Abstract
The event-triggered fixed-time control technique for hypersonic morphing vehicles is discussed in this paper. For simplification, the control-oriented model with morphing-span wings is established. Strong robustness and adaption are demanded since the aerodynamic characteristic change caused by the span morphing is significant. To ensure convergence, the multivariable sliding mode manifold is developed based on fixed-time control technology. The switching dynamic event-triggering mechanism is studied to save the resource of the flight control system. The proposed strategy guarantees a direct control input design. The Lyapunov theory is employed to reveal the fixed-time stability of the closed-loop system. Three simulation cases are introduced to examine the detailed performance.
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