High angle of attack missile autopilot design by pole placement approach

Abstract

This paper presents the missile autopilot design for 180° heading reversal maneuver. For this purpose, angle of attack controller using pole placement approach is designed. The three autopilot gains can be computed from aerodynamic coefficients and three design parameters to satisfy some designer-chosen criteria. Design parameters are closed-loop frequency, damping ratio, and time constant, representing the characteristics of control system. To deal with nonlinear control problems in high angle of attack missile, gain scheduled technique is employed. The simulation results validate performances and capabilities of the control system.