A mathematical model for assessing damage and selecting diagnostic methods for aircraft landing gear components

Abstrak

This paper presents an integrated computational and diagnostic model for assessing the technical condition of aircraft landing gear components based on stress–strain analysis, fracture mechanics principles and fatigue life prediction. The relevance of the study stems from the high loads placed on landing gear components and the need to improve the reliability of their operation.
Unlike traditional non-destructive testing methods, which are mainly focused on detecting already developed defects, the proposed approach enables early-stage damage detection, quantitative evaluation of defect parameters and prediction of crack propagation. The model incorporates the calculation of nominal and local stresses considering stress concentration effects, determination of stress intensity factors and estimation of fatigue life under cyclic loading conditions.
A key feature of the study is the development of an algorithm for selecting the optimal diagnostic method based on the current structural condition, type of defect and operational parameters. This allows the transition from reactive diagnostics to predictive maintenance strategies.
The results of numerical analysis for IL-76 landing gear components made of titanium alloys demonstrate that accounting for stress concentration and crack parameters significantly increases the accuracy of damage assessment and enables early identification of critical zones. The proposed model can be implemented in software systems and integrated into modern structural health monitoring and digital twin platforms.
The practical significance of the work lies in improving diagnostic reliability, reducing maintenance costs and enhancing flight safety.