Abstract:

An autopilot design scheme is presented with feedback linearization technique against the fast time varying, strong coupling and high nonlinear system of the high speed reentry aerocraft dynamics. Furthermore, a guidance law is proposed by using a combination of optimal guidance law design with ideal velocity curve approach. The terminal guidance accuracy, the direction and amplitude of the aerocraft velocity are guaranteed by using the derivative guidance law. Finally, 6 DOF simulations are made based on a kind of reentry aerocraft. The results show that the proposed control scheme and the guidance law are rational, efficient and easy for implementation.

Key words: reentry aerocraft, guidance, control, feedback linearization, optimal