Parameter Identification Method for Nonsmooth Aeroelastic System

In this paper, a parameter identification method merged with the precise integration method and the predictor–corrector strategy is proposed to identify the parameters of a nonsmooth aeroelastic system quickly and accurately. Considering the aeroelastic system subject to unsteady aerodynamic force,...

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Bibliographic Details
Published in:AIAA journal 2022-09, Vol.60 (9), p.5357-5371
Main Authors: Li, Wen-Long, Chen, Yan-Mao, Liu, Ji-Ke, Lu, Zhong-Rong, Liu, Guang
Format: Article
Language:English
Subjects:
Aerodynamic forces
Aeroelasticity
Identification methods
Least squares method
New technology
Nonlinearity
Parameter identification
Parameter sensitivity
Robustness (mathematics)
Sensitivity enhancement
Unsteady aerodynamics
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Summary:In this paper, a parameter identification method merged with the precise integration method and the predictor–corrector strategy is proposed to identify the parameters of a nonsmooth aeroelastic system quickly and accurately. Considering the aeroelastic system subject to unsteady aerodynamic force, the parameters that need to be identified include the structural and nonsmooth parameters. The work of this paper mainly includes three parts. First, based on the precise integration method and combined with the predictor–corrector strategy, a new technology that can accurately locate the switching point is proposed to obtain the response of the aeroelastic system with high precision. Then, the problem for identification of parameters of the nonsmooth aeroelastic system is modeled as a nonlinear least-squares problem between the measured data and the calculated response. A new strategy that can obtain the nonsmooth parameters sensitivity matrix accurately is proposed, and then the parameters are identified through the enhanced response sensitivity approach. Finally, the nonsmooth aeroelastic system with freeplay and hysteresis nonlinearity are taken as the numerical examples to demonstrate the feasibility and robustness of the present method.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J061447