Scaling law for the slow flow of an unstable mechanical system coupled to a nonlinear energy sink

TL;DR

This paper derives a scaling law for the slow flow of an unstable mechanical system coupled to a nonlinear energy sink, improving predictions of the mitigation limit near a fold point using bifurcation analysis and reduced-order modeling.

Contribution

It introduces a novel scaling law for the slow flow dynamics near a fold point, enhancing the accuracy of mitigation limit predictions for systems with NES.

Findings

Derived a scaling law involving fractional exponents 1/3 and 2/3.

Validated the theoretical predictions with numerical simulations.

Provided a new approach to analyze slow flow in coupled nonlinear systems.

Abstract

In this paper one first shows that the slow flow of a mechanical system with one unstable mode coupled to a Nonlinear Energy Sink (NES) can be reduced, in the neighborhood of a fold point of its critical manifold, to a normal form of the dynamic saddle-node bifurcation. This allows us to then obtain a scaling law for the slow flow dynamics and to improve the accuracy of the theoretical prediction of the mitigation limit of the NES previously obtained as part of a zeroth-order approximation. For that purpose, the governing equations of the coupled system are first simplified using a reduced-order model for the primary structure by keeping only its unstable modal coordinates. The slow flow is then derived by means of the complexification-averaging method and, by the presence of a small perturbation parameter related to the mass ratio between the NES and the primary structure, it appears as a fast-slow system. The center manifold theorem is finally used to obtain the reduced form of the slow flow which is solved analytically leading to the scaling law. The latter reveals a nontrivial dependence with respect to the small perturbation parameter of the slow flow dynamics near the fold point, involving the fractional exponents 1/3 and 2/3. Finally, a new theoretical prediction of the mitigation limit is deduced from the scaling law. In the end, the proposed methodology is exemplified and validated numerically using an aeroelastic aircraft wing model coupled to one NES.