A guidance law with finite time convergence accounting for autopilot lag

摘要

Mailbox 327, School of Astronautics, Harbin Institute of Technology, 150001 Harbin, PR China;Mailbox 327, School of Astronautics, Harbin Institute of Technology, 150001 Harbin, PR China;Mailbox 327, School of Astronautics, Harbin Institute of Technology, 150001 Harbin, PR China;%By considering the dynamics of a missile's autopilot as a first-order lag, a guidance law with finite time convergence is designed based on target-missile relative motion equations. It is rigorously proved that states of the guidance system converge to a sliding-mode in finite time and the line-of-sight (LOS) angular rate converges to zero in finite time under the proposed guidance law. Simulation results show that the guidance law is robust against target maneuvers and is able to compensate for the autopilot lag.