Dynamic modeling and vibration control of a coupled rigid-flexible high-order structural system: A comparative study

Abstract

A Generalized Differential Quadrature (GDQ) as an accurate numerical technique based on non-uniform grid point distribution, Chebyshev-Gauss-Lobatto (CGL) and Roots of the Legendre Polynomial (RLP) is investigated for active vibration suppression of flexible spacecraft appendages embedded with piezoelectric (PZT) patches. The flexibility of the system is modeled as a sandwich panel with honeycomb core via high-order theories to monitor extra vibrations of the system for high accuracy missions. The coupled governing partial differential equations of the motion and the corresponding boundary conditions were derived through Hamilton's principle. The spacecraft is maneuvered by constant and harmonic torques with different excitation frequency to analyze the vibration sensitivity of the system. The Strain Rate Feedback (SRF) control law is utilized to apply the effects of PZTs action on vibration suppression of flexible appendages. The numerical study of the system characterized by coupled rigid-flexible (high-order) dynamic provides a powerful general tool for analysis of maneuvering spacecraft with smart sandwich appendages and demonstrates the importance of the proposed formulation for the prediction of higher mode vibration response of flexible parts.