Prescribed Performance Fine Attitude Control for Aeroelastic Hypersonic Vehicle

doi:10.3969/j.issn.1000-1093.2017.03.012

Abstract

Abstract: A fine attitude controller for hypersonic cruise vehicle is designed by combining the backstepping technique, prescribed performance control and neural network. The influence of elastic deformation of hypersonic vehicle on angle of attack is taken into consideration. The effect of aeroelasticity on hypersonic vehicle is described by using the induced angle of attack. The index of fine attitude control is satisfied by the design of prescribed performance in consideration of aeroelasticity, and the transient performance of hypersonic vehicle is assured. The unknown terms of the induced angle-of-attack equations are approximated online by using the fully tuned dynamic neural networks, and the adaptive laws of weight, core and scope of influence of the neural networks are designed by Lyapunov theory. The robust term is induced to solve the approximate errors of the neural networks. A fine attitude controller with prescribed performance for hypersonic vehicle in considering the aeroelasticity is designed. The stability of system and all the signals in the closed-loop system bounded are proved by Lyapunov theory. The simulated results show that the controller can make the tracking errors satisfy the prescribed performance, and the fine attitude control can be implemented. Key

Key words: ordnancescienceandtechnology, hypersonicvehicle, aeroelasticity, prescribedperformance, sophisticatedattitudecontrol, inducedangleofattack

CLC Number:

V249.122⁺.2

ZHAO He-wei, YANG Xiu-xia, SHEN Ru-song, HU Yun-an. Prescribed Performance Fine Attitude Control for Aeroelastic Hypersonic Vehicle[J]. Acta Armamentarii, 2017, 38(3): 501-511.

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第38卷
第3期2017 年3月兵工学报ACTA
ARMAMENTARIIVol.38No.3Mar.2017

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