Neural control of hypersonic flight dynamics with actuator fault and constraint

This paper deals with the control problem of actuator fault and saturation for hypersonic flight vehicles. Different from previous back-stepping design, the scheme is on transforming the dynamics into the "prediction function". The controller is constructed with high gain observer, while the effect...

Full description

Saved in:
Bibliographic Details
Published inScience China. Information sciences Vol. 58; no. 7; pp. 68 - 77
Main Authors Wang, ShiXing, Zhang, Yu, Jin, YuQiang, Zhang, YongQuan
Format Journal Article
LanguageEnglish
Published Beijing Science China Press 01.07.2015
Springer Nature B.V
Subjects
Online AccessGet full text
ISSN1674-733X
1869-1919
DOI10.1007/s11432-015-5338-2

Cover

More Information
Summary:This paper deals with the control problem of actuator fault and saturation for hypersonic flight vehicles. Different from previous back-stepping design, the scheme is on transforming the dynamics into the "prediction function". The controller is constructed with high gain observer, while the effect of fault and saturation is compensated by neural networks. For the input saturation, the auxiliary dynamics is included to design the adaptive learning law. The neural weights and filtered tracking error are guaranteed to be bounded via Lyapunov approach. The effectiveness of the proposed method is verified by simulation of winged-cone model.
Bibliography:11-5847/TP
This paper deals with the control problem of actuator fault and saturation for hypersonic flight vehicles. Different from previous back-stepping design, the scheme is on transforming the dynamics into the "prediction function". The controller is constructed with high gain observer, while the effect of fault and saturation is compensated by neural networks. For the input saturation, the auxiliary dynamics is included to design the adaptive learning law. The neural weights and filtered tracking error are guaranteed to be bounded via Lyapunov approach. The effectiveness of the proposed method is verified by simulation of winged-cone model.
hypersonic flight vehicle, no back-stepping, neural network, longitudinal dynamics, stability
ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
ISSN:1674-733X
1869-1919
DOI:10.1007/s11432-015-5338-2