Design of LPV fault-tolerant controller for hypersonic vehicle based on state observer

Guangbin CAI; Yang Zhao; Wanzhen Quan; Xiusheng Zhang

doi:10.3934/jimo.2019120

Article Contents

2021, Volume 17, Issue 1: 447-465. Doi: 10.3934/jimo.2019120 open access

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Design of LPV fault-tolerant controller for hypersonic vehicle based on state observer

1.
College of Missile Engineering, Rocket Force University of Engineering, Xi'an Shaanxi 710025, China
2.
School of Astronautics, Northwestern Polytechnical University, Xi'an Shaanxi 710072, China

^* Corresponding author: Guangbin Cai
^* Corresponding author: Guangbin Cai

Received: February 28, 2019

Revised: March 31, 2019

Early access: September 2019

Published: January 2021

This work was supported in part by the National Natural Science Foundation of China under grant number 61773387, and by China Postdoctoral Fund under grant numbers 2017T100770 and 2016M590971

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Abstract

Considering the parameter uncertainty and actuator failure of hypersonic vehicle during maneuvering, this paper proposes a state observer-based hypersonic vehicle fault-tolerant control (FTC) system design method. Because hypersonic vehicles are prone to failure during maneuvering, the state quantity cannot be measured. First, a state observer-based FTC control method is designed for the linear parameter-varying (LPV) model with parameter uncertainty and partial failure of the actuator. Then, the Lyapunov function is used to demonstrate the asymptotic stability of the closed-loop system. The performance index function proved that the system has robust stability under the disturbance condition. Subsequently, the linear matrix inequality (LMI) was used to solve the observer parameters and the corresponding gain matrix in the control system. The simulation results indicated that the designed controller can track the flight command signal stably and has strong robustness, which verified the effectiveness of the design controller.

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Mathematics Subject Classification: Primary:58F15, 58F17;Secondary:53C35.

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Figure 1. Curve of flight path angle under actuator fault

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Figure 2. Structure diagram of control system

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Figure 3. Velocity curve under actuator fault

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Figure 4. Flight path angle curve under actuator fault

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Figure 5. Attack angle curve under actuator fault

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Figure 6. Altitude curve under actuator fault

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Figure 7. Velocity tracking performance

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Figure 8. Flight path angle tracking performance

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Figure 9. Attack angle tracking performance

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Figure 10. Altitude tracking performance

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Figure 11. Control surface deflection angle curve

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Figure 12. Diffuser area ratio curve

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