Flexible satellite with honeycomb panels’ boundary control by considering actuator failure

Abstract

This study focuses on the boundary control of flexible satellites equipped with honeycomb panels using Lyapunov's direct method. The panels are modeled as Euler–Bernoulli beams, and the govern ing dynamic equations are derived through Hamilton's principle. A novel Lyapunov function candidate is introduced, and asymptotic stability is rigorously established through the extended LaSalle's invariance principle. Control input laws are strategically developed to handle actuator failures while ensuring stability with minimal sensor utilization. Numerical simulations, performed using the assumed mode method, validate the theoretical findings. The results underscore key contributions, including guaranteed asymptotic stability, large-angle maneuvering capabilities, robustness to actuator failures, and the prevention of spillover instability phenomena. © 2025 COSPAR