Research On The Preparation And Use Method Of Fatigue Load Spectrum Of General Aviation Aircraft Structure Oriented To Digital Twin

The safety hazard caused by the structural fatigue caused by the aging of the aircraft has become an unavoidable problem in the development of general aviation.In order to ensure the safety of aircraft structure,facing the digital twin technology of general aircraft structure,how to use flight data to compile high-quality fatigue load spectrum of key parts has always been an important content of single aircraft life monitoring technology.For this reason,this thesis studies the method of compiling the load spectrum of key parts for the Cessna 172 aircraft using the flight data of Garmin G1000.The main process includes the following aspects:(1)Use the mean interpolation method,isolation forest and other algorithms to process the original flight data to make the flight data available.(2)Extract and visualize the data of typical load state areas,and use PCA principal component analysis and cluster analysis to achieve data dimensionality reduction and data centralization.(3)Calculate the aerodynamic parameters through mathematical transformation between different coordinate systems in aerodynamics,and use the panel method to calculate the aerodynamic load of the Cessna 172 aircraft.(4)The three-dimensional model of the Cessna 172 wing was established and meshed,and the CATIA software was used for finite element analysis to obtain the load spectrum of key parts.This study provides a reference for the operation and maintenance of the Cessna 172 aircraft,the first teaching aircraft of the Civil Aviation Institute of China.