Feedback linearization for a nonlinear skid-to-turn missile model

In this paper a feedback linearization approach for a nonlinear skid-to-turn (STT) missile model has been discussed. In this work most realistic nonlinearities in the missile dynamics, including the coupling effect between pitch and yaw channels due to the effect of bank angle, are taken into full account missile velocity and air density are assumed to be constant or slow-varying variables. Furthermore, the total angle of attack need not be assumed to be confined to small values for autopilot stability. Specifically, exact input-output (I/O) feedback linearization based on a nominal model has been carried out. Thereby, the I/O dynamic characteristics of the pitch and yaw channels can be made linear decoupled. More importantly, the dynamics becomes independent of flight conditions such as missile velocity and air density. The technique applied in this work is useful for the autopilot design of highly maneuvering STT missiles.