Research on guidance law based on the finite time control

A continuous guidance law based on finite-time control theory is presented for the plane model between the missile and the target. The proposed guidance law includes the line-of-sight (LOS) angular rate and a desired LOS angular. The LOS angular rate can converge to zero in finite time to guarantee the zero miss-distance between the missile and the target; the LOS angular reaches the desired value in finite time to guarantee the missile attitude of hitting the target. The continuous guidance law can avoid chatting problem of the sliding mode guidance law and have good robustness. The simulation results demonstrate that our method is valid.