Robust Adaptive Optimized Tracking Control for a Hypersonic Vehicle with Varying Uncertainties

In this paper, a robust adaptive tracking control law is designed and optimized for a multistage hypersonic vehicle (HV) tracking reference command in the existence of unknown but bounded varying system uncertainties during ascent stage. The original problem is transformed into a second-order error tracking system. Based on nonlinear dynamic inversion control and robust adaptive control, the proposed approach can resist model uncertainties and achieve tracking to the reference of angle of pitch, and the stability of the closed-loop system is theoretically proved. Simulation results demonstrate the effectiveness of the control law under the condition of certain specific uncertainties. Moreover, a cost function that represents the consumption of controller and integrated tracking error is introduced. Then, parameters of the control law are optimized with genetic algorithm (GA), and the ultimate optimized parameter combinations for nominal and uncertain systems are directly tested.