Design of an Attitude Control System for Hypersonic Ballistic Missiles with Extendable Swinging Nozzle Control

This research tackles the intricate challenge of attitude control encountered during the nozzle start-up and extension phase subsequent to the stage separation of a hypersonic ballistic missile. A robust attitude control strategy, integrating back-stepping theory with sliding mode control technology, is proposed. Initially, the study formulates a multi-body dynamics model of a hypersonic ballistic missile equipped with an extendable swinging nozzle control mechanism, employing the Newton-Euler method. Leveraging the backstep-ping control principle, a sliding mode control rate is devised through feedback iteration, affirming the stability of the closed-loop system. Ultimately, simulations validate the method's substantial robustness in stabilizing the hypersonic missile during the nozzle extension process amidst aerodynamic parameter perturbations.