Inerter-Based Eigenvector Orientation Approach for Passive Control of Supersonic Panel Flutter

Inspired by the mass amplification property of inerters, an inerter-based passive panel flutter control procedure is developed and proposed. Formulations of aeroelastic equations of motion are based on the use of a wide-beam (flat panel) element stiffness equation subjective to supersonic flow using piston theory. The onset of flutter is analyzed using an eigenvector orientation approach, which may provide the advantage of lead time while the angle between eigenvectors of the first two coalescing modes reduces towards zero. The mass amplification effect of inerters is described and incorporated into the aeroelastic equation of motion of the passive actuation system for the investigation of flutter control. To demonstrate the potential applicability and usefulness of the proposed formulation and procedure, two numerical examples with one and two inerters, respectively, to optimally control the flutter of the panel modeled by wide-beam elements are presented. The results of the numerical simulation of the present examples demonstrate that the present inerter-based method can offset the onset of flutter to a higher level of aerodynamic pressure by optimizing the effective mass ratios and locations of inerters. In addition, this paper demonstrates that fundamental modes may be playing a role when identifying the optimal location of the inerters. It appears that the placement of the inerters may be more effective in controlling flutter at the highest amplitude of the mode shape along the wide beam. The procedure developed in this study may be of use for practical application for passive panel flutter control.