Task reliability allocation method based on aero-engine functional architecture

Through the task reliability allocation method based on the functional architecture of the aero engine, the problem of insufficient task reliability allocation in the prior art is solved, and the accurate allocation and effective design guidance of task reliability indicators in the design stage of the aero engine scheme are achieved.

CN119717500AActive Publication Date: 2025-03-28AVIC GUIYANG ENGINE DESIGN & RES INST
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Patent Information

Application Number
CN202411285568.2
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-09-13
Publication Date
2025-03-28
Estimated Expiration
2044-09-13

AI Technical Summary

Technical Problem

The existing technology lacks an effective task reliability allocation method, and it is difficult to accurately allocate task reliability indicators to the system or functional unit during the design stage of the aero engine scheme, affecting the guiding and constraining effect of the design.

Method used

Based on the functional architecture of the aircraft engine, the allocation of task reliability indicators is completed by judging the impact of functional unit-level object functions on faults, obtaining the category and determination of fault impact, calculating the number of task functions, combining the functional balance, and completing the allocation of task reliability indicators according to the proportion of task functions.

Benefits of technology

It realizes the accurate allocation of task reliability indicators in the design stage of the aero engine scheme, provides design guidance and constraints, and improves the design quality of the system or functional unit.

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Abstract

A task reliability allocation method based on an aero-engine function architecture comprises the following steps: based on a set function redundancy R, a judgment item and allocated MTBF, judging the influence of an engine function unit-level object function on an engine fault, obtaining a fault influence category, and determining the task reliability of the aero-engine function architecture; determining a fault influence judgment value S and a task function judgment value M, and completing task success judgment of functions; calculating a task function number QMi according to the fault influence judgment value S and the task function judgment value M; and obtaining the number of function fault modes, and completing task reliability index allocation according to the proportion of the task function number QMi in combination with the function redundancy R. A task reliability allocation model is constructed on the basis of the influence relationship of factors such as basic reliability, task success function quantity and function redundancy on task reliability on the basis of a functional architecture of a corresponding system and a functional unit product level of an aero-engine.
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