Analysis and design of terminal guidance with large angular on a saucer-shaped UAV

摘要

According to the requirements for terminal angular constraint of the missile guidance, combined with low-velocity characteristic and stealth advantage of the saucer-shaped lifting body Unmanned Aerial Vehicle (UAV), a control and guidance law need to be designed for achieving precise terminal guidance with expected attitude angle. This kind of aircraft usually has no vertical fin and rudder which makes it has bad lateral maneuverability. In this paper, the aircraft installed two direct thrust nozzles providing with yawing moment; for making the best of the nozzles, a guidance law based on Lyapunov stability is adopted, along with an overload feedback controller is designed, which is a blended control strategy of direct thrust and aerodynamic force. Simulation results show that, compared with the controller without direct thrust nozzles, the nozzles control can improve lateral maneuverability and attain more precise guiding with larger terminal angular hitting the target.