IJCAS

Taking into consideration both the autopilot dynamics and uncertainties, this paper proposes a finite time convergent guidance law for homing missile to intercept a maneuvering target. Firstly, an exact observer (differentiator) is employed to estimate the target maneuvers in finite time. Then, a fini-te time convergent guidance law is designed based on the existing finite time sliding-mode control the-ory. It is proved that the line-of-sight (LOS) angular rate converges to zero in finite time under the pro-posed guidance law. Compared with the existing finite time guidance laws, this guidance law can com-pensate for the effects of the autopilot dynamics and uncertainties, and the information used for feed-back control is much easier to obtain. Finally, simulation results show that our scheme, as a finite time convergent algorithm, has strong robustness to bounded disturbances.

Keywords: Autopilot dynamics, finite time convergence, guidance law, maneuvering target, robustness, uncertainties.