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Accelerated fatigue load spectrum compilation method

A technology of fatigue load spectrum and load spectrum, applied in geometric CAD, computer-aided design, design optimization/simulation, etc., can solve the problems of long fatigue test cycle, long life of test target, acceleration, etc.

Pending Publication Date: 2020-02-04
BEIHANG UNIV
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to provide a method for preparing the accelerated fatigue load spectrum, which solves the serious problems that the existing fatigue load spectrum needs to be equipped with a large dispersion coefficient, resulting in long life of the test target and excessively long fatigue test period

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  • Accelerated fatigue load spectrum compilation method

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Embodiment Construction

[0061] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and embodiments. The following examples are intended to illustrate the present invention, but not to limit the scope of the present invention.

[0062] In the description of the present invention, it should be noted that, when "current" is executing an action, multiple currents appear in the text, which are all recorded in real time as time elapses.

[0063] Since the current fatigue load spectrum is the average spectrum, which reflects the average use state of the aircraft, it needs to be matched with the dispersion coefficient of the comprehensive reaction structure and the dispersion of the load spectrum. It is very long and cannot meet the serious problem of development cycle requirements. The invention provides an accelerated fatigue load spectrum compilation method.

[0064] The purpose of compiling the load spectrum is to be use...

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Abstract

The invention relates to the field of fatigue load spectrum compilation, in particular to an accelerated fatigue load spectrum compilation method. The method includes: taking a fleet overload nz-cumulative transcendental N curve family as a data source, performing compiling to obtain a corresponding stand-alone spectrum; calculating, counting and analyzing cluster load spectrum damage; and performing deducing to obtain cluster life distribution, determining the damage of the accelerated fatigue load spectrum by taking meeting the cluster life reliability requirement as a principle, determiningan overload-accumulated transcendental curve corresponding to the accelerated fatigue load spectrum through statistical analysis of a cluster nz-N curve, and further performing compiling to obtain the accelerated fatigue load spectrum. The spectrum considers the dispersion of the cluster load spectrum and the structural characteristics, and only needs to consider the dispersion of the structuralcharacteristics by reasonably weighting the damage of the load spectrum, and the dispersion coefficient value is obviously smaller than the dispersion coefficient under the average spectrum, so that the fatigue test time can be shortened exponentially, and the purpose of fatigue acceleration is achieved.

Description

technical field [0001] The invention relates to the field of fatigue load spectrum compilation, in particular to an accelerated fatigue load spectrum compilation method. Background technique [0002] In the design and finalization stage of the aircraft structure, fatigue analysis and full-scale fatigue test are needed to evaluate the life of the aircraft structure. Fatigue load spectrum is the premise of the fatigue life analysis and test of aircraft structure, which is a typical representative of the load-time history experienced by the aircraft during use. In order to truly and completely simulate the load-time history of the aircraft structure, and to compile a load spectrum that reasonably reflects the use process of the aircraft structure, in order to improve the reliability of the life analysis results and the full-scale test results, the load spectrum compilation method has been paid much attention. [0003] Load-time history data during aircraft use is the basis for...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/15G06F119/04
Inventor 贺小帆李唐李玉海董颖豪王天帅
Owner BEIHANG UNIV
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