Design of terminal sliding-mode guidance law with attack angle constraints

The design of guidance law with terminal line of sight constraint for maneuvering target intercept is investigated for relative motion between missile and target in two-dimension plane. Applying finite time stability theory and sliding model variable structure control method, a traditional nonlinear sliding mode guidance law is proposed. Subsequently, a new sliding mode guidance law avoiding singularity which guarantees the rate of line of sight go to zero with expected line of sight in the end of terminal guidance. Simulations demonstrate the effectiveness of proposed method.