Sliding Mode Control-Based Guidance Law with Damping Term and Angle Constraint

Based on the sliding mode control theory and Lyapunov stability theory, a finite-time convergence guidance law with attack angle constraint is proposed in this paper. As the initial trajectory of the missile which apply the guidance law with angle constraint is too curved. To reduce the fuel consumption of the missile, a damping term is utilized to design the sliding surface function. To deal with the chattering phenomenon in sliding mode motion process, and guarantee the convergence speed as well, a double power combination function reaching law is adopted to constrain the approaching process. Comparing with the traditional sliding mode guidance law, the guidance law of this paper is able to attack a maneuvering target at a specified angle with less energy consumption, and the response of missile for the movement of target is faster. The effectiveness of this guidance law is demonstrated by simulation experiments.