NDLI: Robust pseudo-linearising autopilot for a quasi-linear parameter varying missile model

Content Provider	IEEE Xplore Digital Library
Author	Tsourdos, A. Zbikowski, R. White, B.A.
Copyright Year	2000
Description	Author affiliation: Dept. of Aerosp., Power & Sensors, Cranfield Univ., Swindon, UK (Tsourdos, A.)
Abstract	A sideslip velocity autopilot is designed for a model of a tactical missile and robust stability of the closed-loop system investigated. The tail-controlled missile in the cruciform fin configuration is modelled as a second-order quasi-linear parameter-varying system. This nonlinear model is obtained from the Taylor linearised model of the horizontal motion by including explicit dependence of the aerodynamic derivatives on a state and external parameters. The autopilot design is based on input-output pseudo-linearisation, which is the restriction of input-output feedback linearisation to the set of equilibria of the nonlinear model. The design makes Taylor linearisation of the closed-loop system independent of the choice of equilibria. Simulations for constant lateral acceleration demands show good tracking with fast response time. Parametric stability margins for uncertainty in the controller parameters and aerodynamic derivatives are analysed using quadratic Lyapunov approach.
Starting Page	4077
Ending Page	4081
File Size	433573
Page Count	5
File Format	PDF
ISBN	0780355199
ISSN	07431619
DOI	10.1109/ACC.2000.876988
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2000-06-28
Access Restriction	Subscribed
Rights Holder	American Automatic Control Council(AACC)
Subject Keyword	Robustness Missiles Power system modeling Aerodynamics Robust stability Sensor systems Feedback Delay Stability analysis Uncertainty
Content Type	Text
Resource Type	Article
Subject	Electrical and Electronic Engineering

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