Prediction and validation of aeroelastic limit cycle oscillations using harmonic balance methods and Koopman operator
Prediction and validation of aeroelastic limit cycle oscillations using harmonic balance methods and Koopman operator
Nonlinearities in aerospace systems often induce self-sustaining oscillations known as Limit Cycle Oscillations (LCO), requiring costly analyses for identification. A major challenge is the computational expense of generating bifurcation diagrams, which limits the feasibility of nonlinear analysis in early design phases. This restriction not only constrains design possibilities but also impedes data-driven methods for nonlinear aeroelastic analysis, which rely on efficient data collection-a growing focus in the aerospace sector. This work proposes a computationally efficient numerical framework to predict LCO amplitudes and assess stability in nonlinear aeroelastic systems. The approach integrates the Harmonic Balance Method with the Hill method for stability analysis. To address the sorting problem, a Koopman operator-based data-driven method is employed. The framework is validated using numerical test cases with both smooth and nonsmooth nonlinearities, benchmarked against results from MATCONT, COCO and time-domain simulations. Finally, experimental validation is performed by comparing the framework’s predictions with LCO experimental data obtained through control-based continuation experiments.
Nonlinear aeroelasticity, Numerical continutation, Stability analysis
McGurk, Michael
ff8abe6b-24b8-4d53-8af2-c735ddf26d4f
Yuan, Jie
4bcf9ce8-3af4-4009-9cd0-067521894797
17 March 2025
McGurk, Michael
ff8abe6b-24b8-4d53-8af2-c735ddf26d4f
Yuan, Jie
4bcf9ce8-3af4-4009-9cd0-067521894797
McGurk, Michael and Yuan, Jie
(2025)
Prediction and validation of aeroelastic limit cycle oscillations using harmonic balance methods and Koopman operator.
Nonlinear Dynamics, [012008].
(doi:10.1007/s11071-025-11065-8).
Abstract
Nonlinearities in aerospace systems often induce self-sustaining oscillations known as Limit Cycle Oscillations (LCO), requiring costly analyses for identification. A major challenge is the computational expense of generating bifurcation diagrams, which limits the feasibility of nonlinear analysis in early design phases. This restriction not only constrains design possibilities but also impedes data-driven methods for nonlinear aeroelastic analysis, which rely on efficient data collection-a growing focus in the aerospace sector. This work proposes a computationally efficient numerical framework to predict LCO amplitudes and assess stability in nonlinear aeroelastic systems. The approach integrates the Harmonic Balance Method with the Hill method for stability analysis. To address the sorting problem, a Koopman operator-based data-driven method is employed. The framework is validated using numerical test cases with both smooth and nonsmooth nonlinearities, benchmarked against results from MATCONT, COCO and time-domain simulations. Finally, experimental validation is performed by comparing the framework’s predictions with LCO experimental data obtained through control-based continuation experiments.
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s11071-025-11065-8
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Accepted/In Press date: 28 February 2025
Published date: 17 March 2025
Keywords:
Nonlinear aeroelasticity, Numerical continutation, Stability analysis
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Local EPrints ID: 499719
URI: http://eprints.soton.ac.uk/id/eprint/499719
ISSN: 0924-090X
PURE UUID: 5b8ef19f-1a74-44b5-91af-18027be384d3
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Date deposited: 01 Apr 2025 16:40
Last modified: 30 Aug 2025 02:14
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Author:
Michael McGurk
Author:
Jie Yuan
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