Method for calculating environmental damage elastic modulus of surface coating of cross-scale cross-domain aircraft

Through cross-domain calculation methods across scales, combined with molecular dynamics and finite element simulation, the mechanical behavior of the aircraft surface coating under various environmental damage is simulated, and the problem of difficulty in evaluating and predicting the changes in the elastic modulus of the coating in the prior art is solved, achieving more accurate design optimization and reliability analysis.

CN119692115AActive Publication Date: 2025-03-25HARBIN ENG UNIV
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Patent Information

Application Number
CN202411790925.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-06
Publication Date
2025-03-25
Estimated Expiration
2044-12-06

AI Technical Summary

Technical Problem

The prior art is difficult to effectively evaluate and predict the elastic modulus changes of aircraft surface coatings under a variety of complex environmental damage, resulting in difficult optimization of mechanical properties and service life.

Method used

A cross-domain calculation method with cross-scale, combined with molecular dynamics and finite element simulation, simulates the microscopic and macroscopic mechanical behavior of coating materials under different environmental damage, and predicts the changes in elastic modulus through multi-physics coupling analysis.

Benefits of technology

A comprehensive evaluation of the elastic modulus changes of coating materials under various environmental damage is achieved, providing more accurate design optimization and reliability analysis, extending the service life of coating materials and improving the overall performance and safety of the aircraft.

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Abstract

The invention relates to the technical field of aircraft surface coatings, and particularly discloses a cross-scale cross-domain aircraft surface coating environmental damage elastic modulus calculation method, which comprises the following steps of constructing a surface coating alloy cubic single crystal initial model, simulating a damage process of a coating material in an actual environment, and calculating a surface coating alloy cubic single crystal initial model; the method comprises the following steps: establishing a finite element model of a polycrystalline alloy coating material, simulating mechanical behaviors of a microscale through molecular dynamics, and comprehensively considering the influence of different environmental damages on the elastic modulus of the coating material by utilizing micromechanics verification and macroscopic finite element simulation; theoretical basis and technical support are provided for performance evaluation, design optimization and reliability analysis in the long-term service process of the surface coating of the cross-domain aircraft, the service life of a coating material is prolonged, and the overall performance and safety of the aircraft are improved.
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