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Aircraft structure DFR analysis method based on damage equivalent conversion

A technology of aircraft structure and analysis method, applied in computer-aided design, calculation, geometric CAD, etc., can solve problems such as differences, fatigue life depletion, and differences in actual conditions, and achieve the effect of facilitating engineering applications

Active Publication Date: 2021-04-23
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

However, since the corrosion process is a physical quantity strongly related to the calendar time, the development and accumulation of corrosion damage will continue to change over time. It is obvious that using "a certain moment" to calculate and evaluate whether the fatigue life under corrosion conditions meets the target life requirements There is a difference from the actual situation
At the same time, since the fatigue life of the aircraft will continue to decrease with the increase of the service time during the service period, the target fatigue life corresponding to different moments is different. Although the existing methods have established the relationship between the structural DFR and the corrosion time, and The influence of corrosion on structural fatigue life is characterized by the change of structural DFR value, but the essence of DFR analysis is still based on the whole life index, but in fact, due to the consumption of fatigue life during use, the target life at different times is Different, the analysis is still carried out according to the whole life index, and the analysis result is too conservative

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  • Aircraft structure DFR analysis method based on damage equivalent conversion
  • Aircraft structure DFR analysis method based on damage equivalent conversion
  • Aircraft structure DFR analysis method based on damage equivalent conversion

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Embodiment Construction

[0049] The invention provides an aircraft structure DFR method based on damage equivalent conversion, converts the damage equivalent caused by corrosion into fatigue damage, and re-establishes a new failure criterion according to the aircraft fatigue life index and calendar life index. analysis process.

[0050] According to relevant research results, the following assumptions are made within the acceptable scope of the project:

[0051] a) The damage caused by corrosion fatigue and conventional fatigue of the aircraft structure is independent of each other and conforms to the principle of linear cumulative damage, that is, the corrosion damage in ground parking and the fatigue damage in flight use are independent of each other, and there is no mutual coupling between them;

[0052] b) During the entire service life of the aircraft structure, a unified time coordinate system of ground parking time and air flight time is adopted, and ground parking corrosion is continuous throu...

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Abstract

The invention belongs to the technical field of aircraft structure analysis, and discloses an aircraft structure DFR analysis method based on damage equivalent conversion. The damage equivalent of corrosion to the structure is fatigue damage, direct accumulation of different types of damage is achieved, the limitation that an existing DFR method can only conduct analysis at a certain moment under the corrosion condition is broken through, real-time DFR analysis of the whole life cycle of the aircraft structure under the corrosion condition is achieved, and the fatigue life margin and the calendar life margin are synchronously given, so that it is convenient for engineering application.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure analysis, in particular to an aircraft structure DFR analysis method based on damage equivalent conversion. Background technique [0002] The existing DFR analysis method of aircraft structure under corrosion conditions mainly establishes the change curve of structure DFR value with corrosion time, and then conducts DFR analysis of aircraft structure under corrosion conditions according to the DFR analysis process under general conditions. Under the expected service load spectrum, check whether the design fatigue life meets the target life index requirements. However, since the corrosion process is a physical quantity strongly related to the calendar time, the development and accumulation of corrosion damage will continue to change over time. It is obvious that using "a certain moment" to calculate and evaluate whether the fatigue life under corrosion conditions meets the target life re...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F119/04G06F119/14
CPCG06F30/15G06F2119/04G06F2119/14Y02T90/00
Inventor 王继普王新波张志楠王斌团
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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