A control function that uses Integral Sliding Mode Control aims to minimize the effects of unmatched disturbances by selecting optimal values for design parameters of the sliding surface. This technique is applied to a rocket stabilization problem. A rocket autopilot for the pitch plane is studied, and it is shown that there is the unmatched disturbance present in the system. Because the disturbance is unmatched, it cannot be completely compensated by Integral sliding mode control. By applying robust controller techniques, the goal is to compensate entirely for the matched disturbances while minimizing the effects of the unmatched disturbances. The efficacy of the studied Integral sliding mode control technique is confirmed via computer simulation of a simple rocket autopilot.
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