A Single Aircraft Remaining Life Prediction Method Based on Aircraft Structural Life Envelope Theory

A technology for aircraft structure and life prediction, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as mismatching of calendar life and failure to reflect aircraft structure

Active Publication Date: 2018-03-09
AIR FORCE UNIV PLA
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Problems solved by technology

[0045] To sum up, the reference fatigue life and reference calendar life given by the aircraft factory cannot reflect the impact of the load / corrosion-time history on the structure of the aircraft structure during actual use, which has led to serious problems in some aircraft in my country. The problem of the mismatch between fatigue life and calendar life

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  • A Single Aircraft Remaining Life Prediction Method Based on Aircraft Structural Life Envelope Theory
  • A Single Aircraft Remaining Life Prediction Method Based on Aircraft Structural Life Envelope Theory
  • A Single Aircraft Remaining Life Prediction Method Based on Aircraft Structural Life Envelope Theory

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Embodiment

[0126] The present invention is achieved in this way, the aircraft structure life envelope is the boundary line that characterizes the flight hours / number of landings and the service calendar time range of the aircraft structure in service, that is, the fatigue life of the aircraft structure in service and the use limit of the calendar life Wire. The remaining life prediction method of single aircraft structure based on the life envelope theory of aircraft structure, including the determination of the life envelope of fatigue key parts and the method of remaining life prediction, the determination of the life envelope of corrosion key parts and the method of remaining life prediction, and the life package of corrosion fatigue key parts Line determination and remaining life prediction methods, etc.

[0127] The specific steps are:

[0128] Step 1. Determination of life envelope of key fatigue components and prediction method of remaining life

[0129] Fatigue key parts refer ...

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Abstract

The invention discloses a method for predicting the remaining life of a single aircraft based on the life envelope theory of aircraft structure, which is characterized in that it includes the determination of the life envelope of key fatigue parts and the method for predicting the remaining life, the determination of the life envelope of key corrosion parts and the remaining life The prediction method and the determination of the life envelope of the key components of corrosion fatigue and the remaining life prediction method. The invention provides theoretical and method support for ensuring the safe use of the aircraft structure and improving the efficiency of the service life of the aircraft structure.

Description

technical field [0001] The invention belongs to the technical field of forecasting service life of aircraft structures, and in particular relates to a method for predicting the remaining life of a single aircraft based on the theory of aircraft structure life envelopes. Background technique [0002] Aircraft life refers to the fatigue life represented by the number of effective flight hours or the number of landings and the calendar life represented by the service life of the aircraft from being put into use to being scrapped under normal service conditions, both of which include the first turnaround period, repair interval and total life , and control the first overhaul, overhaul and total life of the aircraft structure based on the principle of first reaching the limit. (At present, China's aircraft mainly controls the first overhaul period, overhaul interval and total life of the aircraft according to the benchmark fatigue life and benchmark calendar life indicators given...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 何宇廷高潮崔荣洪杜金强安涛
Owner AIR FORCE UNIV PLA
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