Helicopter moving part service life management method and device based on digital twinning, and medium

Abstract

The invention provides a helicopter moving part service life management method based on digital twinning. The helicopter moving part service life management method comprises the steps of load data collection, structural stress analysis, crack parametric modeling, fracture mechanics simulation, agent model construction of fracture mechanics parameter prediction, probabilistic prediction of crack propagation, structural risk evaluation and dynamic adjustment of a maintenance inspection plan. The invention relates to an electronic device and a storage medium, which are used for executing a helicopter moving part life management method based on digital twinning. According to the invention, multiple scales of the structure are considered and multiple models are fused; and establishing a digitaltwinning body of the typical moving part structure of the helicopter, performing high-performance real-time simulation according to the flight parameters of the helicopter and the load and damage data of the key part of the structure, dynamically updating the damage state of the typical moving part of the helicopter, and adjusting the residual life and the maintenance and inspection plan of the structure.

Description

technical field [0001] The invention relates to the technical field of structural health monitoring, in particular to a digital twin-based life management method, equipment, and medium for helicopter dynamic components. Background technique [0002] Helicopter moving parts mainly include helicopter rotor shaft, rotor hub, main rotor, tail rotor and other components, which provide lift, forward force and control force for the flight of the helicopter. Their service life and reliability directly affect the flight performance and safety of the helicopter. The key to life assessment. Different from fixed-wing aircraft, the fatigue problem of helicopters is mainly caused by low-amplitude and high-frequency vibration fatigue, which makes the service life of helicopters (in terms of flight hours) relatively low, and the crack growth life is also short, making it more prone to fatigue fractures. Flight accidents caused by damage, so the requirements for life management are more str...

AI Technical Summary

Problems solved by technology

The current stand-alone tracking strategy does not make full use of the load, structure, fatigue and other models developed and verified during the aircraft development stage, and cannot well reflect the stress history and damage evolution experienced by structural details; at the same time, it does not make good use of A large amount of data in the process of aircraft operation and maintenance to track and control various uncertainties such as load and damage scale

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