault message synchronous method after part Download PDF

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Publication number
CN106873565B
CN106873565B CN201510932625.6A CN201510932625A CN106873565B CN 106873565 B CN106873565 B CN 106873565B CN 201510932625 A CN201510932625 A CN 201510932625A CN 106873565 B CN106873565 B CN 106873565B
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fault message
comprehensive
flight control
control computer
logical
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CN106873565A (en
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冉鹏
武方方
张丹涛
董强
姜敏
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No 618 Research Institute of China Aviation Industry
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No 618 Research Institute of China Aviation Industry
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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
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/42—Recording and playback systems, i.e. in which the programme is recorded from a cycle of operations, e.g. the cycle of operations being manually controlled, after which this record is played back on the same machine
    • G05B19/425—Teaching successive positions by numerical control, i.e. commands being entered to control the positioning servo of the tool head or end effector

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Robotics (AREA)
  • Hardware Redundancy (AREA)
  • Testing And Monitoring For Control Systems (AREA)

Abstract

The invention belongs to flight control system BIT (built in test survey) software technologies, are related to a kind of method that redundance flight control system carries out fault message synchronization after flight-control computer changes part.This method uses modeled design method, when generating failed synchronization signal, the failure generated using failure and this channel latched in the comprehensive nonvolatile storage of logical "or", and comprehensive fault message is sent to other channels；Comprehensive fault message and the fault message in other effective channels are integrated using logical "or", the result after synthesis is latched into nonvolatile storage.The present invention can synchronize the fault message of latch when flight control computer changes part, realize that complexity is low, high reliablity substantially increases the reliability and testability of system.

Description

A kind of redundancy flight control computer changes fault message synchronous method after part
Technical field
The invention belongs to flight control system BIT (built in test survey) software technologies, are related to a kind of redundance flight control System carries out the synchronous method of fault message after flight-control computer changes part.
Background technique
Traditional redundance flight control system does not have carries out the synchronous function of fault message after flight control computer changes part. After the flight control computer replacement of certain usual remaining, removed without the processing of any failed synchronization, or by ground checkout equipment The failure logging of each remaining flight control computer of system makes each remaining restart to carry out failure logging.This method removes original Some fault messages are unfavorable for system maintenance, inconvenient to use.
Summary of the invention
The purpose of the present invention is: it proposes that a kind of realization is convenient, it is same fault message can be carried out after flight control computer changes part The method of step.
The technical scheme is that using the comprehensive nonvolatile storage of logical "or" when generating failed synchronization signal In the failure that generates of latched failure and this channel, and comprehensive fault message is sent to other channels；Use logic "or" integrates comprehensive fault message and the fault message in other effective channels, the result after synthesis is latched into non-easy It loses in memory.
The redundancy flight control computer changes fault message synchronous method after part, and its step are as follows:
Step 1: when generating failed synchronization signal, using event latched in the comprehensive nonvolatile storage of logical "or" The failure that barrier and this channel generate；
Step 2: fault message comprehensive in step 1 is sent to other channels；
Step 3: being carried out fault message comprehensive in step 1 and the fault message in other effective channels using logical "or" It is comprehensive；
Step 4: fault message comprehensive in step 3 is latched into nonvolatile storage described in step 1.
The present invention have the advantage that and the utility model has the advantages that the present invention fault message can be carried out after flight control computer changes part same Step, to save the health status of system to greatest extent, substantially increases the testability of system.
Detailed description of the invention
Fig. 1 is the logic chart that a kind of redundancy flight control computer of the present invention changes fault message synchronous method after part；
Fig. 2 is the flow chart that a kind of redundancy flight control computer of the present invention changes fault message synchronous method after part.
Specific embodiment
Below by taking the zeroing test of the right direction rudder zero-bit of triplex redundance flight control computer as an example, the specific implementation of this method is walked Suddenly it is described in detail:
Step 1: processing is as follows:
Step 1.1: flight control computer powers on after changing part, can generate failed synchronization signal nvm_sync (1 is effective), uses Logical "and" integrates fault message elev_r_rigging_null_fl latched in nvm_sync and nonvolatile storage (0 or 1)；
Step 1.2: the synthesis result of step 1.1 is returned to zero by the current right direction rudder zero-bit of logical "or" and this channel Test failure information elev_r_rigging_null_flt is integrated, and elev_r_rigging_null_flt_set (0 is obtained Or 1)；
Step 2: elev_r_rigging_null_flt_set is sent to the flight control computer of other remainings；
Step 3: processing is as follows:
Step 3.1: using the comprehensive left remaining channel flight control computer validity flag fcm_vld_ml of logical "and" (0 or 1) return to zero test result elev_r_rigging_null_flt_l (0 with the right direction rudder zero-bit of left remaining channel flight control computer Or 1)；
Step 3.2: using the comprehensive right remaining channel flight control computer validity flag fcm_vld_mr of logical "and" (0 or 1) return to zero test result elev_r_rigging_null_flt_r (0 with the right direction rudder zero-bit of right remaining channel flight control computer Or 1)；
Step 3.3: being carried out elev_r_rigging_null_flt_set with 3.1 and 3.2 result using logical "or" It is comprehensive, it generates elev_r_rigging_null_flt_set_csol (0 or 1)；
Step 4: elev_r_rigging_null_flt_set_csol is subjected to nonvolatile storage fault latch.
The present invention uses modeled design method, non-volatile using logical "or" synthesis when generating failed synchronization signal The failure that latched failure and this channel generate in memory, and comprehensive fault message is sent to other channels；Make Comprehensive fault message and the fault message in other effective channels are integrated with logical "or", the result after synthesis is latched Into nonvolatile storage.The present invention can synchronize the fault message of latch when flight control computer changes part, realize multiple Polygamy is low, high reliablity, substantially increases the reliability and testability of system.

Claims (4)

1. a kind of redundancy flight control computer changes fault message synchronous method after part, which is characterized in that
When generating failed synchronization signal, failure and this channel latched in the comprehensive nonvolatile storage of logical "or" are used The failure of generation, and comprehensive fault message is sent to other channels；Using logical "or" by comprehensive fault message and its He integrates the fault message in effective channel, and the result after synthesis is latched into nonvolatile storage.
2. a kind of redundancy flight control computer according to claim 1 changes fault message synchronous method after part, feature exists In, the specific steps are as follows:
Step 1: when generating failed synchronization signal, using failure latched in the comprehensive nonvolatile storage of logical "or" and The failure that this channel generates；
Step 2: fault message comprehensive in step 1 is sent to other channels；
Step 3: using logical "or" that fault message comprehensive in step 1 and the progress of the fault message in other effective channels is comprehensive It closes；
Step 4: fault message comprehensive in step 3 is latched into nonvolatile storage described in step 1.
3. a kind of redundancy flight control computer according to claim 2 changes fault message synchronous method after part, it is characterized in that: Failed synchronization signal is discrete signal, and value is 0 or 1.
4. a kind of redundancy flight control computer according to claim 2 changes fault message synchronous method after part, it is characterized in that: Fault message is Boolean type amount, and value is 0 or 1.
CN201510932625.6A 2015-12-14 2015-12-14 A kind of redundancy flight control computer changes fault message synchronous method after part Active CN106873565B (en)

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Publication number Priority date Publication date Assignee Title
CN107783473A (en) * 2017-09-06 2018-03-09 中国航空工业集团公司西安飞行自动控制研究所 A kind of redundancy flight control system BIT detects state judging method
CN113759873B (en) * 2021-09-01 2023-05-23 中国航空工业集团公司西安飞行自动控制研究所 Method for handling self-detection faults in motor of flight control system

Citations (4)

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Publication number Priority date Publication date Assignee Title
JPH11178217A (en) * 1997-12-05 1999-07-02 Hitachi Ltd System and method for synchronizing controllers of multiple systems
CN104002960A (en) * 2014-05-27 2014-08-27 中国航天科技集团公司烽火机械厂 Method and system for recovering vibration faults of electric steering engine
CN104137008A (en) * 2012-02-20 2014-11-05 菲尼克斯电气公司 Method for the failsafe operation of a process control system with redundant control devices
ES2523129T3 (en) * 2011-02-16 2014-11-21 Invensys Systems Inc. Doubly redundant process controller

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104866389A (en) * 2014-02-25 2015-08-26 北京奇虎科技有限公司 Data recovery method as well as data backup method, device and system based on mobile operating system
CN104965769A (en) * 2014-07-28 2015-10-07 浙江大华技术股份有限公司 System, method and apparatus for on-line detecting consistency of memory data between primary and standby servers

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH11178217A (en) * 1997-12-05 1999-07-02 Hitachi Ltd System and method for synchronizing controllers of multiple systems
ES2523129T3 (en) * 2011-02-16 2014-11-21 Invensys Systems Inc. Doubly redundant process controller
CN104137008A (en) * 2012-02-20 2014-11-05 菲尼克斯电气公司 Method for the failsafe operation of a process control system with redundant control devices
CN104002960A (en) * 2014-05-27 2014-08-27 中国航天科技集团公司烽火机械厂 Method and system for recovering vibration faults of electric steering engine

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