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

A technology of life management and moving parts, applied in the direction of electrical digital data processing, computer-aided design, special data processing applications, etc., can solve the problems that cannot reflect the stress history and damage evolution of structural details well

Active Publication Date: 2020-10-02
BEIHANG UNIV
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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 evolu

Method used

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

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Embodiment Construction

[0043] Below, the present invention will be further described in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of not conflicting, the various embodiments described below or the technical features can be combined arbitrarily to form new embodiments. .

[0044] A life management method for helicopter moving parts based on digital twins, such as figure 2 shown, including the following steps:

[0045] Load data acquisition, obtain the load history of the moving parts from the helicopter entity. Using the existing technical means, the measured data of the strain sensor in the key parts of the structure and the flight parameters of the helicopter are fused, and the virtual simulation model (generally given in the development stage) such as the structural finite element is used to give the main load borne by the moving parts of the helicopter ( force and moment) history and the stress status of key parts...

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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...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F30/27G06F119/04G06F119/14
CPCG06F30/15G06F30/23G06F30/27G06F2119/04G06F2119/14
Inventor 董雷霆周轩贺双新
Owner BEIHANG UNIV
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