Design of a STT missile autopilot using functional inversion and LMI approach

摘要

We present a systematic approach for the autopilot design of skid-to-turn (STT) missiles. First, the nonlinear model of a STT missile is partially linearized via functional inversion techniques and then, the additional set-point tracking controller can be designed by the well-known LMI approach. The stabilization conditions are given in terms of LMIs.