Modeling and vibration suppression of flexible spacecraft using higher-order sandwich panel theory

Abstract

This paper presents a novel approach for the modeling and vibration suppression of a flexible spacecraft during a large angle attitude maneuver. A Higher-Order theory is used to model the elastic behavior of solar panel appendages with surface bounded piezoelectric (PZT) patches that capture the transverse shear deformation effects through the thickness of the smart sandwich panel. With the implementation of an appropriate time scales transformation technique and using Singular Perturbation Theory (SPT), the spacecraft dynamic behavior has been divided into double slow and fast subsystems. Modified Sliding Mode (MSM) and Strain Rate Feedback (SRF) control theory have been used for attitude and vibration control simultaneously by global stability proof of the overall system, while the controllers accomplished their missions in coupled rigid/flexible dynamic domain without parasitic parameter interactions. Numerical simulation assesses the benefits of the proposed approach.