Missile rolling attitude control method added with integrator dynamic amplitude limiting

The invention discloses a missile rolling attitude control method with integrator dynamic amplitude limiting, and belongs to the technical field of flight control. The method comprises the steps that a guidance instruction resolving unit calculates a rolling instruction of a missile and sends the rolling instruction to a rolling attitude controller, and a sensitive element unit measures the rolling angular velocity of the missile and sends the rolling angular velocity to the rolling attitude controller; the rolling attitude controller calculates the upper bound and the lower bound of the output value of the integrator according to the maximum available rudder deviation; amplitude limiting is carried out on integrator output according to the upper bound and the lower bound; calculating the output of a variable structure controller according to the information subjected to amplitude limiting processing; calculating a rolling rudder instruction according to the output of the variable structure controller and the