Non-singular Sliding Mode Control of Non-minimum Phase Hypersonic Vehicles

doi:10.12382/bgxb.2023.1158

Abstract

Abstract:

A sliding mode control strategy based on Byrnes-Isidori (B-I) standard is proposed to solve the tracking and controlling problems of non-minimum phase hypersonic vehicles under external disturbance. A new integral sliding mode surface and a novel composite reaching law are designed. The exponential and sign functions are combined in the reaching law to enhance the anti-vibration capability and rapid convergence performance of the hypersonic vehicle. A robust sliding mode controller is constructed to ensure the asymptotic stability of internal dynamics by using the sliding mode control method. And a non-singular terminal sliding mode controller is constructed to ensure the practical finite time stability of velocity tracking error and the bounded stability of external dynamics. Combining the robustness and fast convergence speed of the non-singular terminal sliding mode control, a terminal sliding mode disturbance observer is designed to solve the external disturbance in the velocity subsystem and altitude subsystem.The stability is proved by using the Lyapunov theory, proving the practical finite-time stability of the estimation error. The effectiveness of the control strategy based on the B-I standard is verified by simulation comparison.

Key words: hypersonic vehicle, non-minimum phase, disturbance observer, non-singular sliding mode control

CLC Number:

V212.13

WEI Qiaoling, DU Yuxin, ZHOU Chao, WANG Fang. Non-singular Sliding Mode Control of Non-minimum Phase Hypersonic Vehicles[J]. Acta Armamentarii, 2024, 45(11): 3949-3958.

Figures/Tables 5

Fig.1 Velocity and velocity tracking error

Fig.2 Altitude and altitude tracking error

Fig.3 Tracking errors of pitch angle and flight path angle

Fig.4 Internal state

Fig.5 Control input

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