Autopilot design for the advanced kinetic energy missile (ADKEM) boost phase

This paper describes an application of the feedback linearization design methodology to the development of a time-varying autopilot for the Advanced Kinetic Energy Missile (ADKEM). ADKEM is a hypervelocity missile being developed at the U.S. Army Missile Command (MICOM). The missile is vertically launched, carries a kinetic energy penetrator as a warhead, and is designed for use against stationary and moving hard (ground) and soft (airborne) targets. The rapid change in missile states over the short time duration of the boost phase, the inherent nonlinearities associated with the system, and a requirement for accurate guidance during boost provide an interesting challenge for the autopilot designer.