Guidance with terminal impact angular constraint for hybrid BTT/STT flight vehicle

Guidance law to guide the unpowered flight vehicle to attack ground target vertically is needed in modem warfare, and hybrid BTT/STT guidance command allocation is also needed to reduce the response time of the guidance system. A guidance law design method based on Lyapunov stability theory is proposed, and a guidance law with sight angle and sight angle velocity as feedback variables is designed in longitudinal plane of the vehicle motion. A guidance law aiming at eliminating lateral position error is based the same method is also presented. Guidance command allocation method based on the overload command and current bank angle is proposed to reduce the response time of the guidance system. Numerical simulation shows that the proposed guidance law and guidance command allocation method can improve the guidance precision of the vehicle.