An Integral Controller For Lateral Missile Autopilot Based On Pole-placement Design

摘要

A lateral autopilot design approach has been proposed for a class of tail-controlled missiles having uncertain aerodynamic forces and moments based on incomplete state feedback with integral and feedforward control. The complicacy of designing and implementing an observer is avoided. The design procedure is simple to use and generic formulae for controller gains have been derived in terms of semi-non-dimensional airframe and actuator parameter values. A procedure for the choice of closed-loop poles has been suggested. A methodology for robust trajectory tracking in presence of parameter uncertainty has been presented. The design ensures specified stability margins at different speeds of response. An illustrative example has been provided to demonstrate the effectiveness of the methodology.