Non-linear aerodynamic data rapid modeling method and system and storage medium

Abstract

The invention discloses a nonlinear aerodynamic data rapid modeling method and system and a storage medium. The modeling method comprises the steps of obtaining initial flight data and performing nonlinear aerodynamic modeling; using the initial flight data to generate an orthogonal modeling function and initialize an orthogonal model; acquiring new real-time flight data, and performing iterative updating of the initialized orthogonal model; and determining a nonlinear aerodynamic data real-time model according to the relevancy weight obtained by iterative updating. After new flight data are obtained in the flight process, the data are processed in time, and the orthogonal model is updated, so that the model can ensure that the model has enough complexity to capture nonlinearity of aerodynamic force or torque coefficients, and meanwhile, the structure is simple enough, and the state of the aircraft can be predicted conveniently, quickly and accurately. According to the method, under the reasonable calculation requirement, the global aerodynamic precise model with the good prediction capability can be generated in real time, after new flight data is obtained, the orthogonal function pool can be updated only through simple matrix operation, and the operation efficiency is greatly improved.

Description

technical field [0001] The invention belongs to the field of aircraft engineering, and in particular relates to a nonlinear aerodynamic data rapid modeling method, system and storage medium. Background technique [0002] In recent years, with the continuous progress of aviation technology and computer technology, hypersonic aircraft has developed rapidly, and its superior performance has made it a hot research topic for various scientific and technological powers. Establishing an accurate aerodynamic model is an important part of aircraft engineering. Important foundations and prerequisites for flight control, stability design, and aircraft simulation. [0003] The flight state of an aircraft is characterized by nonlinear aerodynamics, usually involving a wide range of changes in angle of attack α, sideslip angle β, and body axis velocity [1] (like figure 1 shown, where x b ,y b ,z b is the body coordinate system; x w ,y w ,z w is the airflow coordinate system; x s ...

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Problems solved by technology

However, this method also has limitations, because the method of obtaining start-up data through numerical calculations and wind tunnel experiments requires a lot of time, money, and computing resources, and there are inherent accuracy limitations in ground equipment, for example, wind tunnels Scale and geometric differences of the model relative to the full-scale model, wind tunnel wall and support interference, wind tunnel flow angles, Reynolds number differences, and mesh geometric similarity of the vehicle and flow field

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