Research on Accessibility of Integral Sliding Mode Contorl of Missile System
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.
W. G. Zhang et al., "Research on Accessibility of Integral Sliding Mode Contorl of Missile System", Applied Mechanics and Materials, Vols. 66-68, pp. 212-216, 2011