Abstract: Based on the singular perturbation theory and feedback linearization methodology, a new guidance is obtained by constructing a composite control law from a climbing phase control, cruising phase control and switching phase control. In order to reduce onboard computation, a simple close loop guidance algorithm is given. Finally, the simulation results of a certain kind of air to air missile is presented. It is shown that application of the new guidance law results in smaller heading errors at handover.

Key words: midcourse guidance law, singular pertur bation t heory, long- and medium- rangeair -to-air missiles