Missile acceleration controller design using proportional-integral and non-linear dynamic control design method

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In this article, a method to make the normal acceleration of medium angle of attack missile to track some desired trajectories is presented. The dynamics which describe a missile acceleration are known to be non-minimum phase, which makes it difficult to use a straightforward feedback linearization technique. This article aims at showing that this problem may be overcome by employing cascaded regulations in the non-linear area. First, inner loop controller by dynamical sliding mode control (SMC) method based on asymptotic output tracking is designed for angle of attack control which has a minimum phase characteristics. Also then, the problem that is addressed here is the completion of the global loop by designing an additional outer loop proportional-integral (PI) controller and angle of attack estimator. The performance and stability of proposed method are illustrated via computer simulations.
Publisher
SAGE PUBLICATIONS LTD
Issue Date
2012-08
Language
English
Article Type
Article
Keywords

AUTOPILOT DESIGN; EIGENSTRUCTURE ASSIGNMENT; SYSTEMS

Citation

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, v.226, no.G8, pp.882 - 897

ISSN
0954-4100
DOI
10.1177/0954410011417510
URI
http://hdl.handle.net/10203/104306
Appears in Collection
AE-Journal Papers(저널논문)
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