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Flight control system four-redundancy signal monitoring voting method

A four-redundancy, signal technology, applied in the field of flight control systems, can solve problems such as meaningless and uncontrollable aircraft

Active Publication Date: 2020-08-11
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For example, traditional mechanical or hydraulic control systems usually fail gradually, while the failure of the flight control computer or sensors in the fly-by-wire flight control system will immediately make the aircraft uncontrollable, which makes some of the advantages of the fly-by-wire control system irrelevant. make no sense

Method used

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  • Flight control system four-redundancy signal monitoring voting method
  • Flight control system four-redundancy signal monitoring voting method
  • Flight control system four-redundancy signal monitoring voting method

Examples

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Embodiment Construction

[0020] figure 1 A diagram of a redundancy voting system 100 according to an aspect of the present disclosure is shown. As can be seen, figure 1 The redundancy voting system 100 includes a voting module 102 . The n redundancy signals S1 , S2 , . . . , Sn are input to the voting module 102 . According to an example, n can be 3. According to another example, n may be 4. However, the present disclosure is not limited by the specific value of n. The voting module 102 votes on the input n redundancy signals S1, S2, ..., Sn based on the voting algorithm, identifies and eliminates faulty signals or invalid signals therein; and obtains based on normal signals after the faulty signals are eliminated And output the voting result Valid_S.

[0021] In a four-redundancy signal monitoring and voting system according to an exemplary embodiment, the four-redundancy signals can be set as S1, S2, S3, and S4. According to an exemplary embodiment, the four-redundancy signals may be compared...

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Abstract

The invention, on one hand, relates to a four-redundancy signal voting method, which comprises the steps of obtaining four source signals of a current time unit; dividing the four source signals intotwo source signal groups, wherein each source signal group comprises two source signals; for each of the two source signal groups: determining whether the two source signals in the source signal groupare valid and whether the difference between the two source signals in the source signal group is within a threshold; calculating an effective average value of two source signals in the source signalgroup; providing the effective average value of any group as a final voting result of the current time unit through random voting; or if only one source signal group in the two source signal groups is not shielded, providing the effective average value of the source signal group as the final voting result of the current time unit. The invention, on the other hand, also relates to a correspondingapparatus.

Description

technical field [0001] The present disclosure generally relates to flight control systems, and more particularly to redundancy management of flight control systems. Background technique [0002] The application of fly-by-wire flight control system provides an opportunity to optimize aircraft performance and reduce the burden on pilots, but it also brings certain risks. For example, traditional mechanical or hydraulic control systems usually fail gradually, while the failure of the flight control computer or sensors in the fly-by-wire flight control system will immediately make the aircraft uncontrollable, which makes some of the advantages of the fly-by-wire control system irrelevant. It doesn't make sense. [0003] For this reason, and also to meet the requirements of the airworthiness authority for the integrity of the command signal of the fly-by-wire flight control system, the civil fly-by-wire flight control system generally adopts redundant design for the source signa...

Claims

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Application Information

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IPC IPC(8): G05B23/02G06F11/18
CPCG05B23/0205G05B23/0275G05B23/0286G06F11/187
Inventor 戴新喜龚孝懿郭建伟张明峰柳建锋高上
Owner COMAC