Weiner Model Drop Test Identification of a Light Amphibious Airplane
Keywords:Weiner model, kernel function, small signal input, landing gear, light amphibious airplane
The new approach of the Weiner model for identifying drop test dynamics of a light amphibious airplane is presented in this paper. Unlike the traditional identification method of the Hammerstein model using LS-SVM with Gaussian radial basis serving as the kernel function, the small-signal excitation input is used to estimate the linear block of the Weiner model. Then, the static nonlinearity function of the model is identified through LS-SVM. The RMSE of the proposed Weiner model is 0.48805 and 0.38246 for the strut and wheel of the landing gear. The proposed Weiner model has better identification performance than the Hammerstein model and the traditional governing equation of the landing gear. The drop experiment of the light amphibious airplane is carried out not only to prove standard airworthiness compliance but also to verify the identifiability, accuracy, and performance of system identification.
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