Feedback linearization autopilot design for the advanced kinetic energy missile boost phase

Abstract

This paper describes an application of feedback linearization to the design of an autopilot for the boost phase of the advanced kinetic energy missile, a hypervelocity missile being developed by the U.S. Army Missile Command. The rapid change in missile states during the boost phase, coupled with a requirement for accurate guidance, provide a challenge for the autopilot designer. Application of the feedback linearization methodology permitted an autopilot design to be successfully accomplished without the necessity for generating numerous airframe transfer functions and frozen-point stability plots. The resulting autopilot is easily updated to accommodate changes in the missile design.