Abstract:

In terms of the terminal guidance of intercepting the endoatmospheric maneuvering targets, an adaptive integral sliding-mode guidance law is presented. Based on the principle of suppressing the rotation of the line of sight from a missile to a target, a tracking profile is designed where the convergence rate of the line of sight can be regulated. The tracking error and its integral are selected as the state variables. An integral sliding-mode surface of the states converging to zero in finite time and a rapid reaching law are used to derive an integral sliding-mode guidance law. To deal with an unknown target maneuver, an adaptive algorithm is proposed to estimate the square of the upper bound of the target maneuver, and then the adaptive integral sliding-mode guidance law is constructed. The finite-time convergence characteristic of the law is proven, and the convergence regions are given of the state variables.Finally, the guldance law is converted into the corresponding form suitable for the endoatmosphenc interception. The simulation results indicate that the proposed guidance law can precisely intercept the maneuvering targets and the convergence rate is rapid of the tracking error. The overload distribution is reasonable, and less energy is consumed. Furthermore, the law possesses good profile noise characteristics and is easy to be implemented in practice.

Key words: Missile guidance, Maneuvering target, Integral sliding-mode surface, Adaptive algorithm, Finite-time convergence