A Simple Differential Sliding Mode Design for the Overload Control of Missile System

Abstract:

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A simple differential sliding mode control law was designed for the missile overload control system without considering the uncertainties of air-dynamic coefficients. The sliding mode was composed of overload error and the differential error of overload. Finally, a numerical simulation was down and it testified that it is unable to make the system stable with only pure overload control strategy. Although the sliding mode was arrived , Oscillation phenomenon was caused by the poles in imaginary axis.

Info:

Periodical:

Edited by:

Honghua Tan

Pages:

207-211

DOI:

10.4028/www.scientific.net/AMM.66-68.207

Citation:

W. G. Zhang et al., "A Simple Differential Sliding Mode Design for the Overload Control of Missile System", Applied Mechanics and Materials, Vols. 66-68, pp. 207-211, 2011

Online since:

July 2011

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Price:

$35.00

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