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.

研究了基于不均匀网格点分布，Chebyshev-Gauss-Lobatto（CGL）和Legendre多项式的根（RLP）的广义微分正交（GDQ）作为精确的数值技术，以有效抑制嵌入有压电（PZT）贴片。该系统的灵活性被建模为具有蜂窝芯的夹芯板，通过高级理论来监视系统的额外振动，以执行高精度任务。通过汉密尔顿原理导出了运动的耦合控制偏微分方程和相应的边界条件。航天器由具有不同激励频率的恒定转矩和谐波转矩操纵，以分析系统的振动灵敏度。应变率反馈（SRF）控制定律用于将PZT动作的效果应用于柔性附件的振动抑制。以刚柔耦合（高阶）动力学为特征的系统的数值研究为分析带有智能夹心附件的机动航天器提供了强大的通用工具，并证明了所提出的公式对于预测柔性高模振动响应的重要性。部分。