A Method for Synchronizing Fault Information after Replacement of Redundant Flight Control Computer

A technology of flight control computer and fault information, which is applied in the direction of computer control, program control, general control system, etc. It can solve the problems that are not conducive to system maintenance and inconvenient use, and achieve the effect of improving testability

Active Publication Date: 2019-05-21
FLIGHT AUTOMATIC CONTROL RES INST
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AI Technical Summary

Problems solved by technology

This method clears the original fault information, which is not conducive to system maintenance and inconvenient to use.

Method used

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  • A Method for Synchronizing Fault Information after Replacement of Redundant Flight Control Computer
  • A Method for Synchronizing Fault Information after Replacement of Redundant Flight Control Computer

Examples

Experimental program
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Embodiment Construction

[0013] The following takes the right rudder zero adjustment test of the three-redundancy flight control computer as an example to describe the specific implementation steps of this method in detail:

[0014] Step 1: Process as follows:

[0015] Step 1.1: After the flight control computer is powered on, it will generate a fault synchronization signal nvm_sync (1 is valid), and use logic "AND" to synthesize nvm_sync and the fault information elev_r_rigging_null_fl (0 or 1) that has been latched in the non-volatile memory;

[0016] Step 1.2: Combine the comprehensive result of step 1.1 with the current right rudder zero adjustment test fault information elev_r_rigging_null_flt of this channel through logical "or" to obtain elev_r_rigging_null_flt_set (0 or 1);

[0017] Step 2: Send elev_r_rigging_null_flt_set to other redundant flight control computers;

[0018] Step 3: Process as follows:

[0019] Step 3.1: Use logical "AND" to synthesize the validity flag fcm_vld_ml (0 or 1) ...

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Abstract

The present invention belongs to a flight control system BIT software technology, and relates to a redundance flight control system fault information synchronization method after a flight control computer replaces parts. The fault information synchronization method employs a modelling design method, when fault synchronization signals are generated, logic 'or' is used to integrate faults having been latched in a nonvolatile memory and faults generated in a channel, and the integrated fault information is sent to other channels; and the logic 'or' is used to integrate the integrated fault information and fault information of other effective channels, and an integrated result is latched in the nonvolatile memory. The fault information synchronization method after a redundance flight control computer replaces parts can perform synchronization of latched fault information, low in realization complexity, high in reliability and greatly improve the system reliability and testability.

Description

technical field [0001] The invention belongs to the BIT (In-Board Self-Testing) software technology of a flight control system, and relates to a method for synchronizing fault information of a redundant flight control system after the flight control computer is replaced. Background technique [0002] The traditional redundant flight control system does not have the function of synchronizing fault information after the flight control computer is replaced. Usually, after the flight control computer of a certain redundancy is replaced, no fault synchronization is performed, or the fault records of the flight control computers of each redundancy in the system are cleared through the ground detection equipment, so that each redundancy starts to record the fault again. This method clears the original fault information, which is not conducive to system maintenance and inconvenient to use. Contents of the invention [0003] The purpose of the present invention is to propose a met...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B19/425G05B19/042
CPCG05B19/042G05B19/425
Inventor 冉鹏武方方张丹涛董强姜敏
Owner FLIGHT AUTOMATIC CONTROL RES INST
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