An effective integral control law for rolling airframe missiles with a single plane of control surfaces

The dynamics of rolling airframes with a single plane of control surfaces shows periodic properties. This paper introduces an acceleration control law for the rolling airframes. An analysis shows that the nonlinear part of the proposed control law works as an effective integrator on acceleration errors in the sense of averaging cycles of rolling. The control law can be considered as a type of repetitive control, but it does not need any a priori information on the period of control signals. Simulations for an example confirm the performance of the control systems.