摘要：Aiming at the guidance problem with attack angle when missiles impact ground targets, a sliding mode guidance law with autopilot second-order dynamic lag compensation is proposed based on the backstepping method. A fast sliding mode surface is presented to certify the finite-time convergences of the line-of-sight (LOS) angle rate and attack angle. In addition, the differential expansion problem of backstepping method is settled via designing integration Lyapunov functions, which is helpful for expanding engineering application fields of this method. In terms of Lyapunov stability theory, it is demonstrated that all states in the closed-loop system converge to equilibrium point in finite time. Finally, the presented guidance law is simulated in different situations and the results indicate that the control law can compensate autopilot dynamic lag and obtain the desired LOS angle.
