A Two-degree Redundancy Front Wheel Turning Monitoring Method

Abstract

The invention discloses a dual-redundancy front wheel turning monitoring method, which belongs to the technical field of aircraft flight control systems. The method includes the following steps: S1, monitoring whether there is a fault in bus communication; S2, judging whether there is a self-monitoring fault in front wheel turning; S3, monitoring the dynamic performance of front wheel turning, comparing the actual output of front wheel turning with the output of a front wheel turning dynamic performance model, and if the difference exceeds a specified difference value, determining that the front wheel has a turning fault; and S4, analyzing the fault state of the front wheel: under the condition that the front wheel turning communication at dual redundancies is normal and the fault state monitoring and dynamic performance monitoring are normal, if the swing reducing / turning state fed back by front wheel turning at dual redundancies or the turning deviation fed back is inconsistent for 200ms, determining that front wheel turning at dual redundancies fail, otherwise, keeping front wheel turning at dual redundancies normal; and when front wheel turning at dual redundancies fail, judging the failure of front wheel turning, and controlling front wheel turning in a swing reducing state.

Description

technical field [0001] The invention belongs to the technical field of aircraft flight control systems, and in particular relates to a double-redundancy front wheel turning monitoring method. Background technique [0002] With the wide application of digital computers and digital buses in the field of aircraft design, the traditional monitoring methods mainly focus on comparative monitoring and self-monitoring as a supplementary redundancy management algorithm. The state and dynamic response are monitored. As long as the difference of each redundancy signal is within the allowable tolerance range, the judgment of communication fault and self-monitoring fault will not be carried out. The coverage rate is relatively low, and it is difficult to correctly monitor the fault state of the digital bus signal. It is not possible to resolve the case of all channel failures. Contents of the invention [0003] Purpose of the present invention: In order to solve the above problems, th...

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Problems solved by technology

[0002] With the wide application of digital computers and digital buses in the field of aircraft design, the traditional monitoring methods mainly focus on comparative monitoring and self-monitoring as a supplementary redundancy management algorithm. The state and dynamic response are monitored. As long as the difference of each redundancy signal is within the allowable tolerance range, the judgment of communication fault and self-monitoring fault will not be carried out. The coverage rate is relatively low, and it is difficult to correctly monitor the fault state of the digital bus signal. Cases where all channel failures cannot be resolved

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