Robust Non-fragile Negative Imaginary H\infty Synthesis for Attitude Stabilization of Flexible Spacecrafts With Input Constraint

• Published in: IEEE transactions on aerospace and electronic systems pp. 1 - 15
• Main Authors: Cheng, Zhining, He, Zhen, Meng, Fanwei, Zhou, Di, Li, Siyuan
• Format: Journal Article
• Language: English
• Published: IEEE 10.05.2025
• Subjects: Accuracy; Actuators; Attitude control; Attitude stabilization; Closed loop systems; flexible spacecraft; input constraint; Intelligent materials; negative imaginary system; non-fragile control; Perturbation methods; Space vehicles; Transfer functions; Uncertainty; Vibrations
• DOI: 10.1109/TAES.2025.3569514
• ISSN: 0018-9251

High-precision attitude stabilization of flexible spacecraft with model uncertainty, external disturbance, actuator fault and input constraint is investigated in this paper. A robust non-fragile negative imaginary (NI) <inline-formula><tex-math notation="LaTeX">H_\infty</tex-math></inline-formula> synthesis scheme is developed, rendering the closed-loop system asymptotically stable and NI with <inline-formula><tex-math notation="LaTeX">H_\infty</tex-math></inline-formula> norm bounded. Meanwhile, the control input <inline-formula><tex-math notation="LaTeX">u</tex-math></inline-formula> is constrained by the specified upper bound. With a convex relaxation of Bilinear Matrix Inequalities (BMIs), the controller synthesis is cast as a convex optimization problem subject to Linear Matrix Inequality (LMI) constraints. The notable feature of the proposed method is that it achieves flexible vibration suppression and high-precision attitude stabilization simultaneously without requiring additional measurements or intelligent materials. The convergence of the LMIs-based iterative algorithm is guaranteed by a rigorous proof. Finally, comparative simulations demonstrate the effectiveness of the proposed method with high steady-state accuracy and low energy consumption.