A Bandwidth Adaptive Identification Method for Flight Dynamics Model Based on Flight Test Data

Abstract

The invention discloses a flight dynamics model bandwidth adaptive identification method based on flight test data, and belongs to the technical field of aircraft flight test and flight dynamics model identification. In this method, the translational maneuvering action is firstly adopted to the center of the window function, and the preprocessing technology of copying the maneuvering action and rounding and rounding data is used to reduce the edge reduction effect of the window function and improve the accuracy of the frequency domain identification results. The classic Welch spectrum estimation method is used to calculate the input and output power spectral density, coherence function, and frequency domain response, and the multi-window synthesis technology is used to further improve the accuracy of frequency domain identification results. Select the low-order equivalent flight dynamics model and the number of equivalent frequency points; according to the coherence function and power spectral density, adaptively determine the frequency range and frequency node position of the parametric model identification; optimize the least squares method Low-order equivalent fitting in the frequency domain to obtain a more accurate parameterized low-order equivalent model.

Description

technical field [0001] The invention relates to a flight dynamics model bandwidth adaptive identification method based on flight test data, in particular to an identification method for low signal-to-noise ratio short-term maneuver flight test data, and belongs to the technical field of aircraft flight test and flight dynamics model identification. Background technique [0002] After the flight dynamics system identification is carried out on the flight test data under the specific input of the aircraft, supporting data for system modeling, wind tunnel test data calibration, flight control system design and flight quality evaluation can be obtained. An important work in engineering. Because the flight test is affected by many factors such as the type of input excitation signal, the accuracy of the measurement equipment, system interference, and flight atmospheric environment, it is very difficult to accurately identify the aircraft dynamic model from the flight test data. I...

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Problems solved by technology

[0004] In order to overcome the shortcomings of the existing frequency-domain identification method based on flight test data, which have strict requirements on long-term sweep input excitation and low accuracy of identification results such as short-time pulses and double pulses, the present invention provides a flight dynamics model based on flight test data. wide adaptive identification method

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