Paper Title:
Research on Accessibility of Integral Sliding Mode Contorl of Missile System
  Abstract

Considering the no uncertain air-dynamic coefficients situation, a kind of sliding mode control law, which was composed of the angle velocity and overload error, was designed for the overload control system of missile. And the accessibility of sliding mode was analyzed. What worthy pointing out is that a transfer- function-type backstepping algorithm was adopted to solve the derivative item of actuator and a novel type of control was proposed.

  Info
Periodical
Edited by
Honghua Tan
Pages
212-216
DOI
10.4028/www.scientific.net/AMM.66-68.212
Citation
W. G. Zhang, J. W. Lei, L. L. Wang, "Research on Accessibility of Integral Sliding Mode Contorl of Missile System", Applied Mechanics and Materials, Vols. 66-68, pp. 212-216, 2011
Online since
July 2011
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